From 028511c7ef9e413a02c173c925a98dd21b6765ba Mon Sep 17 00:00:00 2001 From: GBenedett Date: Mon, 5 Feb 2024 14:41:48 +0100 Subject: [PATCH 01/55] ThermoData branch --- ceasiompy/SU2Run/func/su2config.py | 2 +- 1 file changed, 1 insertion(+), 1 deletion(-) diff --git a/ceasiompy/SU2Run/func/su2config.py b/ceasiompy/SU2Run/func/su2config.py index 7b77a9bc6..20bb061af 100644 --- a/ceasiompy/SU2Run/func/su2config.py +++ b/ceasiompy/SU2Run/func/su2config.py @@ -341,7 +341,7 @@ def generate_su2_cfd_config(cpacs_path, cpacs_out_path, wkdir): if aeromap_list: aeromap_default = aeromap_list[0] - log.info(f'The aeromap is {aeromap_default}') + log.info(f"The aeromap is {aeromap_default}") aeromap_uid = get_value_or_default(cpacs.tixi, SU2_AEROMAP_UID_XPATH, aeromap_default) From 43beb2fb9ff9f66d3f7c5abddc6cd58da2cf188b Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Wed, 7 Feb 2024 10:08:55 +0100 Subject: [PATCH 02/55] test commit --- ceasiompy/SU2Run/su2run.py | 2 +- 1 file changed, 1 insertion(+), 1 deletion(-) diff --git a/ceasiompy/SU2Run/su2run.py b/ceasiompy/SU2Run/su2run.py index 4b103b22c..132a0a17f 100644 --- a/ceasiompy/SU2Run/su2run.py +++ b/ceasiompy/SU2Run/su2run.py @@ -16,7 +16,7 @@ * complete input/output in __specs__ * Check platform with-> sys.platform * Move run_SU2_fsi to /SU2Run/func/su2fsi.py - +test """ # ================================================================================================= From af40f2b19ae7301fd2461006119fd5a3626ccca9 Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Wed, 7 Feb 2024 10:11:59 +0100 Subject: [PATCH 03/55] new commit --- ceasiompy/SU2Run/func/su2config.py | 29 ++ ceasiompy/SU2Run/func/su2configrans.py | 564 +++++++++++++++++++++++++ ceasiompy/SU2Run/su2run.py | 2 +- ceasiompy/utils/commonnames.py | 3 + ceasiompy/utils/commonxpath.py | 4 + 5 files changed, 601 insertions(+), 1 deletion(-) create mode 100644 ceasiompy/SU2Run/func/su2configrans.py diff --git a/ceasiompy/SU2Run/func/su2config.py b/ceasiompy/SU2Run/func/su2config.py index 20bb061af..07ba8b606 100644 --- a/ceasiompy/SU2Run/func/su2config.py +++ b/ceasiompy/SU2Run/func/su2config.py @@ -20,6 +20,7 @@ # IMPORTS # ================================================================================================= +import numpy as np from pathlib import Path from shutil import copyfile @@ -64,6 +65,8 @@ SU2_ROTATION_RATE_XPATH, SU2_TARGET_CL_XPATH, SU2MESH_XPATH, + ENGINE_TYPE_XPATH, + ENGINE_BC, ) from ceasiompy.utils.configfiles import ConfigFile from cpacspy.cpacsfunctions import ( @@ -294,6 +297,29 @@ def add_actuator_disk(cfg, cpacs, case_dir_path, actuator_disk_file, mesh_marker f.close() +# adding the results of ThermoData to the config file of su2 + + +def add_thermodata(cfg, cpacs, alt, case_nb, alt_list): + + if cpacs.tixi.checkElement(ENGINE_TYPE_XPATH): + log.info("adding engine BC to the SU2 config file") + engine_type = get_value(cpacs.tixi, ENGINE_TYPE_XPATH) + log.info(f"engine type {engine_type}") + alt = alt_list[case_nb] + Atm = Atmosphere(alt) + tot_temp_in = Atm.temperature[0] + tot_pressure_in = Atm.pressure[0] + tot_temp_out = get_value(cpacs.tixi, ENGINE_BC + "/temperatureOutlet").split(";") + tot_pressure_out = get_value(cpacs.tixi, ENGINE_BC + "/pressureOutlet").split(";") + tot_temp_out = tot_temp_out[case_nb] + tot_pressure_out = tot_pressure_out[case_nb] + cfg["INLET_TYPE"] = "TOTAL_CONDITIONS" + cfg[ + "MARKER_INLET" + ] = f"(INLET_ENGINE, {tot_temp_in}, {tot_pressure_in}, {1},{0},{0}, OUTLET_ENGINE,{tot_temp_out}, {tot_pressure_out}, {1},{0},{0} )" + + def generate_su2_cfd_config(cpacs_path, cpacs_out_path, wkdir): """Function to create SU2 config file. @@ -448,6 +474,7 @@ def generate_su2_cfd_config(cpacs_path, cpacs_out_path, wkdir): cfg["HISTORY_OUTPUT"] = "(INNER_ITER, RMS_RES, AERO_COEFF)" # Parameters which will vary for the different cases (alt,mach,aoa,aos) + for case_nb in range(len(alt_list)): cfg["MESH_FILENAME"] = str(su2_mesh) @@ -470,6 +497,8 @@ def generate_su2_cfd_config(cpacs_path, cpacs_out_path, wkdir): f"_aoa{round(aoa, 1)}_aos{round(aos, 1)}" ) + add_thermodata(cfg, cpacs, alt, case_nb, alt_list) + case_dir_path = Path(wkdir, case_dir_name) if not case_dir_path.exists(): case_dir_path.mkdir() diff --git a/ceasiompy/SU2Run/func/su2configrans.py b/ceasiompy/SU2Run/func/su2configrans.py new file mode 100644 index 000000000..09e141fb3 --- /dev/null +++ b/ceasiompy/SU2Run/func/su2configrans.py @@ -0,0 +1,564 @@ +""" +CEASIOMpy: Conceptual Aircraft Design Software + +Developed by CFS ENGINEERING, 1015 Lausanne, Switzerland + +Function generate or modify SU2 configuration files + +Python version: >=3.8 + +| Author: Aidan Jungo +| Creation: 2020-02-24 + +TODO: + + * add and test control surface functions + +""" + +# ================================================================================================= +# IMPORTS +# ================================================================================================= + +from pathlib import Path +from shutil import copyfile + +from ambiance import Atmosphere +from ceasiompy.SU2Run.func.su2actuatordiskfile import ( + get_advanced_ratio, + get_radial_stations, + save_plots, + thrust_calculator, + write_actuator_disk_data, + write_header, +) +from ceasiompy.SU2Run.func.su2utils import get_mesh_markers, get_su2_config_template +from ceasiompy.utils.ceasiomlogger import get_logger +from ceasiompy.utils.commonnames import ( + ACTUATOR_DISK_FILE_NAME, + ACTUATOR_DISK_INLET_SUFFIX, + ACTUATOR_DISK_OUTLET_SUFFIX, + CONFIG_CFD_NAME, + SU2_FORCES_BREAKDOWN_NAME, +) +from ceasiompy.utils.commonxpath import ( + GMSH_SYMMETRY_XPATH, + PROP_XPATH, + RANGE_XPATH, + SU2_ACTUATOR_DISK_XPATH, + SU2_AEROMAP_UID_XPATH, + SU2_BC_FARFIELD_XPATH, + SU2_BC_WALL_XPATH, + SU2_CFL_NB_XPATH, + SU2_CFL_ADAPT_XPATH, + SU2_CFL_ADAPT_PARAM_DOWN_XPATH, + SU2_CFL_ADAPT_PARAM_UP_XPATH, + SU2_CFL_MAX_XPATH, + SU2_CFL_MIN_XPATH, + SU2_CONTROL_SURF_XPATH, + SU2_DAMPING_DER_XPATH, + SU2_DEF_MESH_XPATH, + SU2_FIXED_CL_XPATH, + SU2_MAX_ITER_XPATH, + SU2_MG_LEVEL_XPATH, + SU2_ROTATION_RATE_XPATH, + SU2_TARGET_CL_XPATH, + SU2MESH_XPATH, + ENGINE_TYPE_XPATH, + ENGINE_BC, +) +from ceasiompy.utils.configfiles import ConfigFile +from cpacspy.cpacsfunctions import ( + create_branch, + get_string_vector, + get_value, + get_value_or_default, +) +from cpacspy.cpacspy import CPACS + +log = get_logger() + +MODULE_DIR = Path(__file__).parent + + +# ================================================================================================= +# CLASSES +# ================================================================================================= + + +# ================================================================================================= +# FUNCTIONS +# ================================================================================================= + + +def add_damping_derivatives(cfg, wkdir, case_dir_name, rotation_rate): + """Add damping derivatives parameter to the config file and save them to their respective + directory. + + Args: + cfg (ConfigFile): ConfigFile object. + wkdir (Path): Path to the working directory + case_dir_name (str): Name of the case directory + rotation_rate (float): Rotation rate that will be impose to calculate damping derivatives + """ + + cfg["GRID_MOVEMENT"] = "ROTATING_FRAME" + + cfg["ROTATION_RATE"] = f"{rotation_rate} 0.0 0.0" + case_dir = Path(wkdir, f"{case_dir_name}_dp") + case_dir.mkdir() + cfg.write_file(Path(case_dir, CONFIG_CFD_NAME), overwrite=True) + + cfg["ROTATION_RATE"] = f"0.0 {rotation_rate} 0.0" + case_dir = Path(wkdir, f"{case_dir_name}_dq") + case_dir.mkdir() + cfg.write_file(Path(case_dir, CONFIG_CFD_NAME), overwrite=True) + + cfg["ROTATION_RATE"] = f"0.0 0.0 {rotation_rate}" + case_dir = Path(wkdir, f"{case_dir_name}_dr") + case_dir.mkdir() + cfg.write_file(Path(case_dir, CONFIG_CFD_NAME), overwrite=True) + + log.info("Damping derivatives cases directories has been created.") + + +def add_actuator_disk(cfg, cpacs, case_dir_path, actuator_disk_file, mesh_markers, alt, mach): + """Add actuator disk parameter to the config file. + + Args: + cfg (ConfigFile): ConfigFile object. + cpacs (CPACS): CPACS object from cpacspy library + case_dir_path (Path): Path object to the current case directory + actuator_disk_file (Path): Path to the actuator disk file + mesh_markers (dict): Dictionary containing all the mesh markers + + Returns: + cfg (ConfigFile): ConfigFile object. + """ + + ad_inlet_marker = sorted(mesh_markers["actuator_disk_inlet"]) + ad_outlet_marker = sorted(mesh_markers["actuator_disk_outlet"]) + + if "None" in ad_inlet_marker or "None" in ad_outlet_marker: + return + + if len(ad_inlet_marker) != len(ad_outlet_marker): + raise ValueError( + "The number of inlet and outlet markers of the actuator disk must be the same." + ) + + # Get rotorcraft configuration (propeller) + try: + rotorcraft_config = cpacs.rotorcraft.configuration + except AttributeError: + raise ValueError( + "The actuator disk is defined but no rotorcraft configuration is defined in " + "the CPACS file." + ) + + rotor_uid_pos = {} + for i in range(1, rotorcraft_config.get_rotor_count() + 1): + rotor = rotorcraft_config.get_rotor(i) + + rotor_uid = rotor.get_uid() + pos_x = rotor.get_translation().x + pos_y = rotor.get_translation().y + pos_z = rotor.get_translation().z + radius = rotor.get_radius() + hub_radius = 0.0 # TODO: get correctly from CPACS + + rotor_xpath = cpacs.tixi.uIDGetXPath(rotor_uid) + + number_of_blades_xpath = ( + rotor_xpath + "/rotorHub/rotorBladeAttachments/rotorBladeAttachment/numberOfBlades" + ) + number_of_blades = get_value_or_default(cpacs.tixi, number_of_blades_xpath, 3) + + # TODO: this is the nominal speed, how to get a speed which correspond to each flight cond. + rotational_velocity_xpath = rotor_xpath + "/nominalRotationsPerMinute" + rotational_velocity = ( + get_value_or_default(cpacs.tixi, rotational_velocity_xpath, 3000) / 60.0 + ) + + rotor_uid_pos[rotor_uid] = ( + pos_x, + pos_y, + pos_z, + radius, + hub_radius, + number_of_blades, + rotational_velocity, + ) + + cfg["ACTDISK_DOUBLE_SURFACE"] = "YES" + cfg["ACTDISK_TYPE"] = "VARIABLE_LOAD" + cfg["ACTDISK_FILENAME"] = ACTUATOR_DISK_FILE_NAME + cfg["MGLEVEL"] = 0 # Calculation diverges if multigrid is used with a disk actuator + + actdisk_markers = [] + + f = open(actuator_disk_file, "w") + f = write_header(f) + + for maker_inlet, marker_outlet in zip(ad_inlet_marker, ad_outlet_marker): + inlet_uid = maker_inlet.split(ACTUATOR_DISK_INLET_SUFFIX)[0] + outlet_uid = marker_outlet.split(ACTUATOR_DISK_OUTLET_SUFFIX)[0] + + if inlet_uid != outlet_uid: + raise ValueError("The inlet and outlet markers of the actuator disk must be the same.") + + if "_mirrored" in maker_inlet: + uid = inlet_uid.split("_mirrored")[0] + sym = -1 + else: + uid = inlet_uid + sym = 1 + + center = [] + center.append(round(rotor_uid_pos[uid][0], 5)) + center.append(round(sym * rotor_uid_pos[uid][1], 5)) + center.append(round(rotor_uid_pos[uid][2], 5)) + + axis = (1.0, 0.0, 0.0) # TODO: get the axis by applying the rotation matrix + radius = round(rotor_uid_pos[uid][3], 5) + hub_radius = round(rotor_uid_pos[uid][4], 5) + number_of_blades = round(rotor_uid_pos[uid][5], 5) + rotational_velocity = round(rotor_uid_pos[uid][6], 5) + + actdisk_markers.append(maker_inlet) + actdisk_markers.append(marker_outlet) + actdisk_markers.append(str(center[0])) + actdisk_markers.append(str(center[1])) + actdisk_markers.append(str(center[2])) + actdisk_markers.append(str(center[0])) + actdisk_markers.append(str(center[1])) + actdisk_markers.append(str(center[2])) + + Atm = Atmosphere(alt) + free_stream_velocity = mach * Atm.speed_of_sound[0] + + radial_stations = get_radial_stations(radius, hub_radius) + advanced_ratio = get_advanced_ratio(free_stream_velocity, rotational_velocity, radius) + + prandtl_correction_xpath = PROP_XPATH + "/propeller/blade/loss" + prandtl_correction = get_value_or_default(cpacs.tixi, prandtl_correction_xpath, True) + + thrust_xpath = PROP_XPATH + "/propeller/thrust" + thrust = get_value_or_default(cpacs.tixi, thrust_xpath, 3000) + total_thrust_coefficient = float( + thrust / (Atm.density * rotational_velocity**2 * (radius * 2) ** 4) + ) + + ( + radial_thrust_coefs, + radial_power_coefs, + non_dimensional_radius, + optimal_axial_interference_factor, + optimal_rotational_interference_factor, + prandtl_correction_values, + ) = thrust_calculator( + radial_stations, + total_thrust_coefficient, + radius, + free_stream_velocity, + prandtl_correction, + number_of_blades, + rotational_velocity, + ) + + save_plots( + radial_stations, + radial_thrust_coefs, + radial_power_coefs, + non_dimensional_radius, + optimal_axial_interference_factor, + optimal_rotational_interference_factor, + prandtl_correction_values, + case_dir_path, + inlet_uid, + ) + + f = write_actuator_disk_data( + file=f, + inlet_marker=maker_inlet, + outlet_marker=marker_outlet, + center=center, + axis=axis, + radius=radius, + advanced_ratio=advanced_ratio, + radial_stations=radial_stations, + radial_thrust_coefs=radial_thrust_coefs, + radial_power_coefs=radial_power_coefs, + ) + + cfg["MARKER_ACTDISK"] = " (" + ", ".join(actdisk_markers) + " )" + + f.close() + + +def generate_su2_cfd_config(cpacs_path, cpacs_out_path, wkdir): + """Function to create SU2 config file. + + Function 'generate_su2_cfd_config' reads data in the CPACS file and generate configuration + files for one or multiple flight conditions (alt,mach,aoa,aos) + + Source: + * SU2 config template: https://github.com/su2code/SU2/blob/master/config_template.cfg + + Args: + cpacs_path (Path): Path to CPACS file + cpacs_out_path (Path):Path to CPACS output file + wkdir (Path): Path to the working directory + + """ + + cpacs = CPACS(cpacs_path) + + su2_mesh = Path(get_value(cpacs.tixi, SU2MESH_XPATH)) + if not su2_mesh.is_file(): + raise FileNotFoundError(f"SU2 mesh file {su2_mesh} not found") + + mesh_markers = get_mesh_markers(su2_mesh) + + create_branch(cpacs.tixi, SU2_BC_WALL_XPATH) + bc_wall_str = ";".join(mesh_markers["wall"]) + cpacs.tixi.updateTextElement(SU2_BC_WALL_XPATH, bc_wall_str) + + create_branch(cpacs.tixi, SU2_BC_FARFIELD_XPATH) + bc_farfiled_str = ";".join(mesh_markers["engine_intake"] + mesh_markers["engine_exhaust"]) + cpacs.tixi.updateTextElement(SU2_BC_FARFIELD_XPATH, bc_farfiled_str) + + create_branch(cpacs.tixi, SU2_ACTUATOR_DISK_XPATH) + bc_actuator_disk_str = ";".join( + mesh_markers["actuator_disk_inlet"] + mesh_markers["actuator_disk_outlet"] + ) + cpacs.tixi.updateTextElement(SU2_ACTUATOR_DISK_XPATH, bc_actuator_disk_str) + + fixed_cl = get_value_or_default(cpacs.tixi, SU2_FIXED_CL_XPATH, "NO") + target_cl = get_value_or_default(cpacs.tixi, SU2_TARGET_CL_XPATH, 1.0) + + if fixed_cl == "NO": + # Get the first aeroMap as default one or create automatically one + aeromap_list = cpacs.get_aeromap_uid_list() + + if aeromap_list: + aeromap_default = aeromap_list[0] + log.info(f"The aeromap is {aeromap_default}") + + aeromap_uid = get_value_or_default(cpacs.tixi, SU2_AEROMAP_UID_XPATH, aeromap_default) + + activate_aeromap = cpacs.get_aeromap_by_uid(aeromap_uid) + alt_list = activate_aeromap.get("altitude").tolist() + mach_list = activate_aeromap.get("machNumber").tolist() + aoa_list = activate_aeromap.get("angleOfAttack").tolist() + aos_list = activate_aeromap.get("angleOfSideslip").tolist() + + else: + default_aeromap = cpacs.create_aeromap("DefaultAeromap") + default_aeromap.description = "AeroMap created automatically" + + mach = get_value_or_default(cpacs.tixi, RANGE_XPATH + "/cruiseMach", 0.3) + alt = get_value_or_default(cpacs.tixi, RANGE_XPATH + "/cruiseAltitude", 10000) + + default_aeromap.add_row(alt=alt, mach=mach, aos=0.0, aoa=0.0) + default_aeromap.save() + + alt_list = [alt] + mach_list = [mach] + aoa_list = [0.0] + aos_list = [0.0] + + aeromap_uid = get_value_or_default(cpacs.tixi, SU2_AEROMAP_UID_XPATH, "DefaultAeromap") + log.info(f"{aeromap_uid} has been created") + + else: # if fixed_cl == 'YES': + log.info("Configuration file for fixed CL calculation will be created.") + + fixed_cl_aeromap = cpacs.create_aeromap("aeroMap_fixedCL_SU2") + fixed_cl_aeromap.description = f"AeroMap created for SU2 fixed CL value of {target_cl}" + + mach = get_value_or_default(cpacs.tixi, RANGE_XPATH + "/cruiseMach", 0.78) + alt = get_value_or_default(cpacs.tixi, RANGE_XPATH + "/cruiseAltitude", 12000) + + fixed_cl_aeromap.add_row(alt=alt, mach=mach, aos=0.0, aoa=0.0) + fixed_cl_aeromap.save() + + alt_list = [alt] + mach_list = [mach] + aoa_list = [0.0] + aos_list = [0.0] + + cfg = ConfigFile(get_su2_config_template()) + + # Check if symmetry plane is defined (Default: False) + sym_factor = 1.0 + if get_value_or_default(cpacs.tixi, GMSH_SYMMETRY_XPATH, False): + log.info("Symmetry plane is defined. The reference area will be divided by 2.") + sym_factor = 2.0 + + # General parameters + cfg["RESTART_SOL"] = "NO" + cfg["REF_LENGTH"] = cpacs.aircraft.ref_length + cfg["REF_AREA"] = cpacs.aircraft.ref_area / sym_factor + cfg["REF_ORIGIN_MOMENT_X"] = cpacs.aircraft.ref_point_x + cfg["REF_ORIGIN_MOMENT_Y"] = cpacs.aircraft.ref_point_y + cfg["REF_ORIGIN_MOMENT_Z"] = cpacs.aircraft.ref_point_z + + # Settings + + cfl_down = get_value_or_default(cpacs.tixi, SU2_CFL_ADAPT_PARAM_DOWN_XPATH, 0.5) + cfl_up = get_value_or_default(cpacs.tixi, SU2_CFL_ADAPT_PARAM_UP_XPATH, 1.5) + cfl_min = get_value_or_default(cpacs.tixi, SU2_CFL_MIN_XPATH, 0.5) + cfl_max = get_value_or_default(cpacs.tixi, SU2_CFL_MAX_XPATH, 100) + + if get_value_or_default(cpacs.tixi, SU2_CFL_ADAPT_XPATH, True): + cfg["CFL_ADAPT"] = "YES" + + else: + cfg["CFL_ADAPT"] = "NO" + + cfg["INNER_ITER"] = int(get_value_or_default(cpacs.tixi, SU2_MAX_ITER_XPATH, 200)) + cfg["CFL_NUMBER"] = get_value_or_default(cpacs.tixi, SU2_CFL_NB_XPATH, 1.0) + cfg["CFL_ADAPT_PARAM"] = f"( {cfl_down}, {cfl_up}, {cfl_min}, {cfl_max} )" + cfg["MGLEVEL"] = int(get_value_or_default(cpacs.tixi, SU2_MG_LEVEL_XPATH, 3)) + + # Fixed CL mode (AOA will not be taken into account) + cfg["FIXED_CL_MODE"] = fixed_cl + cfg["TARGET_CL"] = target_cl + cfg["DCL_DALPHA"] = "0.1" + cfg["UPDATE_AOA_ITER_LIMIT"] = "50" + cfg["ITER_DCL_DALPHA"] = "80" + + # Mesh Marker + bc_wall_str = f"( {','.join(mesh_markers['wall'])} )" + + # ThermoData config file adding for engine BC + + if cpacs.tixi.checkElement(ENGINE_TYPE_XPATH): + log.info("adding engine BC to the SU2 config file") + engine_type = get_value(cpacs.tixi, ENGINE_TYPE_XPATH) + log.info(f"engine type {engine_type}") + alt = alt_list[0] + Atm = Atmosphere(alt) + tot_temp_in = Atm.temperature[0] + tot_pressure_in = Atm.pressure[0] + print(tot_pressure_in) + + if engine_type == 0: + log.info("turbojet boundary conditions") + tot_temp_out = get_value(cpacs.tixi, ENGINE_BC + "/temperatureOutlet") + tot_pressure_out = get_value(cpacs.tixi, ENGINE_BC + "/pressureOutlet") + cfg["INLET_TYPE"] = "TOTAL_CONDITIONS" + cfg[ + "MARKER_INLET" + ] = f"(INLET_ENGINE,{tot_temp_in}, {tot_pressure_in}, {1},{0},{0},OUTLET_ENGINE, {tot_temp_out}, {tot_pressure_out}, {1},{0},{0} )" + + elif engine_type == 1: + log.info("turbofan boundary conditions") + tot_temp_out = get_value(cpacs.tixi, ENGINE_BC + "/temperatureOutlet") + tot_pressure_out = get_value(cpacs.tixi, ENGINE_BC + "/pressureOutlet") + cfg["INLET_TYPE"] = "TOTAL_CONDITIONS" + cfg[ + "MARKER_INLET" + ] = f"(INLET_ENGINE, {tot_temp_in}, {tot_pressure_in}, {1},{0},{0}, OUTLET_ENGINE,{tot_temp_out}, {tot_pressure_out}, {1},{0},{0} )" + + cfg["MARKER_EULER"] = bc_wall_str + farfield_bc = ( + mesh_markers["farfield"] + mesh_markers["engine_intake"] + mesh_markers["engine_exhaust"] + ) + cfg["MARKER_FAR"] = f"( {','.join(farfield_bc)} )" + cfg["MARKER_SYM"] = f"( {','.join(mesh_markers['symmetry'])} )" + cfg["MARKER_PLOTTING"] = bc_wall_str + cfg["MARKER_MONITORING"] = bc_wall_str + cfg["MARKER_MOVING"] = "( NONE )" # TODO: when do we need to define MARKER_MOVING? + cfg["DV_MARKER"] = bc_wall_str + + # Output + cfg["WRT_FORCES_BREAKDOWN"] = "YES" + cfg["BREAKDOWN_FILENAME"] = SU2_FORCES_BREAKDOWN_NAME + cfg["OUTPUT_FILES"] = "(RESTART, PARAVIEW, SURFACE_PARAVIEW)" + cfg["HISTORY_OUTPUT"] = "(INNER_ITER, RMS_RES, AERO_COEFF)" + + # Parameters which will vary for the different cases (alt,mach,aoa,aos) + for case_nb in range(len(alt_list)): + cfg["MESH_FILENAME"] = str(su2_mesh) + + alt = alt_list[case_nb] + mach = mach_list[case_nb] + aoa = aoa_list[case_nb] + aos = aos_list[case_nb] + + Atm = Atmosphere(alt) + + cfg["MACH_NUMBER"] = mach + cfg["AOA"] = aoa + cfg["SIDESLIP_ANGLE"] = aos + cfg["FREESTREAM_PRESSURE"] = Atm.pressure[0] + cfg["FREESTREAM_TEMPERATURE"] = Atm.temperature[0] + cfg["ROTATION_RATE"] = "0.0 0.0 0.0" + + case_dir_name = ( + f"Case{str(case_nb).zfill(2)}_alt{alt}_mach{round(mach, 2)}" + f"_aoa{round(aoa, 1)}_aos{round(aos, 1)}" + ) + + case_dir_path = Path(wkdir, case_dir_name) + if not case_dir_path.exists(): + case_dir_path.mkdir() + + if get_value_or_default(cpacs.tixi, SU2_ACTUATOR_DISK_XPATH, False): + actuator_disk_file = Path(wkdir, ACTUATOR_DISK_FILE_NAME) + add_actuator_disk( + cfg, cpacs, case_dir_path, actuator_disk_file, mesh_markers, alt, mach + ) + + if actuator_disk_file.exists(): + case_actuator_disk_file = Path(case_dir_path, ACTUATOR_DISK_FILE_NAME) + copyfile(actuator_disk_file, case_actuator_disk_file) + + bc_wall_str = ( + "(" + + ",".join( + mesh_markers["wall"] + + mesh_markers["actuator_disk_inlet"] + + mesh_markers["actuator_disk_outlet"] + ) + + ")" + ) + + cfg["MARKER_PLOTTING"] = bc_wall_str + cfg["MARKER_MONITORING"] = bc_wall_str + + config_output_path = Path(case_dir_path, CONFIG_CFD_NAME) + cfg.write_file(config_output_path, overwrite=True) + + if get_value_or_default(cpacs.tixi, SU2_DAMPING_DER_XPATH, False): + rotation_rate = get_value_or_default(cpacs.tixi, SU2_ROTATION_RATE_XPATH, 1.0) + add_damping_derivatives(cfg, wkdir, case_dir_name, rotation_rate) + + # Control surfaces deflections (TODO: create a subfunctions) + if get_value_or_default(cpacs.tixi, SU2_CONTROL_SURF_XPATH, False): + # Get deformed mesh list + if cpacs.tixi.checkElement(SU2_DEF_MESH_XPATH): + su2_def_mesh_list = get_string_vector(cpacs.tixi, SU2_DEF_MESH_XPATH) + else: + log.warning("No SU2 deformed mesh has been found!") + su2_def_mesh_list = [] + + for su2_def_mesh in su2_def_mesh_list: + mesh_path = Path(wkdir, "MESH", su2_def_mesh) + config_dir_path = Path(wkdir, case_dir_name + "_" + su2_def_mesh.split(".")[0]) + config_dir_path.mkdir() + cfg["MESH_FILENAME"] = mesh_path + + cfg.write_file(Path(config_dir_path, CONFIG_CFD_NAME), overwrite=True) + + cpacs.save_cpacs(cpacs_out_path, overwrite=True) + + +# ================================================================================================= +# MAIN +# ================================================================================================= + +if __name__ == "__main__": + log.info("Nothing to execute!") diff --git a/ceasiompy/SU2Run/su2run.py b/ceasiompy/SU2Run/su2run.py index 132a0a17f..4b103b22c 100644 --- a/ceasiompy/SU2Run/su2run.py +++ b/ceasiompy/SU2Run/su2run.py @@ -16,7 +16,7 @@ * complete input/output in __specs__ * Check platform with-> sys.platform * Move run_SU2_fsi to /SU2Run/func/su2fsi.py -test + """ # ================================================================================================= diff --git a/ceasiompy/utils/commonnames.py b/ceasiompy/utils/commonnames.py index 2fcdabd97..0de79f1c1 100644 --- a/ceasiompy/utils/commonnames.py +++ b/ceasiompy/utils/commonnames.py @@ -43,3 +43,6 @@ # WEIGHT & BALANCE MTOM_FIGURE_NAME = "MTOM_Prediction.png" + +# PYCYCLE +ENGINE_BOUNDARY_CONDITIONS = "EngineBC.dat" diff --git a/ceasiompy/utils/commonxpath.py b/ceasiompy/utils/commonxpath.py index 0b9e28a57..19e0b646f 100644 --- a/ceasiompy/utils/commonxpath.py +++ b/ceasiompy/utils/commonxpath.py @@ -180,3 +180,7 @@ CHECK_LONGITUDINAL_STABILITY_XPATH = STABILITY_XPATH + "/stabilityToCheck/longitudinal" CHECK_DIRECTIONAL_STABILITY_XPATH = STABILITY_XPATH + "/stabilityToCheck/directional" CHECK_LATERAL_STABILITY_XPATH = STABILITY_XPATH + "/stabilityToCheck/lateral" + +# PYCYCLE +ENGINE_TYPE_XPATH = CEASIOMPY_XPATH + "/ThermoData" +ENGINE_BC = CEASIOMPY_XPATH + "/BC" From b97865babf6cfa87bc52ca8da86809fa78a952b3 Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Wed, 7 Feb 2024 10:16:39 +0100 Subject: [PATCH 04/55] new commit --- ceasiompy/ThermoData | 1 + 1 file changed, 1 insertion(+) create mode 160000 ceasiompy/ThermoData diff --git a/ceasiompy/ThermoData b/ceasiompy/ThermoData new file mode 160000 index 000000000..d806eea42 --- /dev/null +++ b/ceasiompy/ThermoData @@ -0,0 +1 @@ +Subproject commit d806eea4242e779fbd66a6a7e8a674e6d0c9b4ff From a968071d0fa72e46742012417c7315d73557b739 Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Wed, 7 Feb 2024 10:31:42 +0100 Subject: [PATCH 05/55] new commit --- ceasiompy/ThermoData | 1 - 1 file changed, 1 deletion(-) delete mode 160000 ceasiompy/ThermoData diff --git a/ceasiompy/ThermoData b/ceasiompy/ThermoData deleted file mode 160000 index d806eea42..000000000 --- a/ceasiompy/ThermoData +++ /dev/null @@ -1 +0,0 @@ -Subproject commit d806eea4242e779fbd66a6a7e8a674e6d0c9b4ff From c0decca227de2f6516d2b63f203c8ef93494f057 Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Wed, 7 Feb 2024 10:32:48 +0100 Subject: [PATCH 06/55] new commit --- ceasiompy/ThermoData/README.md | 1 + ceasiompy/ThermoData/__specs__.py | 69 +++ ceasiompy/ThermoData/func/run_func.py | 162 +++++++ ceasiompy/ThermoData/func/turbofan_func.py | 436 ++++++++++++++++++ ceasiompy/ThermoData/func/turbojet_func.py | 228 +++++++++ .../testing_pycycle/des_hbtf_func_test.py | 390 ++++++++++++++++ .../testing_pycycle/des_turbojet_func.py | 173 +++++++ ceasiompy/ThermoData/thermodata.py | 89 ++++ 8 files changed, 1548 insertions(+) create mode 100644 ceasiompy/ThermoData/README.md create mode 100644 ceasiompy/ThermoData/__specs__.py create mode 100644 ceasiompy/ThermoData/func/run_func.py create mode 100644 ceasiompy/ThermoData/func/turbofan_func.py create mode 100644 ceasiompy/ThermoData/func/turbojet_func.py create mode 100644 ceasiompy/ThermoData/testing_pycycle/des_hbtf_func_test.py create mode 100644 ceasiompy/ThermoData/testing_pycycle/des_turbojet_func.py create mode 100644 ceasiompy/ThermoData/thermodata.py diff --git a/ceasiompy/ThermoData/README.md b/ceasiompy/ThermoData/README.md new file mode 100644 index 000000000..77e55d5ff --- /dev/null +++ b/ceasiompy/ThermoData/README.md @@ -0,0 +1 @@ +# Thermo_Data \ No newline at end of file diff --git a/ceasiompy/ThermoData/__specs__.py b/ceasiompy/ThermoData/__specs__.py new file mode 100644 index 000000000..86c68fb89 --- /dev/null +++ b/ceasiompy/ThermoData/__specs__.py @@ -0,0 +1,69 @@ +from pathlib import Path +from ceasiompy.utils.moduleinterfaces import CPACSInOut +from ceasiompy.utils.commonxpath import ( + REF_XPATH, + CLCALC_XPATH, + SU2_FIXED_CL_XPATH, + SU2_TARGET_CL_XPATH, + ENGINE_TYPE_XPATH, + RANGE_XPATH, +) + +# ===== Module Status ===== +# True if the module is active +# False if the module is disabled (not working or not ready) +module_status = True + +# ===== Results directory path ===== + +RESULTS_DIR = Path("Results", "Thermodata") + +# ===== CPACS inputs and outputs ===== + +cpacs_inout = CPACSInOut() + +# ===== Input ===== + + +cpacs_inout.add_input( + var_name="net_force", + var_type=float, + default_value=2000, + unit="1", # AGGIUNGERE UNITA DI MISURA + descr="Engine net force", + xpath=RANGE_XPATH + "/NetForce", + gui=True, + gui_name="NetForce", + gui_group="Cruise", +) + +cpacs_inout.add_input( + var_name="engine type", + var_type=list, + default_value=[0, 1], + unit=None, + descr="0: TBJ, 1: TBF ", + xpath=ENGINE_TYPE_XPATH, + gui=True, + gui_name="0 for Turbojet 1 for Turbofan", + gui_group="User inputs", +) + + +# ===== Output ===== + +cpacs_inout.add_output( + var_name="target_cl", + default_value=None, + unit="1", + descr="Value of CL to achieve to have a level flight with the given conditions", + xpath=SU2_TARGET_CL_XPATH, +) + +cpacs_inout.add_output( + var_name="fixed_cl", + default_value=None, + unit="-", + descr="FIXED_CL_MODE parameter for SU2", + xpath=SU2_FIXED_CL_XPATH, +) diff --git a/ceasiompy/ThermoData/func/run_func.py b/ceasiompy/ThermoData/func/run_func.py new file mode 100644 index 000000000..eb0a6b58a --- /dev/null +++ b/ceasiompy/ThermoData/func/run_func.py @@ -0,0 +1,162 @@ +""" +CEASIOMpy: Conceptual Aircraft Design Software + +Developed by CFS ENGINEERING, 1015 Lausanne, Switzerland + +Function to run the PyCycle code in order to obtain turbojet and turbofan boundary conditions +at given altitude, mach number and net force = thrust of the engine + +Python version: >=3.8 + +| Author: Giacomo Benedetti and Francesco Marcucci +| Creation: 2023-12-12 + +""" + +from pathlib import Path + +from ceasiompy.ThermoData.func.turbofan_func import ( + turbofan_analysis, + write_hbtf_file, +) + +from ceasiompy.ThermoData.func.turbojet_func import ( + turbojet_analysis, + write_turbojet_file, +) + +from ceasiompy.utils.ceasiomlogger import get_logger + +from ceasiompy.utils.commonxpath import ( + ENGINE_TYPE_XPATH, + ENGINE_BC, + RANGE_XPATH, + SU2_AEROMAP_UID_XPATH, +) +from ceasiompy.utils.commonnames import ( + ENGINE_BOUNDARY_CONDITIONS, +) +from cpacspy.cpacsfunctions import ( + get_value_or_default, + add_float_vector, +) +from cpacspy.cpacsfunctions import create_branch, get_value_or_default +from cpacspy.cpacspy import CPACS + +log = get_logger() + +MODULE_DIR = Path(__file__).parent +MODULE_NAME = MODULE_DIR.name + + +def thermo_data_run(cpacs_path, cpacs_out_path, wkdir): + """Running the PyCycle code by choosing between turbojet or turbofan engine + + Args + cpacs_path (Path): Path to CPACS file + cpacs_out_path (Path):Path to CPACS output file + wkdir (str): Path to the working directory + """ + + if not wkdir.exists(): + raise OSError(f"The working directory : {wkdir} does not exit!") + + cpacs = CPACS(cpacs_path) + tixi = cpacs.tixi + + Fn = get_value_or_default(tixi, RANGE_XPATH + "/NetForce", 2000) + + aeromap_list = cpacs.get_aeromap_uid_list() + + if aeromap_list: + aeromap_default = aeromap_list[0] + log.info(f"The aeromap is {aeromap_default}") + aeromap_uid = get_value_or_default( + cpacs.tixi, SU2_AEROMAP_UID_XPATH, aeromap_default + ) + activate_aeromap = cpacs.get_aeromap_by_uid(aeromap_uid) + alt_list = activate_aeromap.get("altitude").tolist() + mach_list = activate_aeromap.get("machNumber").tolist() + T_tot_out_array = [] + P_tot_out_array = [] + + for case_nb in range(len(alt_list)): + alt = alt_list[case_nb] + MN = mach_list[case_nb] + case_dir_name = f"Case{str(case_nb).zfill(2)}_alt{alt}_mach{round(MN, 2)}" + case_dir_path = Path(wkdir, case_dir_name) + + if not case_dir_path.exists(): + case_dir_path.mkdir() + + EngineBC = Path(case_dir_path, ENGINE_BOUNDARY_CONDITIONS) + + f = open(EngineBC, "w") + + engine_type = get_value_or_default(tixi, ENGINE_TYPE_XPATH, 0) + create_branch(cpacs.tixi, ENGINE_BC) + + if engine_type == 0: + ( + T_tot_out, + V_stat_out, + MN_out, + P_tot_out, + massflow_stat_out, + T_stat_out, + P_stat_out, + ) = turbojet_analysis(alt, MN, Fn) + + T_tot_out_array.append(T_tot_out) + P_tot_out_array.append(P_tot_out) + + f = write_turbojet_file( + file=f, + T_tot_out=T_tot_out, + V_stat_out=V_stat_out, + MN_out=MN_out, + P_tot_out=P_tot_out, + massflow_stat_out=massflow_stat_out, + T_stat_out=T_stat_out, + P_stat_out=P_stat_out, + ) + + else: + + ( + T_tot_out_byp, + V_stat_out_byp, + MN_out_byp, + P_tot_out_byp, + massflow_stat_out_byp, + T_stat_out_byp, + T_tot_out_core, + V_stat_out_core, + MN_out_core, + P_tot_out_core, + massflow_stat_out_core, + T_stat_out_core, + ) = turbofan_analysis(alt, MN, Fn) + + T_tot_out_array.append(T_tot_out_core) + P_tot_out_array.append(P_tot_out_core) + + f = write_hbtf_file( + file=f, + T_tot_out_byp=T_tot_out_byp, + V_stat_out_byp=V_stat_out_byp, + MN_out_byp=MN_out_byp, + P_tot_out_byp=P_tot_out_byp, + massflow_stat_out_byp=massflow_stat_out_byp, + T_stat_out_byp=T_stat_out_byp, + T_tot_out_core=T_tot_out_core, + V_stat_out_core=V_stat_out_core, + MN_out_core=MN_out_core, + P_tot_out_core=P_tot_out_core, + massflow_stat_out_core=massflow_stat_out_core, + T_stat_out_core=T_stat_out_core, + ) + add_float_vector(tixi, ENGINE_BC + "/temperatureOutlet", T_tot_out_array) + add_float_vector(tixi, ENGINE_BC + "/pressureOutlet", P_tot_out_array) + + cpacs.save_cpacs(cpacs_out_path, overwrite=True) diff --git a/ceasiompy/ThermoData/func/turbofan_func.py b/ceasiompy/ThermoData/func/turbofan_func.py new file mode 100644 index 000000000..52521c47f --- /dev/null +++ b/ceasiompy/ThermoData/func/turbofan_func.py @@ -0,0 +1,436 @@ +""" +CEASIOMpy: Conceptual Aircraft Design Software + +Developed by CFS ENGINEERING, 1015 Lausanne, Switzerland + +Function to run the PyCycle code for the turbofan engine + +Python version: >=3.8 + +| Author: Giacomo Benedetti and Francesco Marcucci +| Creation: 2023-12-12 + +""" +import sys + +import openmdao.api as om + +import pycycle.api as pyc + +from scipy.constants import convert_temperature + +from ceasiompy.utils.ceasiomlogger import get_logger + +log = get_logger() + +# ================================================================================================= +# FUNCTIONS +# ================================================================================================= + + +def turbofan_analysis(alt, MN, Fn): + class HBTF(pyc.Cycle): + def setup(self): + + # Setup the problem by including all the relevant components here - comp, burner, turbine etc + + # Create any relevant short hands here: + + design = self.options["design"] + + USE_TABULAR = False + if USE_TABULAR: + self.options["thermo_method"] = "TABULAR" + self.options["thermo_data"] = pyc.AIR_JETA_TAB_SPEC + FUEL_TYPE = "FAR" + else: + self.options["thermo_method"] = "CEA" + self.options["thermo_data"] = pyc.species_data.janaf + FUEL_TYPE = "Jet-A(g)" + + # Add subsystems to build the engine deck: + self.add_subsystem("fc", pyc.FlightConditions()) + self.add_subsystem("inlet", pyc.Inlet()) + + self.add_subsystem( + "fan", + pyc.Compressor(map_data=pyc.FanMap, bleed_names=[], map_extrap=True), + promotes_inputs=[("Nmech", "LP_Nmech")], + ) + self.add_subsystem("splitter", pyc.Splitter()) + self.add_subsystem("duct4", pyc.Duct()) + self.add_subsystem( + "lpc", + pyc.Compressor(map_data=pyc.LPCMap, map_extrap=True), + promotes_inputs=[("Nmech", "LP_Nmech")], + ) + self.add_subsystem("duct6", pyc.Duct()) + self.add_subsystem( + "hpc", + pyc.Compressor( + map_data=pyc.HPCMap, + bleed_names=["cool1", "cool2", "cust"], + map_extrap=True, + ), + promotes_inputs=[("Nmech", "HP_Nmech")], + ) + self.add_subsystem("bld3", pyc.BleedOut(bleed_names=["cool3", "cool4"])) + self.add_subsystem("burner", pyc.Combustor(fuel_type=FUEL_TYPE)) + self.add_subsystem( + "hpt", + pyc.Turbine( + map_data=pyc.HPTMap, bleed_names=["cool3", "cool4"], map_extrap=True + ), + promotes_inputs=[("Nmech", "HP_Nmech")], + ) + self.add_subsystem("duct11", pyc.Duct()) + self.add_subsystem( + "lpt", + pyc.Turbine( + map_data=pyc.LPTMap, bleed_names=["cool1", "cool2"], map_extrap=True + ), + promotes_inputs=[("Nmech", "LP_Nmech")], + ) + self.add_subsystem("duct13", pyc.Duct()) + self.add_subsystem("core_nozz", pyc.Nozzle(nozzType="CV", lossCoef="Cv")) + + self.add_subsystem("byp_bld", pyc.BleedOut(bleed_names=["bypBld"])) + self.add_subsystem("duct15", pyc.Duct()) + self.add_subsystem("byp_nozz", pyc.Nozzle(nozzType="CV", lossCoef="Cv")) + + # Create shaft instances. Note that LP shaft has 3 ports! => no gearbox + self.add_subsystem( + "lp_shaft", + pyc.Shaft(num_ports=3), + promotes_inputs=[("Nmech", "LP_Nmech")], + ) + self.add_subsystem( + "hp_shaft", + pyc.Shaft(num_ports=2), + promotes_inputs=[("Nmech", "HP_Nmech")], + ) + self.add_subsystem("perf", pyc.Performance(num_nozzles=2, num_burners=1)) + + # Now use the explicit connect method to make connections -- connect(, ) + + # Connect the inputs to perf group + self.connect("inlet.Fl_O:tot:P", "perf.Pt2") + self.connect("hpc.Fl_O:tot:P", "perf.Pt3") + self.connect("burner.Wfuel", "perf.Wfuel_0") + self.connect("inlet.F_ram", "perf.ram_drag") + self.connect("core_nozz.Fg", "perf.Fg_0") + self.connect("byp_nozz.Fg", "perf.Fg_1") + + # LP-shaft connections + self.connect("fan.trq", "lp_shaft.trq_0") + self.connect("lpc.trq", "lp_shaft.trq_1") + self.connect("lpt.trq", "lp_shaft.trq_2") + # HP-shaft connections + self.connect("hpc.trq", "hp_shaft.trq_0") + self.connect("hpt.trq", "hp_shaft.trq_1") + # Ideally expanding flow by conneting flight condition static pressure to nozzle exhaust pressure + self.connect("fc.Fl_O:stat:P", "core_nozz.Ps_exhaust") + self.connect("fc.Fl_O:stat:P", "byp_nozz.Ps_exhaust") + + balance = self.add_subsystem("balance", om.BalanceComp()) + if design: + balance.add_balance("W", units="lbm/s", eq_units="lbf") + # Here balance.W is implicit state variable that is the OUTPUT of balance object + self.connect( + "balance.W", "fc.W" + ) # Connect the output of balance to the relevant input + self.connect( + "perf.Fn", "balance.lhs:W" + ) # This statement makes perf.Fn the LHS of the balance eqn. + self.promotes("balance", inputs=[("rhs:W", "Fn_DES")]) + + balance.add_balance("FAR", eq_units="degR", lower=1e-4, val=0.017) + self.connect("balance.FAR", "burner.Fl_I:FAR") + self.connect("burner.Fl_O:tot:T", "balance.lhs:FAR") + self.promotes("balance", inputs=[("rhs:FAR", "T4_MAX")]) + + # Note that for the following two balances the mult val is set to -1 so that the NET torque is zero + balance.add_balance( + "lpt_PR", + val=1.5, + lower=1.001, + upper=8, + eq_units="hp", + use_mult=True, + mult_val=-1, + ) + self.connect("balance.lpt_PR", "lpt.PR") + self.connect("lp_shaft.pwr_in_real", "balance.lhs:lpt_PR") + self.connect("lp_shaft.pwr_out_real", "balance.rhs:lpt_PR") + + balance.add_balance( + "hpt_PR", + val=1.5, + lower=1.001, + upper=8, + eq_units="hp", + use_mult=True, + mult_val=-1, + ) + self.connect("balance.hpt_PR", "hpt.PR") + self.connect("hp_shaft.pwr_in_real", "balance.lhs:hpt_PR") + self.connect("hp_shaft.pwr_out_real", "balance.rhs:hpt_PR") + + # Set up all the flow connections: + self.pyc_connect_flow("fc.Fl_O", "inlet.Fl_I") + self.pyc_connect_flow("inlet.Fl_O", "fan.Fl_I") + self.pyc_connect_flow("fan.Fl_O", "splitter.Fl_I") + self.pyc_connect_flow("splitter.Fl_O1", "duct4.Fl_I") + self.pyc_connect_flow("duct4.Fl_O", "lpc.Fl_I") + self.pyc_connect_flow("lpc.Fl_O", "duct6.Fl_I") + self.pyc_connect_flow("duct6.Fl_O", "hpc.Fl_I") + self.pyc_connect_flow("hpc.Fl_O", "bld3.Fl_I") + self.pyc_connect_flow("bld3.Fl_O", "burner.Fl_I") + self.pyc_connect_flow("burner.Fl_O", "hpt.Fl_I") + self.pyc_connect_flow("hpt.Fl_O", "duct11.Fl_I") + self.pyc_connect_flow("duct11.Fl_O", "lpt.Fl_I") + self.pyc_connect_flow("lpt.Fl_O", "duct13.Fl_I") + self.pyc_connect_flow("duct13.Fl_O", "core_nozz.Fl_I") + self.pyc_connect_flow("splitter.Fl_O2", "byp_bld.Fl_I") + self.pyc_connect_flow("byp_bld.Fl_O", "duct15.Fl_I") + self.pyc_connect_flow("duct15.Fl_O", "byp_nozz.Fl_I") + + # Bleed flows: + self.pyc_connect_flow("hpc.cool1", "lpt.cool1", connect_stat=False) + self.pyc_connect_flow("hpc.cool2", "lpt.cool2", connect_stat=False) + self.pyc_connect_flow("bld3.cool3", "hpt.cool3", connect_stat=False) + self.pyc_connect_flow("bld3.cool4", "hpt.cool4", connect_stat=False) + + # Specify solver settings: + newton = self.nonlinear_solver = om.NewtonSolver() + newton.options["atol"] = 1e-8 + + # set this very small, so it never activates and we rely on atol + newton.options["rtol"] = 1e-99 + newton.options["iprint"] = 2 + newton.options["maxiter"] = 50 + newton.options["solve_subsystems"] = True + newton.options["max_sub_solves"] = 1000 + newton.options["reraise_child_analysiserror"] = False + # ls = newton.linesearch = BoundsEnforceLS() + ls = newton.linesearch = om.ArmijoGoldsteinLS() + ls.options["maxiter"] = 3 + ls.options["rho"] = 0.75 + # ls.options['print_bound_enforce'] = True + + self.linear_solver = om.DirectSolver() + + super().setup() + + class MPhbtf(pyc.MPCycle): + def setup(self): + + self.pyc_add_pnt( + "DESIGN", HBTF(thermo_method="CEA") + ) # Create an instance of the High Bypass ratio Turbofan + + super().setup() + + def viewer(prob, pt, file=sys.stdout): + """ + print a report of all the relevant cycle properties + """ + + if pt == "DESIGN": + MN = prob["DESIGN.fc.Fl_O:stat:MN"] + LPT_PR = prob["DESIGN.balance.lpt_PR"] + HPT_PR = prob["DESIGN.balance.hpt_PR"] + FAR = prob["DESIGN.balance.FAR"] + else: + MN = prob[pt + ".fc.Fl_O:stat:MN"] + LPT_PR = prob[pt + ".lpt.PR"] + HPT_PR = prob[pt + ".hpt.PR"] + FAR = prob[pt + ".balance.FAR"] + + summary_data = ( + MN, + prob[pt + ".fc.alt"], + prob[pt + ".inlet.Fl_O:stat:W"], + prob[pt + ".perf.Fn"], + prob[pt + ".perf.Fg"], + prob[pt + ".inlet.F_ram"], + prob[pt + ".perf.OPR"], + prob[pt + ".perf.TSFC"], + prob[pt + ".splitter.BPR"], + ) + + print(file=file, flush=True) + print(file=file, flush=True) + print(file=file, flush=True) + print( + "----------------------------------------------------------------------------", + file=file, + flush=True, + ) + print(" POINT:", pt, file=file, flush=True) + print( + "----------------------------------------------------------------------------", + file=file, + flush=True, + ) + print( + " PERFORMANCE CHARACTERISTICS", file=file, flush=True + ) + print( + " Mach Alt W Fn Fg Fram OPR TSFC BPR ", + file=file, + flush=True, + ) + print( + " %7.5f %7.1f %7.3f %7.1f %7.1f %7.1f %7.3f %7.5f %7.3f" % summary_data, + file=file, + flush=True, + ) + + fs_names = [ + "fc.Fl_O", + "core_nozz.Fl_O", + "byp_nozz.Fl_O", + ] + fs_full_names = [f"{pt}.{fs}" for fs in fs_names] + pyc.print_flow_station(prob, fs_full_names, file=file) + + import time + + prob = om.Problem() + + prob.model = mp_hbtf = MPhbtf() + + prob.setup() + + prob.set_val("DESIGN.fan.PR", 1.685) + prob.set_val("DESIGN.fan.eff", 0.8948) + + prob.set_val("DESIGN.lpc.PR", 1.935) + prob.set_val("DESIGN.lpc.eff", 0.9243) + + prob.set_val("DESIGN.hpc.PR", 9.369) + prob.set_val("DESIGN.hpc.eff", 0.8707) + + prob.set_val("DESIGN.hpt.eff", 0.8888) + prob.set_val("DESIGN.lpt.eff", 0.8996) + + prob.set_val("DESIGN.fc.alt", alt, units="ft") + prob.set_val("DESIGN.fc.MN", MN) + + prob.set_val("DESIGN.T4_MAX", 2857, units="degR") + prob.set_val("DESIGN.Fn_DES", Fn, units="lbf") + + # Set initial guesses for balances + prob["DESIGN.balance.FAR"] = 0.1 + prob["DESIGN.balance.W"] = 10.0 + prob["DESIGN.balance.lpt_PR"] = 2 + prob["DESIGN.balance.hpt_PR"] = 2.0 + prob["DESIGN.fc.balance.Pt"] = 2 + prob["DESIGN.fc.balance.Tt"] = 500.0 + + prob.set_solver_print(level=-1) + prob.set_solver_print(level=2, depth=1) + + flight_env = [(0.9, 6000)] + + viewer_file = open("hbtf_des_view.out", "w") + + for PC in [1, 0.9]: + viewer(prob, "DESIGN", file=viewer_file) + prob.run_model() + + print() + + # Obtaining variables names + + # variable_names = open("variables_hptf.txt", "w") + # print( + # prob.model.list_outputs(val=True, units=True, implicit=False), + # file=variable_names, + # ) + + # BYPASS VARIABLES + T_tot_out_byp = convert_temperature( + (prob.get_val("DESIGN.byp_nozz.throat_total.flow.Fl_O:tot:T")), + "Rankine", + "Celsius", + ) + V_stat_out_byp = prob.get_val("DESIGN.byp_nozz.mux.Fl_O:stat:V") * 0.3048 + MN_out_byp = prob.get_val("DESIGN.byp_nozz.mux.Fl_O:stat:MN") + P_tot_out_byp = ( + prob.get_val("DESIGN.byp_nozz.throat_total.flow.Fl_O:tot:P") * 6894.7573 + ) # Pa + massflow_stat_out_byp = ( + prob.get_val("DESIGN.byp_nozz.mux.Fl_O:stat:W") * 0.45359237 + ) # kg/s + T_stat_out_byp = convert_temperature( + (prob.get_val("DESIGN.byp_nozz.mux.Fl_O:stat:T")), "Rankine", "Celsius" + ) # celsius + + # CORE VARIABLES + T_tot_out_core = convert_temperature( + (prob.get_val("DESIGN.core_nozz.throat_total.flow.Fl_O:tot:T")), + "Rankine", + "Kelvin", + ) + V_stat_out_core = prob.get_val("DESIGN.core_nozz.mux.Fl_O:stat:V") * 0.3048 + MN_out_core = prob.get_val("DESIGN.core_nozz.mux.Fl_O:stat:MN") + P_tot_out_core = ( + prob.get_val("DESIGN.core_nozz.throat_total.flow.Fl_O:tot:P") * 6894.7573 + ) # Pa + massflow_stat_out_core = ( + prob.get_val("DESIGN.core_nozz.mux.Fl_O:stat:W") * 0.45359237 + ) # kg/s + T_stat_out_core = convert_temperature( + (prob.get_val("DESIGN.core_nozz.mux.Fl_O:stat:T")), "Rankine", "Kelvin" + ) # celsius + + return ( + T_tot_out_byp, + V_stat_out_byp, + MN_out_byp, + P_tot_out_byp, + massflow_stat_out_byp, + T_stat_out_byp, + T_tot_out_core, + V_stat_out_core, + MN_out_core, + P_tot_out_core, + massflow_stat_out_core, + T_stat_out_core, + ) + + +def write_hbtf_file( + file, + T_tot_out_byp, + V_stat_out_byp, + MN_out_byp, + P_tot_out_byp, + massflow_stat_out_byp, + T_stat_out_byp, + T_tot_out_core, + V_stat_out_core, + MN_out_core, + P_tot_out_core, + massflow_stat_out_core, + T_stat_out_core, +): + + file.write(f"T_tot_out_core = {T_tot_out_core} [K]\n") + file.write(f"V_stat_out_core = {V_stat_out_core} [m/s]\n") + file.write(f"MN_out_core = {MN_out_core} [adim]\n") + file.write(f"P_tot_out_core = {P_tot_out_core} [Pa]\n") + file.write(f"massflow_out_core = {massflow_stat_out_core} [kg/s]\n") + file.write(f"T_stat_out_core = {T_stat_out_core} [K]\n") + file.write(f"T_tot_out_byp = {T_tot_out_byp} [K]\n") + file.write(f"V_stat_out_byp = {V_stat_out_byp} [m/s]\n") + file.write(f"MN_out_byp = {MN_out_byp} [adim]\n") + file.write(f"P_tot_out_byp = {P_tot_out_byp} [Pa]\n") + file.write(f"massflow_stat_out_byp = {massflow_stat_out_byp} [kg/s]\n") + file.write(f"T_stat_out_byp = {T_stat_out_byp} [K]\n") + + log.info("hbtf.dat file generated!") + + return file diff --git a/ceasiompy/ThermoData/func/turbojet_func.py b/ceasiompy/ThermoData/func/turbojet_func.py new file mode 100644 index 000000000..371195bad --- /dev/null +++ b/ceasiompy/ThermoData/func/turbojet_func.py @@ -0,0 +1,228 @@ +""" +CEASIOMpy: Conceptual Aircraft Design Software + +Developed by CFS ENGINEERING, 1015 Lausanne, Switzerland + +Function to run the PyCycle code for the turbojet engine + +Python version: >=3.8 + +| Author: Giacomo Benedetti and Francesco Marcucci +| Creation: 2023-12-12 + +""" + +import openmdao.api as om + +import pycycle.api as pyc + +from scipy.constants import convert_temperature + +from ceasiompy.utils.ceasiomlogger import get_logger + +log = get_logger() + +# ================================================================================================= +# FUNCTIONS +# ================================================================================================= + + +def turbojet_analysis(alt, MN, Fn): + class Turbojet(pyc.Cycle): + def setup(self): + + USE_TABULAR = True + + if USE_TABULAR: + self.options["thermo_method"] = "TABULAR" + self.options["thermo_data"] = pyc.AIR_JETA_TAB_SPEC + FUEL_TYPE = "FAR" + + design = self.options["design"] + + # Add engine elements + self.add_subsystem("fc", pyc.FlightConditions()) + self.add_subsystem("inlet", pyc.Inlet()) + self.add_subsystem( + "comp", + pyc.Compressor(map_data=pyc.AXI5, map_extrap=True), + promotes_inputs=["Nmech"], + ) + self.add_subsystem("burner", pyc.Combustor(fuel_type=FUEL_TYPE)) + self.add_subsystem( + "turb", pyc.Turbine(map_data=pyc.LPT2269), promotes_inputs=["Nmech"] + ) + self.add_subsystem("nozz", pyc.Nozzle(nozzType="CD", lossCoef="Cv")) + self.add_subsystem( + "shaft", pyc.Shaft(num_ports=2), promotes_inputs=["Nmech"] + ) + self.add_subsystem("perf", pyc.Performance(num_nozzles=1, num_burners=1)) + + # Connect flow stations + self.pyc_connect_flow("fc.Fl_O", "inlet.Fl_I", connect_w=False) + self.pyc_connect_flow("inlet.Fl_O", "comp.Fl_I") + self.pyc_connect_flow("comp.Fl_O", "burner.Fl_I") + self.pyc_connect_flow("burner.Fl_O", "turb.Fl_I") + self.pyc_connect_flow("turb.Fl_O", "nozz.Fl_I") + + # Make other non-flow connections + # Connect turbomachinery elements to shaft + self.connect("comp.trq", "shaft.trq_0") + self.connect("turb.trq", "shaft.trq_1") + + # Connnect nozzle exhaust to freestream static conditions + self.connect("fc.Fl_O:stat:P", "nozz.Ps_exhaust") + + # Connect outputs to perfomance element + self.connect("inlet.Fl_O:tot:P", "perf.Pt2") + self.connect("comp.Fl_O:tot:P", "perf.Pt3") + self.connect("burner.Wfuel", "perf.Wfuel_0") + self.connect("inlet.F_ram", "perf.ram_drag") + self.connect("nozz.Fg", "perf.Fg_0") + + # Add balances for design and off-design + balance = self.add_subsystem("balance", om.BalanceComp()) + if design: + + balance.add_balance( + "W", units="lbm/s", eq_units="lbf", rhs_name="Fn_target" + ) + self.connect("balance.W", "inlet.Fl_I:stat:W") + self.connect("perf.Fn", "balance.lhs:W") + + balance.add_balance( + "FAR", eq_units="degR", lower=1e-4, val=0.017, rhs_name="T4_target" + ) + self.connect("balance.FAR", "burner.Fl_I:FAR") + self.connect("burner.Fl_O:tot:T", "balance.lhs:FAR") + + balance.add_balance( + "turb_PR", val=1.5, lower=1.001, upper=8, eq_units="hp", rhs_val=0.0 + ) + self.connect("balance.turb_PR", "turb.PR") + self.connect("shaft.pwr_net", "balance.lhs:turb_PR") + + newton = self.nonlinear_solver = om.NewtonSolver() + newton.options["atol"] = 1e-6 + newton.options["rtol"] = 1e-6 + newton.options["iprint"] = 2 + newton.options["maxiter"] = 15 + newton.options["solve_subsystems"] = True + newton.options["max_sub_solves"] = 100 + newton.options["reraise_child_analysiserror"] = False + + self.linear_solver = om.DirectSolver() + + super().setup() + + class MPTurbojet(pyc.MPCycle): + def setup(self): + self.pyc_add_pnt("DESIGN", Turbojet()) + + self.set_input_defaults("DESIGN.Nmech", 8070.0, units="rpm") + self.set_input_defaults("DESIGN.inlet.MN", 0.60) + self.set_input_defaults("DESIGN.comp.MN", 0.020) # .2 + self.set_input_defaults("DESIGN.burner.MN", 0.020) # .2 + self.set_input_defaults("DESIGN.turb.MN", 0.4) + + self.pyc_add_cycle_param("burner.dPqP", 0.03) + self.pyc_add_cycle_param("nozz.Cv", 0.99) + + super().setup() + + import time + + # defining the optimization problem + + prob = om.Problem() + + mp_turbojet = prob.model = MPTurbojet() + prob.setup(check=False) + + # define input values + prob.set_val("DESIGN.fc.alt", alt, units="ft") + prob.set_val("DESIGN.fc.MN", MN) + prob.set_val("DESIGN.balance.Fn_target", Fn, units="lbf") + prob.set_val("DESIGN.balance.T4_target", 2370.0, units="degR") + prob.set_val("DESIGN.comp.PR", 13.5) + prob.set_val("DESIGN.comp.eff", 0.83) + prob.set_val("DESIGN.turb.eff", 0.86) + + if Fn > 2700: + prob["DESIGN.balance.FAR"] = 0.0175506829934 + prob["DESIGN.balance.W"] = 75.453135137 + prob["DESIGN.balance.turb_PR"] = 4.46138725662 + prob["DESIGN.fc.balance.Pt"] = 14.6955113159 + prob["DESIGN.fc.balance.Tt"] = 518.665288153 + + elif 2700 <= Fn < 850: + prob["DESIGN.balance.FAR"] = 0.0175506829934 + prob["DESIGN.balance.W"] = 50.453135137 + prob["DESIGN.balance.turb_PR"] = 4.46138725662 + prob["DESIGN.fc.balance.Pt"] = 14.6955113159 + prob["DESIGN.fc.balance.Tt"] = 518.665288153 + + else: + prob["DESIGN.balance.FAR"] = 0.0175506829934 + prob["DESIGN.balance.W"] = 10.453135137 + prob["DESIGN.balance.turb_PR"] = 4.46138725662 + prob["DESIGN.fc.balance.Pt"] = 14.6955113159 + prob["DESIGN.fc.balance.Tt"] = 518.665288153 + + prob.set_solver_print(level=-1) + # prob.set_solver_print(level=2, depth=1) + + prob.run_model() + + print() + + # command to visualize all the output of the system + # a = prob.model.list_outputs(val=True, units=True) + + T_tot_out = convert_temperature( + (prob.get_val("DESIGN.nozz.throat_total.flow.Fl_O:tot:T")), "Rankine", "Kelvin" + ) + V_stat_out = (prob.get_val("DESIGN.nozz.mux.Fl_O:stat:V")) * 0.3048 + MN_out = prob.get_val("DESIGN.nozz.mux.Fl_O:stat:MN") + T_stat_out = convert_temperature( + prob.get_val("DESIGN.nozz.mux.Fl_O:stat:T"), "Rankine", "Kelvin" + ) # celsius + massflow_stat_out = prob.get_val("DESIGN.nozz.mux.Fl_O:stat:W") * 0.45359237 # kg/s + P_tot_out = ( + prob.get_val("DESIGN.nozz.throat_total.flow.Fl_O:tot:P") * 6894.7573 + ) # Pa + P_stat_out = prob.get_val("DESIGN.nozz.mux.Fl_O:stat:P") * 6894.7573 # Pa + + return ( + T_tot_out, + V_stat_out, + MN_out, + P_tot_out, + massflow_stat_out, + T_stat_out, + P_stat_out, + ) + + +def write_turbojet_file( + file, + T_tot_out, + V_stat_out, + MN_out, + P_tot_out, + massflow_stat_out, + T_stat_out, + P_stat_out, +): + + file.write(f"T_tot_out = {T_tot_out} [K]\n") + file.write(f"V_stat_out = {V_stat_out} [m/s]\n") + file.write(f"MN_out = {MN_out} [adim]\n") + file.write(f"P_tot_out = {P_tot_out} [Pa]\n") + file.write(f"massflow_out = {massflow_stat_out} [kg/s]\n") + file.write(f"T_stat_out = {T_stat_out} [K]\n") + file.write(f"P_stat_out = {P_stat_out} [Pa]\n") + + log.info("turbojet.dat file generated!") + + return file diff --git a/ceasiompy/ThermoData/testing_pycycle/des_hbtf_func_test.py b/ceasiompy/ThermoData/testing_pycycle/des_hbtf_func_test.py new file mode 100644 index 000000000..dbc960816 --- /dev/null +++ b/ceasiompy/ThermoData/testing_pycycle/des_hbtf_func_test.py @@ -0,0 +1,390 @@ +import sys + +import numpy as np + +import openmdao.api as om + +import pycycle.api as pyc + +import re + +from scipy.constants import convert_temperature + + +def run_turbofan_analysis_test(alt, MN): + class HBTF(pyc.Cycle): + def setup(self): + + # Setup the problem by including all the relevant components here - comp, burner, turbine etc + + # Create any relevant short hands here: + + design = self.options["design"] + + USE_TABULAR = False + if USE_TABULAR: + self.options["thermo_method"] = "TABULAR" + self.options["thermo_data"] = pyc.AIR_JETA_TAB_SPEC + FUEL_TYPE = "FAR" + else: + self.options["thermo_method"] = "CEA" + self.options["thermo_data"] = pyc.species_data.janaf + FUEL_TYPE = "Jet-A(g)" + + # Add subsystems to build the engine deck: + self.add_subsystem("fc", pyc.FlightConditions()) + self.add_subsystem("inlet", pyc.Inlet()) + + self.add_subsystem( + "fan", + pyc.Compressor(map_data=pyc.FanMap, bleed_names=[], map_extrap=True), + promotes_inputs=[("Nmech", "LP_Nmech")], + ) + self.add_subsystem("splitter", pyc.Splitter()) + self.add_subsystem("duct4", pyc.Duct()) + self.add_subsystem( + "lpc", + pyc.Compressor(map_data=pyc.LPCMap, map_extrap=True), + promotes_inputs=[("Nmech", "LP_Nmech")], + ) + self.add_subsystem("duct6", pyc.Duct()) + self.add_subsystem( + "hpc", + pyc.Compressor( + map_data=pyc.HPCMap, + bleed_names=["cool1", "cool2", "cust"], + map_extrap=True, + ), + promotes_inputs=[("Nmech", "HP_Nmech")], + ) + self.add_subsystem("bld3", pyc.BleedOut(bleed_names=["cool3", "cool4"])) + self.add_subsystem("burner", pyc.Combustor(fuel_type=FUEL_TYPE)) + self.add_subsystem( + "hpt", + pyc.Turbine( + map_data=pyc.HPTMap, bleed_names=["cool3", "cool4"], map_extrap=True + ), + promotes_inputs=[("Nmech", "HP_Nmech")], + ) + self.add_subsystem("duct11", pyc.Duct()) + self.add_subsystem( + "lpt", + pyc.Turbine( + map_data=pyc.LPTMap, bleed_names=["cool1", "cool2"], map_extrap=True + ), + promotes_inputs=[("Nmech", "LP_Nmech")], + ) + self.add_subsystem("duct13", pyc.Duct()) + self.add_subsystem("core_nozz", pyc.Nozzle(nozzType="CV", lossCoef="Cv")) + + self.add_subsystem("byp_bld", pyc.BleedOut(bleed_names=["bypBld"])) + self.add_subsystem("duct15", pyc.Duct()) + self.add_subsystem("byp_nozz", pyc.Nozzle(nozzType="CV", lossCoef="Cv")) + + # Create shaft instances. Note that LP shaft has 3 ports! => no gearbox + self.add_subsystem( + "lp_shaft", + pyc.Shaft(num_ports=3), + promotes_inputs=[("Nmech", "LP_Nmech")], + ) + self.add_subsystem( + "hp_shaft", + pyc.Shaft(num_ports=2), + promotes_inputs=[("Nmech", "HP_Nmech")], + ) + self.add_subsystem("perf", pyc.Performance(num_nozzles=2, num_burners=1)) + + # Now use the explicit connect method to make connections -- connect(, ) + + # Connect the inputs to perf group + self.connect("inlet.Fl_O:tot:P", "perf.Pt2") + self.connect("hpc.Fl_O:tot:P", "perf.Pt3") + self.connect("burner.Wfuel", "perf.Wfuel_0") + self.connect("inlet.F_ram", "perf.ram_drag") + self.connect("core_nozz.Fg", "perf.Fg_0") + self.connect("byp_nozz.Fg", "perf.Fg_1") + + # LP-shaft connections + self.connect("fan.trq", "lp_shaft.trq_0") + self.connect("lpc.trq", "lp_shaft.trq_1") + self.connect("lpt.trq", "lp_shaft.trq_2") + # HP-shaft connections + self.connect("hpc.trq", "hp_shaft.trq_0") + self.connect("hpt.trq", "hp_shaft.trq_1") + # Ideally expanding flow by conneting flight condition static pressure to nozzle exhaust pressure + self.connect("fc.Fl_O:stat:P", "core_nozz.Ps_exhaust") + self.connect("fc.Fl_O:stat:P", "byp_nozz.Ps_exhaust") + + balance = self.add_subsystem("balance", om.BalanceComp()) + if design: + balance.add_balance("W", units="lbm/s", eq_units="lbf") + # Here balance.W is implicit state variable that is the OUTPUT of balance object + self.connect( + "balance.W", "fc.W" + ) # Connect the output of balance to the relevant input + self.connect( + "perf.Fn", "balance.lhs:W" + ) # This statement makes perf.Fn the LHS of the balance eqn. + self.promotes("balance", inputs=[("rhs:W", "Fn_DES")]) + + balance.add_balance("FAR", eq_units="degR", lower=1e-4, val=0.017) + self.connect("balance.FAR", "burner.Fl_I:FAR") + self.connect("burner.Fl_O:tot:T", "balance.lhs:FAR") + self.promotes("balance", inputs=[("rhs:FAR", "T4_MAX")]) + + # Note that for the following two balances the mult val is set to -1 so that the NET torque is zero + balance.add_balance( + "lpt_PR", + val=1.5, + lower=1.001, + upper=8, + eq_units="hp", + use_mult=True, + mult_val=-1, + ) + self.connect("balance.lpt_PR", "lpt.PR") + self.connect("lp_shaft.pwr_in_real", "balance.lhs:lpt_PR") + self.connect("lp_shaft.pwr_out_real", "balance.rhs:lpt_PR") + + balance.add_balance( + "hpt_PR", + val=1.5, + lower=1.001, + upper=8, + eq_units="hp", + use_mult=True, + mult_val=-1, + ) + self.connect("balance.hpt_PR", "hpt.PR") + self.connect("hp_shaft.pwr_in_real", "balance.lhs:hpt_PR") + self.connect("hp_shaft.pwr_out_real", "balance.rhs:hpt_PR") + + # Set up all the flow connections: + self.pyc_connect_flow("fc.Fl_O", "inlet.Fl_I") + self.pyc_connect_flow("inlet.Fl_O", "fan.Fl_I") + self.pyc_connect_flow("fan.Fl_O", "splitter.Fl_I") + self.pyc_connect_flow("splitter.Fl_O1", "duct4.Fl_I") + self.pyc_connect_flow("duct4.Fl_O", "lpc.Fl_I") + self.pyc_connect_flow("lpc.Fl_O", "duct6.Fl_I") + self.pyc_connect_flow("duct6.Fl_O", "hpc.Fl_I") + self.pyc_connect_flow("hpc.Fl_O", "bld3.Fl_I") + self.pyc_connect_flow("bld3.Fl_O", "burner.Fl_I") + self.pyc_connect_flow("burner.Fl_O", "hpt.Fl_I") + self.pyc_connect_flow("hpt.Fl_O", "duct11.Fl_I") + self.pyc_connect_flow("duct11.Fl_O", "lpt.Fl_I") + self.pyc_connect_flow("lpt.Fl_O", "duct13.Fl_I") + self.pyc_connect_flow("duct13.Fl_O", "core_nozz.Fl_I") + self.pyc_connect_flow("splitter.Fl_O2", "byp_bld.Fl_I") + self.pyc_connect_flow("byp_bld.Fl_O", "duct15.Fl_I") + self.pyc_connect_flow("duct15.Fl_O", "byp_nozz.Fl_I") + + # Bleed flows: + self.pyc_connect_flow("hpc.cool1", "lpt.cool1", connect_stat=False) + self.pyc_connect_flow("hpc.cool2", "lpt.cool2", connect_stat=False) + self.pyc_connect_flow("bld3.cool3", "hpt.cool3", connect_stat=False) + self.pyc_connect_flow("bld3.cool4", "hpt.cool4", connect_stat=False) + + # Specify solver settings: + newton = self.nonlinear_solver = om.NewtonSolver() + newton.options["atol"] = 1e-8 + + # set this very small, so it never activates and we rely on atol + newton.options["rtol"] = 1e-99 + newton.options["iprint"] = 2 + newton.options["maxiter"] = 50 + newton.options["solve_subsystems"] = True + newton.options["max_sub_solves"] = 1000 + newton.options["reraise_child_analysiserror"] = False + # ls = newton.linesearch = BoundsEnforceLS() + ls = newton.linesearch = om.ArmijoGoldsteinLS() + ls.options["maxiter"] = 3 + ls.options["rho"] = 0.75 + # ls.options['print_bound_enforce'] = True + + self.linear_solver = om.DirectSolver() + + super().setup() + + class MPhbtf(pyc.MPCycle): + def setup(self): + + self.pyc_add_pnt( + "DESIGN", HBTF(thermo_method="CEA") + ) # Create an instance of the High Bypass ratio Turbofan + + self.set_input_defaults("DESIGN.inlet.MN", 0.751) + self.set_input_defaults("DESIGN.fan.MN", 0.4578) + self.set_input_defaults("DESIGN.splitter.BPR", 5.105) + self.set_input_defaults("DESIGN.splitter.MN1", 0.3104) + self.set_input_defaults("DESIGN.splitter.MN2", 0.4518) + self.set_input_defaults("DESIGN.duct4.MN", 0.3121) + self.set_input_defaults("DESIGN.lpc.MN", 0.3059) + self.set_input_defaults("DESIGN.duct6.MN", 0.3563) + self.set_input_defaults("DESIGN.hpc.MN", 0.2442) + self.set_input_defaults("DESIGN.bld3.MN", 0.3000) + self.set_input_defaults("DESIGN.burner.MN", 0.1025) + self.set_input_defaults("DESIGN.hpt.MN", 0.3650) + self.set_input_defaults("DESIGN.duct11.MN", 0.3063) + self.set_input_defaults("DESIGN.lpt.MN", 0.4127) + self.set_input_defaults("DESIGN.duct13.MN", 0.4463) + self.set_input_defaults("DESIGN.byp_bld.MN", 0.4489) + self.set_input_defaults("DESIGN.duct15.MN", 0.4589) + self.set_input_defaults("DESIGN.LP_Nmech", 4666.1, units="rpm") + self.set_input_defaults("DESIGN.HP_Nmech", 14705.7, units="rpm") + + # --- Set up bleed values ----- + + self.pyc_add_cycle_param("inlet.ram_recovery", 0.9990) + self.pyc_add_cycle_param("duct4.dPqP", 0.0048) + self.pyc_add_cycle_param("duct6.dPqP", 0.0101) + self.pyc_add_cycle_param("burner.dPqP", 0.0540) + self.pyc_add_cycle_param("duct11.dPqP", 0.0051) + self.pyc_add_cycle_param("duct13.dPqP", 0.0107) + self.pyc_add_cycle_param("duct15.dPqP", 0.0149) + self.pyc_add_cycle_param("core_nozz.Cv", 0.9933) + self.pyc_add_cycle_param("byp_bld.bypBld:frac_W", 0.005) + self.pyc_add_cycle_param("byp_nozz.Cv", 0.9939) + self.pyc_add_cycle_param("hpc.cool1:frac_W", 0.050708) + self.pyc_add_cycle_param("hpc.cool1:frac_P", 0.5) + self.pyc_add_cycle_param("hpc.cool1:frac_work", 0.5) + self.pyc_add_cycle_param("hpc.cool2:frac_W", 0.020274) + self.pyc_add_cycle_param("hpc.cool2:frac_P", 0.55) + self.pyc_add_cycle_param("hpc.cool2:frac_work", 0.5) + self.pyc_add_cycle_param("bld3.cool3:frac_W", 0.067214) + self.pyc_add_cycle_param("bld3.cool4:frac_W", 0.101256) + self.pyc_add_cycle_param("hpc.cust:frac_P", 0.5) + self.pyc_add_cycle_param("hpc.cust:frac_work", 0.5) + self.pyc_add_cycle_param("hpc.cust:frac_W", 0.0445) + self.pyc_add_cycle_param("hpt.cool3:frac_P", 1.0) + self.pyc_add_cycle_param("hpt.cool4:frac_P", 0.0) + self.pyc_add_cycle_param("lpt.cool1:frac_P", 1.0) + self.pyc_add_cycle_param("lpt.cool2:frac_P", 0.0) + self.pyc_add_cycle_param("hp_shaft.HPX", 250.0, units="hp") + + super().setup() + + import time + + prob = om.Problem() + + prob.model = mp_hbtf = MPhbtf() + + prob.setup() + + prob.set_val("DESIGN.fan.PR", 1.685) + prob.set_val("DESIGN.fan.eff", 0.8948) + + prob.set_val("DESIGN.lpc.PR", 1.935) + prob.set_val("DESIGN.lpc.eff", 0.9243) + + prob.set_val("DESIGN.hpc.PR", 9.369) + prob.set_val("DESIGN.hpc.eff", 0.8707) + + prob.set_val("DESIGN.hpt.eff", 0.8888) + prob.set_val("DESIGN.lpt.eff", 0.8996) + + prob.set_val("DESIGN.fc.alt", alt, units="ft") + prob.set_val("DESIGN.fc.MN", MN) + + prob.set_val("DESIGN.T4_MAX", 2857, units="degR") + prob.set_val("DESIGN.Fn_DES", 5900.0, units="lbf") + + # Set initial guesses for balances + prob["DESIGN.balance.FAR"] = 0.025 + prob["DESIGN.balance.W"] = 100.0 + prob["DESIGN.balance.lpt_PR"] = 4.0 + prob["DESIGN.balance.hpt_PR"] = 3.0 + prob["DESIGN.fc.balance.Pt"] = 5.2 + prob["DESIGN.fc.balance.Tt"] = 440.0 + + prob.set_solver_print(level=-1) + # prob.set_solver_print(level=2, depth=1) + + prob.run_model() + + print() + + # Obtaining variables names + + # variable_names = open("variables_hptf.txt", "w") + # print( + # prob.model.list_outputs(val=True, units=True, implicit=False), + # file=variable_names, + # ) + + # BYPASS VARIABLES + T_tot_out_byp = convert_temperature( + (prob.get_val("DESIGN.byp_nozz.throat_total.flow.Fl_O:tot:T")), + "Rankine", + "Celsius", + ) + V_stat_out_byp = prob.get_val("DESIGN.byp_nozz.mux.Fl_O:stat:V") * 0.3048 + MN_out_byp = prob.get_val("DESIGN.byp_nozz.mux.Fl_O:stat:MN") + P_tot_out_byp = ( + prob.get_val("DESIGN.byp_nozz.throat_total.flow.Fl_O:tot:P") * 6894.7573 + ) # Pa + massflow_stat_out_byp = ( + prob.get_val("DESIGN.byp_nozz.mux.Fl_O:stat:W") * 0.45359237 + ) # kg/s + T_stat_out_byp = convert_temperature( + (prob.get_val("DESIGN.byp_nozz.mux.Fl_O:stat:T")), "Rankine", "Celsius" + ) # celsius + + # CORE VARIABLES + T_tot_out_core = convert_temperature( + (prob.get_val("DESIGN.core_nozz.throat_total.flow.Fl_O:tot:T")), + "Rankine", + "Kelvin", + ) + V_stat_out_core = prob.get_val("DESIGN.core_nozz.mux.Fl_O:stat:V") * 0.3048 + MN_out_core = prob.get_val("DESIGN.core_nozz.mux.Fl_O:stat:MN") + P_tot_out_core = ( + prob.get_val("DESIGN.core_nozz.throat_total.flow.Fl_O:tot:P") * 6894.7573 + ) # Pa + massflow_stat_out_core = ( + prob.get_val("DESIGN.core_nozz.mux.Fl_O:stat:W") * 0.45359237 + ) # kg/s + T_stat_out_core = convert_temperature( + (prob.get_val("DESIGN.core_nozz.mux.Fl_O:stat:T")), "Rankine", "Kelvin" + ) # celsius + + res = np.array( + [ + T_tot_out_byp, + V_stat_out_byp, + MN_out_byp, + P_tot_out_byp, + massflow_stat_out_byp, + T_stat_out_byp, + T_tot_out_core, + V_stat_out_core, + MN_out_core, + P_tot_out_core, + massflow_stat_out_core, + T_stat_out_core, + ] + ) + print(f"T_tot_out_core = {T_tot_out_core} [K]") + print(f"V_stat_out_core = {V_stat_out_core} [m/s]") + print(f"MN_out_core = {MN_out_core} [adim]") + print(f"P_tot_out_core = {P_tot_out_core} [Pa]") + print(f"massflow_out_core = {massflow_stat_out_core} [kg/s]") + print(f"T_stat_out_core = {T_stat_out_core} [K]") + print(f"T_tot_out_byp = {T_tot_out_byp} [K]") + print(f"V_stat_out_byp = {V_stat_out_byp} [m/s]") + print(f"MN_out_byp = {MN_out_byp} [adim]") + print(f"P_tot_out_byp = {P_tot_out_byp} [Pa]") + print(f"massflow_stat_out_byp = {massflow_stat_out_byp} [kg/s]") + print(f"T_stat_out_core = {T_stat_out_core} [K]") + + return res + + +if __name__ == "__main__": + + alt = float(input("insert altitude [ft]: ")) + + MN = float(input("insert mach number[adim]: ")) + + run_turbofan_analysis_test(alt, MN) + print("temperature [celsius], stat velocity [m/s], MN for bypass and core") diff --git a/ceasiompy/ThermoData/testing_pycycle/des_turbojet_func.py b/ceasiompy/ThermoData/testing_pycycle/des_turbojet_func.py new file mode 100644 index 000000000..d36447fef --- /dev/null +++ b/ceasiompy/ThermoData/testing_pycycle/des_turbojet_func.py @@ -0,0 +1,173 @@ +import sys + +import openmdao.api as om + +import pycycle.api as pyc + +import numpy as np + +import re + +from scipy.constants import convert_temperature + + +def run_turbojet_analysis(alt, MN, Fn): + class Turbojet(pyc.Cycle): + def setup(self): + + USE_TABULAR = True + + if USE_TABULAR: + self.options["thermo_method"] = "TABULAR" + self.options["thermo_data"] = pyc.AIR_JETA_TAB_SPEC + FUEL_TYPE = "FAR" + + design = self.options["design"] + + # Add engine elements + self.add_subsystem("fc", pyc.FlightConditions()) + self.add_subsystem("inlet", pyc.Inlet()) + self.add_subsystem( + "comp", + pyc.Compressor(map_data=pyc.AXI5, map_extrap=True), + promotes_inputs=["Nmech"], + ) + self.add_subsystem("burner", pyc.Combustor(fuel_type=FUEL_TYPE)) + self.add_subsystem( + "turb", pyc.Turbine(map_data=pyc.LPT2269), promotes_inputs=["Nmech"] + ) + self.add_subsystem("nozz", pyc.Nozzle(nozzType="CD", lossCoef="Cv")) + self.add_subsystem( + "shaft", pyc.Shaft(num_ports=2), promotes_inputs=["Nmech"] + ) + self.add_subsystem("perf", pyc.Performance(num_nozzles=1, num_burners=1)) + + # Connect flow stations + self.pyc_connect_flow("fc.Fl_O", "inlet.Fl_I", connect_w=False) + self.pyc_connect_flow("inlet.Fl_O", "comp.Fl_I") + self.pyc_connect_flow("comp.Fl_O", "burner.Fl_I") + self.pyc_connect_flow("burner.Fl_O", "turb.Fl_I") + self.pyc_connect_flow("turb.Fl_O", "nozz.Fl_I") + + # Make other non-flow connections + # Connect turbomachinery elements to shaft + self.connect("comp.trq", "shaft.trq_0") + self.connect("turb.trq", "shaft.trq_1") + + # Connnect nozzle exhaust to freestream static conditions + self.connect("fc.Fl_O:stat:P", "nozz.Ps_exhaust") + + # Connect outputs to perfomance element + self.connect("inlet.Fl_O:tot:P", "perf.Pt2") + self.connect("comp.Fl_O:tot:P", "perf.Pt3") + self.connect("burner.Wfuel", "perf.Wfuel_0") + self.connect("inlet.F_ram", "perf.ram_drag") + self.connect("nozz.Fg", "perf.Fg_0") + + # Add balances for design and off-design + balance = self.add_subsystem("balance", om.BalanceComp()) + if design: + + balance.add_balance( + "W", units="lbm/s", eq_units="lbf", rhs_name="Fn_target" + ) + self.connect("balance.W", "inlet.Fl_I:stat:W") + self.connect("perf.Fn", "balance.lhs:W") + + balance.add_balance( + "FAR", eq_units="degR", lower=1e-4, val=0.017, rhs_name="T4_target" + ) + self.connect("balance.FAR", "burner.Fl_I:FAR") + self.connect("burner.Fl_O:tot:T", "balance.lhs:FAR") + + balance.add_balance( + "turb_PR", val=1.5, lower=1.001, upper=8, eq_units="hp", rhs_val=0.0 + ) + self.connect("balance.turb_PR", "turb.PR") + self.connect("shaft.pwr_net", "balance.lhs:turb_PR") + + newton = self.nonlinear_solver = om.NewtonSolver() + newton.options["atol"] = 1e-6 + newton.options["rtol"] = 1e-6 + newton.options["iprint"] = 2 + newton.options["maxiter"] = 15 + newton.options["solve_subsystems"] = True + newton.options["max_sub_solves"] = 100 + newton.options["reraise_child_analysiserror"] = False + + self.linear_solver = om.DirectSolver() + + super().setup() + + class MPTurbojet(pyc.MPCycle): + def setup(self): + self.pyc_add_pnt("DESIGN", Turbojet()) + + self.set_input_defaults("DESIGN.Nmech", 8070.0, units="rpm") + self.set_input_defaults("DESIGN.inlet.MN", 0.60) + self.set_input_defaults("DESIGN.comp.MN", 0.020) # .2 + self.set_input_defaults("DESIGN.burner.MN", 0.020) # .2 + self.set_input_defaults("DESIGN.turb.MN", 0.4) + + self.pyc_add_cycle_param("burner.dPqP", 0.03) + self.pyc_add_cycle_param("nozz.Cv", 0.99) + + super().setup() + + import time + + # defining the optimization problem + + prob = om.Problem() + mp_turbojet = prob.model = MPTurbojet() + prob.setup(check=False) + + # define input values + prob.set_val("DESIGN.fc.alt", alt, units="ft") + prob.set_val("DESIGN.fc.MN", MN) + prob.set_val("DESIGN.balance.Fn_target", Fn, units="lbf") + prob.set_val("DESIGN.balance.T4_target", 2370.0, units="degR") + prob.set_val("DESIGN.comp.PR", 13.5) + prob.set_val("DESIGN.comp.eff", 0.83) + prob.set_val("DESIGN.turb.eff", 0.86) + + # define initial guesses for the balances + prob["DESIGN.balance.FAR"] = 0.0175506829934 + prob["DESIGN.balance.W"] = 168.453135137 + prob["DESIGN.balance.turb_PR"] = 4.46138725662 + prob["DESIGN.fc.balance.Pt"] = 14.6955113159 + prob["DESIGN.fc.balance.Tt"] = 518.665288153 + + prob.set_solver_print(level=-1) + # prob.set_solver_print(level=2, depth=1) + + prob.run_model() + + print() + + # command to visualize all the output of the system + # a = prob.model.list_outputs(val=True, units=True) + + T_tot_out = convert_temperature( + (prob.get_val("DESIGN.nozz.throat_total.flow.Fl_O:tot:T")), "Rankine", "Kelvin" + ) + V_stat_out = (prob.get_val("DESIGN.nozz.mux.Fl_O:stat:V")) * 0.3048 + MN_out = prob.get_val("DESIGN.nozz.mux.Fl_O:stat:MN") + T_stat_out = convert_temperature( + prob.get_val("DESIGN.nozz.mux.Fl_O:stat:T"), "Rankine", "Kelvin" + ) # celsius + massflow_stat_out = prob.get_val("DESIGN.nozz.mux.Fl_O:stat:W") * 0.45359237 # kg/s + P_tot_out = ( + prob.get_val("DESIGN.nozz.throat_total.flow.Fl_O:tot:P") * 6894.7573 + ) # Pa + + res = np.array( + [T_tot_out, V_stat_out, MN_out, P_tot_out, massflow_stat_out, T_stat_out] + ) + print(f"T_tot_out = {T_tot_out} [K]") + print(f"V_stat_out = {V_stat_out} [m/s]") + print(f"MN_out = {MN_out} [adim]") + print(f"P_tot_out = {P_tot_out} [Pa]") + print(f"massflow_out = {massflow_stat_out} [kg/s]") + print(f"T_stat_out = {T_stat_out} [K]") + return res diff --git a/ceasiompy/ThermoData/thermodata.py b/ceasiompy/ThermoData/thermodata.py new file mode 100644 index 000000000..b7b621fde --- /dev/null +++ b/ceasiompy/ThermoData/thermodata.py @@ -0,0 +1,89 @@ +""" +CEASIOMpy: Conceptual Aircraft Design Software + +Developed by CFS ENGINEERING, 1015 Lausanne, Switzerland + +Calculate outlet conditions fot turbojet and turbofan engines by using the open source code PyCycle +and saving those conditions in a text file + +| Author: Giacomo Benedetti and Francesco Marcucci +| Creation: 2023-12-12 +""" + +# ================================================================================================= +# IMPORTS +# ================================================================================================= + +import shutil +from pathlib import Path + +from ceasiompy.ThermoData.func.run_func import ( + thermo_data_run, +) + +from ceasiompy.utils.ceasiomlogger import get_logger + +from ceasiompy.utils.moduleinterfaces import ( + check_cpacs_input_requirements, + get_toolinput_file_path, + get_tooloutput_file_path, +) +from ceasiompy.utils.commonxpath import ( + REF_XPATH, + CLCALC_XPATH, + ENGINE_TYPE_XPATH, +) +from ceasiompy.utils.commonnames import ( + ENGINE_BOUNDARY_CONDITIONS, +) +from cpacspy.cpacsfunctions import ( + get_value_or_default, +) +from cpacspy.cpacsfunctions import create_branch, get_value, get_value_or_default +from cpacspy.cpacspy import CPACS +from markdownpy.markdownpy import MarkdownDoc +from ceasiompy.utils.ceasiompyutils import get_results_directory + + +log = get_logger() + +MODULE_DIR = Path(__file__).parent +MODULE_NAME = MODULE_DIR.name + + +# ================================================================================================= +# CLASSES +# ================================================================================================= + + +# ================================================================================================= +# FUNCTIONS +# ================================================================================================= + + +# ================================================================================================= +# MAIN +# ================================================================================================= + + +def main(cpacs_path, cpacs_out_path): + + log.info("----- Start of " + MODULE_NAME + " -----") + + results_dir = get_results_directory("ThermoData") + + thermo_data_run(cpacs_path, cpacs_out_path, results_dir) + + folder_name = "reports" + + shutil.rmtree(folder_name) + + log.info("----- End of " + MODULE_NAME + " -----") + + +if __name__ == "__main__": + + cpacs_path = get_toolinput_file_path(MODULE_NAME) + cpacs_out_path = get_tooloutput_file_path(MODULE_NAME) + + main(cpacs_path, cpacs_out_path) From 97271970667ad8018d59b2e2dc461ff155219d4d Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Wed, 7 Feb 2024 10:46:04 +0100 Subject: [PATCH 07/55] new commit --- "src/streamlit/pages/01_ \342\236\241_Workflow.py" | 1 + 1 file changed, 1 insertion(+) diff --git "a/src/streamlit/pages/01_ \342\236\241_Workflow.py" "b/src/streamlit/pages/01_ \342\236\241_Workflow.py" index 27ac8306e..ac987512f 100644 --- "a/src/streamlit/pages/01_ \342\236\241_Workflow.py" +++ "b/src/streamlit/pages/01_ \342\236\241_Workflow.py" @@ -66,6 +66,7 @@ def section_predefined_workflow(): predefine_workflows = [ ["PyTornado", "WeightConventional"], ["CPACS2GMSH", "SU2Run", "SkinFriction"], + ["CPACS2GMSH", "ThermoData", "SU2Run"], ["CPACS2SUMO", "SUMOAutoMesh", "SU2Run", "ExportCSV"], ] From 4162727beb063bd254e0675309800ad1230951fa Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Wed, 7 Feb 2024 11:58:35 +0100 Subject: [PATCH 08/55] fixing some problems for merging --- ceasiompy/SU2Run/func/su2config.py | 7 +- ceasiompy/SU2Run/func/su2configrans.py | 14 +- ceasiompy/ThermoData/func/run_func.py | 8 +- ceasiompy/ThermoData/func/turbofan_func.py | 32 +- .../testing_pycycle/des_hbtf_func_test.py | 390 ------------------ .../testing_pycycle/des_turbojet_func.py | 173 -------- 6 files changed, 26 insertions(+), 598 deletions(-) delete mode 100644 ceasiompy/ThermoData/testing_pycycle/des_hbtf_func_test.py delete mode 100644 ceasiompy/ThermoData/testing_pycycle/des_turbojet_func.py diff --git a/ceasiompy/SU2Run/func/su2config.py b/ceasiompy/SU2Run/func/su2config.py index 07ba8b606..e8e4ee232 100644 --- a/ceasiompy/SU2Run/func/su2config.py +++ b/ceasiompy/SU2Run/func/su2config.py @@ -315,9 +315,10 @@ def add_thermodata(cfg, cpacs, alt, case_nb, alt_list): tot_temp_out = tot_temp_out[case_nb] tot_pressure_out = tot_pressure_out[case_nb] cfg["INLET_TYPE"] = "TOTAL_CONDITIONS" - cfg[ - "MARKER_INLET" - ] = f"(INLET_ENGINE, {tot_temp_in}, {tot_pressure_in}, {1},{0},{0}, OUTLET_ENGINE,{tot_temp_out}, {tot_pressure_out}, {1},{0},{0} )" + cfg["MARKER_INLET"] = ( + f"(INLET_ENGINE, {tot_temp_in}, {tot_pressure_in}, {1},{0},{0}, " + f"OUTLET_ENGINE,{tot_temp_out},{tot_pressure_out}, {1},{0},{0})" + ) def generate_su2_cfd_config(cpacs_path, cpacs_out_path, wkdir): diff --git a/ceasiompy/SU2Run/func/su2configrans.py b/ceasiompy/SU2Run/func/su2configrans.py index 09e141fb3..a1feee3cd 100644 --- a/ceasiompy/SU2Run/func/su2configrans.py +++ b/ceasiompy/SU2Run/func/su2configrans.py @@ -449,18 +449,20 @@ def generate_su2_cfd_config(cpacs_path, cpacs_out_path, wkdir): tot_temp_out = get_value(cpacs.tixi, ENGINE_BC + "/temperatureOutlet") tot_pressure_out = get_value(cpacs.tixi, ENGINE_BC + "/pressureOutlet") cfg["INLET_TYPE"] = "TOTAL_CONDITIONS" - cfg[ - "MARKER_INLET" - ] = f"(INLET_ENGINE,{tot_temp_in}, {tot_pressure_in}, {1},{0},{0},OUTLET_ENGINE, {tot_temp_out}, {tot_pressure_out}, {1},{0},{0} )" + cfg["MARKER_INLET"] = ( + f"(INLET_ENGINE, {tot_temp_in}, {tot_pressure_in}, {1},{0},{0}, " + f"OUTLET_ENGINE,{tot_temp_out},{tot_pressure_out}, {1},{0},{0})" + ) elif engine_type == 1: log.info("turbofan boundary conditions") tot_temp_out = get_value(cpacs.tixi, ENGINE_BC + "/temperatureOutlet") tot_pressure_out = get_value(cpacs.tixi, ENGINE_BC + "/pressureOutlet") cfg["INLET_TYPE"] = "TOTAL_CONDITIONS" - cfg[ - "MARKER_INLET" - ] = f"(INLET_ENGINE, {tot_temp_in}, {tot_pressure_in}, {1},{0},{0}, OUTLET_ENGINE,{tot_temp_out}, {tot_pressure_out}, {1},{0},{0} )" + cfg["MARKER_INLET"] = ( + f"(INLET_ENGINE, {tot_temp_in}, {tot_pressure_in}, {1},{0},{0}, " + f"OUTLET_ENGINE,{tot_temp_out},{tot_pressure_out}, {1},{0},{0})" + ) cfg["MARKER_EULER"] = bc_wall_str farfield_bc = ( diff --git a/ceasiompy/ThermoData/func/run_func.py b/ceasiompy/ThermoData/func/run_func.py index eb0a6b58a..45bf617bf 100644 --- a/ceasiompy/ThermoData/func/run_func.py +++ b/ceasiompy/ThermoData/func/run_func.py @@ -4,7 +4,7 @@ Developed by CFS ENGINEERING, 1015 Lausanne, Switzerland Function to run the PyCycle code in order to obtain turbojet and turbofan boundary conditions -at given altitude, mach number and net force = thrust of the engine +at given altitude, mach number and net force = thrust of the engine Python version: >=3.8 @@ -39,8 +39,8 @@ from cpacspy.cpacsfunctions import ( get_value_or_default, add_float_vector, + create_branch, ) -from cpacspy.cpacsfunctions import create_branch, get_value_or_default from cpacspy.cpacspy import CPACS log = get_logger() @@ -71,9 +71,7 @@ def thermo_data_run(cpacs_path, cpacs_out_path, wkdir): if aeromap_list: aeromap_default = aeromap_list[0] log.info(f"The aeromap is {aeromap_default}") - aeromap_uid = get_value_or_default( - cpacs.tixi, SU2_AEROMAP_UID_XPATH, aeromap_default - ) + aeromap_uid = get_value_or_default(cpacs.tixi, SU2_AEROMAP_UID_XPATH, aeromap_default) activate_aeromap = cpacs.get_aeromap_by_uid(aeromap_uid) alt_list = activate_aeromap.get("altitude").tolist() mach_list = activate_aeromap.get("machNumber").tolist() diff --git a/ceasiompy/ThermoData/func/turbofan_func.py b/ceasiompy/ThermoData/func/turbofan_func.py index 52521c47f..1cb944b38 100644 --- a/ceasiompy/ThermoData/func/turbofan_func.py +++ b/ceasiompy/ThermoData/func/turbofan_func.py @@ -32,7 +32,7 @@ def turbofan_analysis(alt, MN, Fn): class HBTF(pyc.Cycle): def setup(self): - # Setup the problem by including all the relevant components here - comp, burner, turbine etc + # Setup the problem by including all the relevant components here # Create any relevant short hands here: @@ -78,17 +78,13 @@ def setup(self): self.add_subsystem("burner", pyc.Combustor(fuel_type=FUEL_TYPE)) self.add_subsystem( "hpt", - pyc.Turbine( - map_data=pyc.HPTMap, bleed_names=["cool3", "cool4"], map_extrap=True - ), + pyc.Turbine(map_data=pyc.HPTMap, bleed_names=["cool3", "cool4"], map_extrap=True), promotes_inputs=[("Nmech", "HP_Nmech")], ) self.add_subsystem("duct11", pyc.Duct()) self.add_subsystem( "lpt", - pyc.Turbine( - map_data=pyc.LPTMap, bleed_names=["cool1", "cool2"], map_extrap=True - ), + pyc.Turbine(map_data=pyc.LPTMap, bleed_names=["cool1", "cool2"], map_extrap=True), promotes_inputs=[("Nmech", "LP_Nmech")], ) self.add_subsystem("duct13", pyc.Duct()) @@ -128,7 +124,8 @@ def setup(self): # HP-shaft connections self.connect("hpc.trq", "hp_shaft.trq_0") self.connect("hpt.trq", "hp_shaft.trq_1") - # Ideally expanding flow by conneting flight condition static pressure to nozzle exhaust pressure + # Ideally expanding flow by conneting flight condition static + # pressure to nozzle exhaust pressure self.connect("fc.Fl_O:stat:P", "core_nozz.Ps_exhaust") self.connect("fc.Fl_O:stat:P", "byp_nozz.Ps_exhaust") @@ -149,7 +146,8 @@ def setup(self): self.connect("burner.Fl_O:tot:T", "balance.lhs:FAR") self.promotes("balance", inputs=[("rhs:FAR", "T4_MAX")]) - # Note that for the following two balances the mult val is set to -1 so that the NET torque is zero + # Note that for the following two balances + # the mult val is set to -1 so that the NET torque is zero balance.add_balance( "lpt_PR", val=1.5, @@ -273,9 +271,7 @@ def viewer(prob, pt, file=sys.stdout): file=file, flush=True, ) - print( - " PERFORMANCE CHARACTERISTICS", file=file, flush=True - ) + print(" PERFORMANCE CHARACTERISTICS", file=file, flush=True) print( " Mach Alt W Fn Fg Fram OPR TSFC BPR ", file=file, @@ -358,12 +354,8 @@ def viewer(prob, pt, file=sys.stdout): ) V_stat_out_byp = prob.get_val("DESIGN.byp_nozz.mux.Fl_O:stat:V") * 0.3048 MN_out_byp = prob.get_val("DESIGN.byp_nozz.mux.Fl_O:stat:MN") - P_tot_out_byp = ( - prob.get_val("DESIGN.byp_nozz.throat_total.flow.Fl_O:tot:P") * 6894.7573 - ) # Pa - massflow_stat_out_byp = ( - prob.get_val("DESIGN.byp_nozz.mux.Fl_O:stat:W") * 0.45359237 - ) # kg/s + P_tot_out_byp = prob.get_val("DESIGN.byp_nozz.throat_total.flow.Fl_O:tot:P") * 6894.7573 # Pa + massflow_stat_out_byp = prob.get_val("DESIGN.byp_nozz.mux.Fl_O:stat:W") * 0.45359237 # kg/s T_stat_out_byp = convert_temperature( (prob.get_val("DESIGN.byp_nozz.mux.Fl_O:stat:T")), "Rankine", "Celsius" ) # celsius @@ -379,9 +371,7 @@ def viewer(prob, pt, file=sys.stdout): P_tot_out_core = ( prob.get_val("DESIGN.core_nozz.throat_total.flow.Fl_O:tot:P") * 6894.7573 ) # Pa - massflow_stat_out_core = ( - prob.get_val("DESIGN.core_nozz.mux.Fl_O:stat:W") * 0.45359237 - ) # kg/s + massflow_stat_out_core = prob.get_val("DESIGN.core_nozz.mux.Fl_O:stat:W") * 0.45359237 # kg/s T_stat_out_core = convert_temperature( (prob.get_val("DESIGN.core_nozz.mux.Fl_O:stat:T")), "Rankine", "Kelvin" ) # celsius diff --git a/ceasiompy/ThermoData/testing_pycycle/des_hbtf_func_test.py b/ceasiompy/ThermoData/testing_pycycle/des_hbtf_func_test.py deleted file mode 100644 index dbc960816..000000000 --- a/ceasiompy/ThermoData/testing_pycycle/des_hbtf_func_test.py +++ /dev/null @@ -1,390 +0,0 @@ -import sys - -import numpy as np - -import openmdao.api as om - -import pycycle.api as pyc - -import re - -from scipy.constants import convert_temperature - - -def run_turbofan_analysis_test(alt, MN): - class HBTF(pyc.Cycle): - def setup(self): - - # Setup the problem by including all the relevant components here - comp, burner, turbine etc - - # Create any relevant short hands here: - - design = self.options["design"] - - USE_TABULAR = False - if USE_TABULAR: - self.options["thermo_method"] = "TABULAR" - self.options["thermo_data"] = pyc.AIR_JETA_TAB_SPEC - FUEL_TYPE = "FAR" - else: - self.options["thermo_method"] = "CEA" - self.options["thermo_data"] = pyc.species_data.janaf - FUEL_TYPE = "Jet-A(g)" - - # Add subsystems to build the engine deck: - self.add_subsystem("fc", pyc.FlightConditions()) - self.add_subsystem("inlet", pyc.Inlet()) - - self.add_subsystem( - "fan", - pyc.Compressor(map_data=pyc.FanMap, bleed_names=[], map_extrap=True), - promotes_inputs=[("Nmech", "LP_Nmech")], - ) - self.add_subsystem("splitter", pyc.Splitter()) - self.add_subsystem("duct4", pyc.Duct()) - self.add_subsystem( - "lpc", - pyc.Compressor(map_data=pyc.LPCMap, map_extrap=True), - promotes_inputs=[("Nmech", "LP_Nmech")], - ) - self.add_subsystem("duct6", pyc.Duct()) - self.add_subsystem( - "hpc", - pyc.Compressor( - map_data=pyc.HPCMap, - bleed_names=["cool1", "cool2", "cust"], - map_extrap=True, - ), - promotes_inputs=[("Nmech", "HP_Nmech")], - ) - self.add_subsystem("bld3", pyc.BleedOut(bleed_names=["cool3", "cool4"])) - self.add_subsystem("burner", pyc.Combustor(fuel_type=FUEL_TYPE)) - self.add_subsystem( - "hpt", - pyc.Turbine( - map_data=pyc.HPTMap, bleed_names=["cool3", "cool4"], map_extrap=True - ), - promotes_inputs=[("Nmech", "HP_Nmech")], - ) - self.add_subsystem("duct11", pyc.Duct()) - self.add_subsystem( - "lpt", - pyc.Turbine( - map_data=pyc.LPTMap, bleed_names=["cool1", "cool2"], map_extrap=True - ), - promotes_inputs=[("Nmech", "LP_Nmech")], - ) - self.add_subsystem("duct13", pyc.Duct()) - self.add_subsystem("core_nozz", pyc.Nozzle(nozzType="CV", lossCoef="Cv")) - - self.add_subsystem("byp_bld", pyc.BleedOut(bleed_names=["bypBld"])) - self.add_subsystem("duct15", pyc.Duct()) - self.add_subsystem("byp_nozz", pyc.Nozzle(nozzType="CV", lossCoef="Cv")) - - # Create shaft instances. Note that LP shaft has 3 ports! => no gearbox - self.add_subsystem( - "lp_shaft", - pyc.Shaft(num_ports=3), - promotes_inputs=[("Nmech", "LP_Nmech")], - ) - self.add_subsystem( - "hp_shaft", - pyc.Shaft(num_ports=2), - promotes_inputs=[("Nmech", "HP_Nmech")], - ) - self.add_subsystem("perf", pyc.Performance(num_nozzles=2, num_burners=1)) - - # Now use the explicit connect method to make connections -- connect(, ) - - # Connect the inputs to perf group - self.connect("inlet.Fl_O:tot:P", "perf.Pt2") - self.connect("hpc.Fl_O:tot:P", "perf.Pt3") - self.connect("burner.Wfuel", "perf.Wfuel_0") - self.connect("inlet.F_ram", "perf.ram_drag") - self.connect("core_nozz.Fg", "perf.Fg_0") - self.connect("byp_nozz.Fg", "perf.Fg_1") - - # LP-shaft connections - self.connect("fan.trq", "lp_shaft.trq_0") - self.connect("lpc.trq", "lp_shaft.trq_1") - self.connect("lpt.trq", "lp_shaft.trq_2") - # HP-shaft connections - self.connect("hpc.trq", "hp_shaft.trq_0") - self.connect("hpt.trq", "hp_shaft.trq_1") - # Ideally expanding flow by conneting flight condition static pressure to nozzle exhaust pressure - self.connect("fc.Fl_O:stat:P", "core_nozz.Ps_exhaust") - self.connect("fc.Fl_O:stat:P", "byp_nozz.Ps_exhaust") - - balance = self.add_subsystem("balance", om.BalanceComp()) - if design: - balance.add_balance("W", units="lbm/s", eq_units="lbf") - # Here balance.W is implicit state variable that is the OUTPUT of balance object - self.connect( - "balance.W", "fc.W" - ) # Connect the output of balance to the relevant input - self.connect( - "perf.Fn", "balance.lhs:W" - ) # This statement makes perf.Fn the LHS of the balance eqn. - self.promotes("balance", inputs=[("rhs:W", "Fn_DES")]) - - balance.add_balance("FAR", eq_units="degR", lower=1e-4, val=0.017) - self.connect("balance.FAR", "burner.Fl_I:FAR") - self.connect("burner.Fl_O:tot:T", "balance.lhs:FAR") - self.promotes("balance", inputs=[("rhs:FAR", "T4_MAX")]) - - # Note that for the following two balances the mult val is set to -1 so that the NET torque is zero - balance.add_balance( - "lpt_PR", - val=1.5, - lower=1.001, - upper=8, - eq_units="hp", - use_mult=True, - mult_val=-1, - ) - self.connect("balance.lpt_PR", "lpt.PR") - self.connect("lp_shaft.pwr_in_real", "balance.lhs:lpt_PR") - self.connect("lp_shaft.pwr_out_real", "balance.rhs:lpt_PR") - - balance.add_balance( - "hpt_PR", - val=1.5, - lower=1.001, - upper=8, - eq_units="hp", - use_mult=True, - mult_val=-1, - ) - self.connect("balance.hpt_PR", "hpt.PR") - self.connect("hp_shaft.pwr_in_real", "balance.lhs:hpt_PR") - self.connect("hp_shaft.pwr_out_real", "balance.rhs:hpt_PR") - - # Set up all the flow connections: - self.pyc_connect_flow("fc.Fl_O", "inlet.Fl_I") - self.pyc_connect_flow("inlet.Fl_O", "fan.Fl_I") - self.pyc_connect_flow("fan.Fl_O", "splitter.Fl_I") - self.pyc_connect_flow("splitter.Fl_O1", "duct4.Fl_I") - self.pyc_connect_flow("duct4.Fl_O", "lpc.Fl_I") - self.pyc_connect_flow("lpc.Fl_O", "duct6.Fl_I") - self.pyc_connect_flow("duct6.Fl_O", "hpc.Fl_I") - self.pyc_connect_flow("hpc.Fl_O", "bld3.Fl_I") - self.pyc_connect_flow("bld3.Fl_O", "burner.Fl_I") - self.pyc_connect_flow("burner.Fl_O", "hpt.Fl_I") - self.pyc_connect_flow("hpt.Fl_O", "duct11.Fl_I") - self.pyc_connect_flow("duct11.Fl_O", "lpt.Fl_I") - self.pyc_connect_flow("lpt.Fl_O", "duct13.Fl_I") - self.pyc_connect_flow("duct13.Fl_O", "core_nozz.Fl_I") - self.pyc_connect_flow("splitter.Fl_O2", "byp_bld.Fl_I") - self.pyc_connect_flow("byp_bld.Fl_O", "duct15.Fl_I") - self.pyc_connect_flow("duct15.Fl_O", "byp_nozz.Fl_I") - - # Bleed flows: - self.pyc_connect_flow("hpc.cool1", "lpt.cool1", connect_stat=False) - self.pyc_connect_flow("hpc.cool2", "lpt.cool2", connect_stat=False) - self.pyc_connect_flow("bld3.cool3", "hpt.cool3", connect_stat=False) - self.pyc_connect_flow("bld3.cool4", "hpt.cool4", connect_stat=False) - - # Specify solver settings: - newton = self.nonlinear_solver = om.NewtonSolver() - newton.options["atol"] = 1e-8 - - # set this very small, so it never activates and we rely on atol - newton.options["rtol"] = 1e-99 - newton.options["iprint"] = 2 - newton.options["maxiter"] = 50 - newton.options["solve_subsystems"] = True - newton.options["max_sub_solves"] = 1000 - newton.options["reraise_child_analysiserror"] = False - # ls = newton.linesearch = BoundsEnforceLS() - ls = newton.linesearch = om.ArmijoGoldsteinLS() - ls.options["maxiter"] = 3 - ls.options["rho"] = 0.75 - # ls.options['print_bound_enforce'] = True - - self.linear_solver = om.DirectSolver() - - super().setup() - - class MPhbtf(pyc.MPCycle): - def setup(self): - - self.pyc_add_pnt( - "DESIGN", HBTF(thermo_method="CEA") - ) # Create an instance of the High Bypass ratio Turbofan - - self.set_input_defaults("DESIGN.inlet.MN", 0.751) - self.set_input_defaults("DESIGN.fan.MN", 0.4578) - self.set_input_defaults("DESIGN.splitter.BPR", 5.105) - self.set_input_defaults("DESIGN.splitter.MN1", 0.3104) - self.set_input_defaults("DESIGN.splitter.MN2", 0.4518) - self.set_input_defaults("DESIGN.duct4.MN", 0.3121) - self.set_input_defaults("DESIGN.lpc.MN", 0.3059) - self.set_input_defaults("DESIGN.duct6.MN", 0.3563) - self.set_input_defaults("DESIGN.hpc.MN", 0.2442) - self.set_input_defaults("DESIGN.bld3.MN", 0.3000) - self.set_input_defaults("DESIGN.burner.MN", 0.1025) - self.set_input_defaults("DESIGN.hpt.MN", 0.3650) - self.set_input_defaults("DESIGN.duct11.MN", 0.3063) - self.set_input_defaults("DESIGN.lpt.MN", 0.4127) - self.set_input_defaults("DESIGN.duct13.MN", 0.4463) - self.set_input_defaults("DESIGN.byp_bld.MN", 0.4489) - self.set_input_defaults("DESIGN.duct15.MN", 0.4589) - self.set_input_defaults("DESIGN.LP_Nmech", 4666.1, units="rpm") - self.set_input_defaults("DESIGN.HP_Nmech", 14705.7, units="rpm") - - # --- Set up bleed values ----- - - self.pyc_add_cycle_param("inlet.ram_recovery", 0.9990) - self.pyc_add_cycle_param("duct4.dPqP", 0.0048) - self.pyc_add_cycle_param("duct6.dPqP", 0.0101) - self.pyc_add_cycle_param("burner.dPqP", 0.0540) - self.pyc_add_cycle_param("duct11.dPqP", 0.0051) - self.pyc_add_cycle_param("duct13.dPqP", 0.0107) - self.pyc_add_cycle_param("duct15.dPqP", 0.0149) - self.pyc_add_cycle_param("core_nozz.Cv", 0.9933) - self.pyc_add_cycle_param("byp_bld.bypBld:frac_W", 0.005) - self.pyc_add_cycle_param("byp_nozz.Cv", 0.9939) - self.pyc_add_cycle_param("hpc.cool1:frac_W", 0.050708) - self.pyc_add_cycle_param("hpc.cool1:frac_P", 0.5) - self.pyc_add_cycle_param("hpc.cool1:frac_work", 0.5) - self.pyc_add_cycle_param("hpc.cool2:frac_W", 0.020274) - self.pyc_add_cycle_param("hpc.cool2:frac_P", 0.55) - self.pyc_add_cycle_param("hpc.cool2:frac_work", 0.5) - self.pyc_add_cycle_param("bld3.cool3:frac_W", 0.067214) - self.pyc_add_cycle_param("bld3.cool4:frac_W", 0.101256) - self.pyc_add_cycle_param("hpc.cust:frac_P", 0.5) - self.pyc_add_cycle_param("hpc.cust:frac_work", 0.5) - self.pyc_add_cycle_param("hpc.cust:frac_W", 0.0445) - self.pyc_add_cycle_param("hpt.cool3:frac_P", 1.0) - self.pyc_add_cycle_param("hpt.cool4:frac_P", 0.0) - self.pyc_add_cycle_param("lpt.cool1:frac_P", 1.0) - self.pyc_add_cycle_param("lpt.cool2:frac_P", 0.0) - self.pyc_add_cycle_param("hp_shaft.HPX", 250.0, units="hp") - - super().setup() - - import time - - prob = om.Problem() - - prob.model = mp_hbtf = MPhbtf() - - prob.setup() - - prob.set_val("DESIGN.fan.PR", 1.685) - prob.set_val("DESIGN.fan.eff", 0.8948) - - prob.set_val("DESIGN.lpc.PR", 1.935) - prob.set_val("DESIGN.lpc.eff", 0.9243) - - prob.set_val("DESIGN.hpc.PR", 9.369) - prob.set_val("DESIGN.hpc.eff", 0.8707) - - prob.set_val("DESIGN.hpt.eff", 0.8888) - prob.set_val("DESIGN.lpt.eff", 0.8996) - - prob.set_val("DESIGN.fc.alt", alt, units="ft") - prob.set_val("DESIGN.fc.MN", MN) - - prob.set_val("DESIGN.T4_MAX", 2857, units="degR") - prob.set_val("DESIGN.Fn_DES", 5900.0, units="lbf") - - # Set initial guesses for balances - prob["DESIGN.balance.FAR"] = 0.025 - prob["DESIGN.balance.W"] = 100.0 - prob["DESIGN.balance.lpt_PR"] = 4.0 - prob["DESIGN.balance.hpt_PR"] = 3.0 - prob["DESIGN.fc.balance.Pt"] = 5.2 - prob["DESIGN.fc.balance.Tt"] = 440.0 - - prob.set_solver_print(level=-1) - # prob.set_solver_print(level=2, depth=1) - - prob.run_model() - - print() - - # Obtaining variables names - - # variable_names = open("variables_hptf.txt", "w") - # print( - # prob.model.list_outputs(val=True, units=True, implicit=False), - # file=variable_names, - # ) - - # BYPASS VARIABLES - T_tot_out_byp = convert_temperature( - (prob.get_val("DESIGN.byp_nozz.throat_total.flow.Fl_O:tot:T")), - "Rankine", - "Celsius", - ) - V_stat_out_byp = prob.get_val("DESIGN.byp_nozz.mux.Fl_O:stat:V") * 0.3048 - MN_out_byp = prob.get_val("DESIGN.byp_nozz.mux.Fl_O:stat:MN") - P_tot_out_byp = ( - prob.get_val("DESIGN.byp_nozz.throat_total.flow.Fl_O:tot:P") * 6894.7573 - ) # Pa - massflow_stat_out_byp = ( - prob.get_val("DESIGN.byp_nozz.mux.Fl_O:stat:W") * 0.45359237 - ) # kg/s - T_stat_out_byp = convert_temperature( - (prob.get_val("DESIGN.byp_nozz.mux.Fl_O:stat:T")), "Rankine", "Celsius" - ) # celsius - - # CORE VARIABLES - T_tot_out_core = convert_temperature( - (prob.get_val("DESIGN.core_nozz.throat_total.flow.Fl_O:tot:T")), - "Rankine", - "Kelvin", - ) - V_stat_out_core = prob.get_val("DESIGN.core_nozz.mux.Fl_O:stat:V") * 0.3048 - MN_out_core = prob.get_val("DESIGN.core_nozz.mux.Fl_O:stat:MN") - P_tot_out_core = ( - prob.get_val("DESIGN.core_nozz.throat_total.flow.Fl_O:tot:P") * 6894.7573 - ) # Pa - massflow_stat_out_core = ( - prob.get_val("DESIGN.core_nozz.mux.Fl_O:stat:W") * 0.45359237 - ) # kg/s - T_stat_out_core = convert_temperature( - (prob.get_val("DESIGN.core_nozz.mux.Fl_O:stat:T")), "Rankine", "Kelvin" - ) # celsius - - res = np.array( - [ - T_tot_out_byp, - V_stat_out_byp, - MN_out_byp, - P_tot_out_byp, - massflow_stat_out_byp, - T_stat_out_byp, - T_tot_out_core, - V_stat_out_core, - MN_out_core, - P_tot_out_core, - massflow_stat_out_core, - T_stat_out_core, - ] - ) - print(f"T_tot_out_core = {T_tot_out_core} [K]") - print(f"V_stat_out_core = {V_stat_out_core} [m/s]") - print(f"MN_out_core = {MN_out_core} [adim]") - print(f"P_tot_out_core = {P_tot_out_core} [Pa]") - print(f"massflow_out_core = {massflow_stat_out_core} [kg/s]") - print(f"T_stat_out_core = {T_stat_out_core} [K]") - print(f"T_tot_out_byp = {T_tot_out_byp} [K]") - print(f"V_stat_out_byp = {V_stat_out_byp} [m/s]") - print(f"MN_out_byp = {MN_out_byp} [adim]") - print(f"P_tot_out_byp = {P_tot_out_byp} [Pa]") - print(f"massflow_stat_out_byp = {massflow_stat_out_byp} [kg/s]") - print(f"T_stat_out_core = {T_stat_out_core} [K]") - - return res - - -if __name__ == "__main__": - - alt = float(input("insert altitude [ft]: ")) - - MN = float(input("insert mach number[adim]: ")) - - run_turbofan_analysis_test(alt, MN) - print("temperature [celsius], stat velocity [m/s], MN for bypass and core") diff --git a/ceasiompy/ThermoData/testing_pycycle/des_turbojet_func.py b/ceasiompy/ThermoData/testing_pycycle/des_turbojet_func.py deleted file mode 100644 index d36447fef..000000000 --- a/ceasiompy/ThermoData/testing_pycycle/des_turbojet_func.py +++ /dev/null @@ -1,173 +0,0 @@ -import sys - -import openmdao.api as om - -import pycycle.api as pyc - -import numpy as np - -import re - -from scipy.constants import convert_temperature - - -def run_turbojet_analysis(alt, MN, Fn): - class Turbojet(pyc.Cycle): - def setup(self): - - USE_TABULAR = True - - if USE_TABULAR: - self.options["thermo_method"] = "TABULAR" - self.options["thermo_data"] = pyc.AIR_JETA_TAB_SPEC - FUEL_TYPE = "FAR" - - design = self.options["design"] - - # Add engine elements - self.add_subsystem("fc", pyc.FlightConditions()) - self.add_subsystem("inlet", pyc.Inlet()) - self.add_subsystem( - "comp", - pyc.Compressor(map_data=pyc.AXI5, map_extrap=True), - promotes_inputs=["Nmech"], - ) - self.add_subsystem("burner", pyc.Combustor(fuel_type=FUEL_TYPE)) - self.add_subsystem( - "turb", pyc.Turbine(map_data=pyc.LPT2269), promotes_inputs=["Nmech"] - ) - self.add_subsystem("nozz", pyc.Nozzle(nozzType="CD", lossCoef="Cv")) - self.add_subsystem( - "shaft", pyc.Shaft(num_ports=2), promotes_inputs=["Nmech"] - ) - self.add_subsystem("perf", pyc.Performance(num_nozzles=1, num_burners=1)) - - # Connect flow stations - self.pyc_connect_flow("fc.Fl_O", "inlet.Fl_I", connect_w=False) - self.pyc_connect_flow("inlet.Fl_O", "comp.Fl_I") - self.pyc_connect_flow("comp.Fl_O", "burner.Fl_I") - self.pyc_connect_flow("burner.Fl_O", "turb.Fl_I") - self.pyc_connect_flow("turb.Fl_O", "nozz.Fl_I") - - # Make other non-flow connections - # Connect turbomachinery elements to shaft - self.connect("comp.trq", "shaft.trq_0") - self.connect("turb.trq", "shaft.trq_1") - - # Connnect nozzle exhaust to freestream static conditions - self.connect("fc.Fl_O:stat:P", "nozz.Ps_exhaust") - - # Connect outputs to perfomance element - self.connect("inlet.Fl_O:tot:P", "perf.Pt2") - self.connect("comp.Fl_O:tot:P", "perf.Pt3") - self.connect("burner.Wfuel", "perf.Wfuel_0") - self.connect("inlet.F_ram", "perf.ram_drag") - self.connect("nozz.Fg", "perf.Fg_0") - - # Add balances for design and off-design - balance = self.add_subsystem("balance", om.BalanceComp()) - if design: - - balance.add_balance( - "W", units="lbm/s", eq_units="lbf", rhs_name="Fn_target" - ) - self.connect("balance.W", "inlet.Fl_I:stat:W") - self.connect("perf.Fn", "balance.lhs:W") - - balance.add_balance( - "FAR", eq_units="degR", lower=1e-4, val=0.017, rhs_name="T4_target" - ) - self.connect("balance.FAR", "burner.Fl_I:FAR") - self.connect("burner.Fl_O:tot:T", "balance.lhs:FAR") - - balance.add_balance( - "turb_PR", val=1.5, lower=1.001, upper=8, eq_units="hp", rhs_val=0.0 - ) - self.connect("balance.turb_PR", "turb.PR") - self.connect("shaft.pwr_net", "balance.lhs:turb_PR") - - newton = self.nonlinear_solver = om.NewtonSolver() - newton.options["atol"] = 1e-6 - newton.options["rtol"] = 1e-6 - newton.options["iprint"] = 2 - newton.options["maxiter"] = 15 - newton.options["solve_subsystems"] = True - newton.options["max_sub_solves"] = 100 - newton.options["reraise_child_analysiserror"] = False - - self.linear_solver = om.DirectSolver() - - super().setup() - - class MPTurbojet(pyc.MPCycle): - def setup(self): - self.pyc_add_pnt("DESIGN", Turbojet()) - - self.set_input_defaults("DESIGN.Nmech", 8070.0, units="rpm") - self.set_input_defaults("DESIGN.inlet.MN", 0.60) - self.set_input_defaults("DESIGN.comp.MN", 0.020) # .2 - self.set_input_defaults("DESIGN.burner.MN", 0.020) # .2 - self.set_input_defaults("DESIGN.turb.MN", 0.4) - - self.pyc_add_cycle_param("burner.dPqP", 0.03) - self.pyc_add_cycle_param("nozz.Cv", 0.99) - - super().setup() - - import time - - # defining the optimization problem - - prob = om.Problem() - mp_turbojet = prob.model = MPTurbojet() - prob.setup(check=False) - - # define input values - prob.set_val("DESIGN.fc.alt", alt, units="ft") - prob.set_val("DESIGN.fc.MN", MN) - prob.set_val("DESIGN.balance.Fn_target", Fn, units="lbf") - prob.set_val("DESIGN.balance.T4_target", 2370.0, units="degR") - prob.set_val("DESIGN.comp.PR", 13.5) - prob.set_val("DESIGN.comp.eff", 0.83) - prob.set_val("DESIGN.turb.eff", 0.86) - - # define initial guesses for the balances - prob["DESIGN.balance.FAR"] = 0.0175506829934 - prob["DESIGN.balance.W"] = 168.453135137 - prob["DESIGN.balance.turb_PR"] = 4.46138725662 - prob["DESIGN.fc.balance.Pt"] = 14.6955113159 - prob["DESIGN.fc.balance.Tt"] = 518.665288153 - - prob.set_solver_print(level=-1) - # prob.set_solver_print(level=2, depth=1) - - prob.run_model() - - print() - - # command to visualize all the output of the system - # a = prob.model.list_outputs(val=True, units=True) - - T_tot_out = convert_temperature( - (prob.get_val("DESIGN.nozz.throat_total.flow.Fl_O:tot:T")), "Rankine", "Kelvin" - ) - V_stat_out = (prob.get_val("DESIGN.nozz.mux.Fl_O:stat:V")) * 0.3048 - MN_out = prob.get_val("DESIGN.nozz.mux.Fl_O:stat:MN") - T_stat_out = convert_temperature( - prob.get_val("DESIGN.nozz.mux.Fl_O:stat:T"), "Rankine", "Kelvin" - ) # celsius - massflow_stat_out = prob.get_val("DESIGN.nozz.mux.Fl_O:stat:W") * 0.45359237 # kg/s - P_tot_out = ( - prob.get_val("DESIGN.nozz.throat_total.flow.Fl_O:tot:P") * 6894.7573 - ) # Pa - - res = np.array( - [T_tot_out, V_stat_out, MN_out, P_tot_out, massflow_stat_out, T_stat_out] - ) - print(f"T_tot_out = {T_tot_out} [K]") - print(f"V_stat_out = {V_stat_out} [m/s]") - print(f"MN_out = {MN_out} [adim]") - print(f"P_tot_out = {P_tot_out} [Pa]") - print(f"massflow_out = {massflow_stat_out} [kg/s]") - print(f"T_stat_out = {T_stat_out} [K]") - return res From 204af4ab850c9a42bcac88fe871c2f828df5c373 Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Wed, 7 Feb 2024 12:18:17 +0100 Subject: [PATCH 09/55] solving some issue for merging --- ceasiompy/ThermoData/func/turbofan_func.py | 2 +- ceasiompy/ThermoData/thermodata.py | 9 +-------- 2 files changed, 2 insertions(+), 9 deletions(-) diff --git a/ceasiompy/ThermoData/func/turbofan_func.py b/ceasiompy/ThermoData/func/turbofan_func.py index 1cb944b38..7f6548b8a 100644 --- a/ceasiompy/ThermoData/func/turbofan_func.py +++ b/ceasiompy/ThermoData/func/turbofan_func.py @@ -295,7 +295,7 @@ def viewer(prob, pt, file=sys.stdout): prob = om.Problem() - prob.model = mp_hbtf = MPhbtf() + prob.model = MPhbtf() prob.setup() diff --git a/ceasiompy/ThermoData/thermodata.py b/ceasiompy/ThermoData/thermodata.py index b7b621fde..5c624caf6 100644 --- a/ceasiompy/ThermoData/thermodata.py +++ b/ceasiompy/ThermoData/thermodata.py @@ -3,7 +3,7 @@ Developed by CFS ENGINEERING, 1015 Lausanne, Switzerland -Calculate outlet conditions fot turbojet and turbofan engines by using the open source code PyCycle +Calculate outlet conditions fot turbojet and turbofan engines by using the open source code PyCycle and saving those conditions in a text file | Author: Giacomo Benedetti and Francesco Marcucci @@ -24,7 +24,6 @@ from ceasiompy.utils.ceasiomlogger import get_logger from ceasiompy.utils.moduleinterfaces import ( - check_cpacs_input_requirements, get_toolinput_file_path, get_tooloutput_file_path, ) @@ -36,12 +35,6 @@ from ceasiompy.utils.commonnames import ( ENGINE_BOUNDARY_CONDITIONS, ) -from cpacspy.cpacsfunctions import ( - get_value_or_default, -) -from cpacspy.cpacsfunctions import create_branch, get_value, get_value_or_default -from cpacspy.cpacspy import CPACS -from markdownpy.markdownpy import MarkdownDoc from ceasiompy.utils.ceasiompyutils import get_results_directory From ed669c4ffa1bbce406f8e9a54b0c81bb6b249b76 Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Wed, 7 Feb 2024 12:30:41 +0100 Subject: [PATCH 10/55] solving config file generation single condition --- ceasiompy/SU2Run/func/su2config.py | 12 ++++++++---- 1 file changed, 8 insertions(+), 4 deletions(-) diff --git a/ceasiompy/SU2Run/func/su2config.py b/ceasiompy/SU2Run/func/su2config.py index e8e4ee232..b1d5b1e0e 100644 --- a/ceasiompy/SU2Run/func/su2config.py +++ b/ceasiompy/SU2Run/func/su2config.py @@ -310,10 +310,14 @@ def add_thermodata(cfg, cpacs, alt, case_nb, alt_list): Atm = Atmosphere(alt) tot_temp_in = Atm.temperature[0] tot_pressure_in = Atm.pressure[0] - tot_temp_out = get_value(cpacs.tixi, ENGINE_BC + "/temperatureOutlet").split(";") - tot_pressure_out = get_value(cpacs.tixi, ENGINE_BC + "/pressureOutlet").split(";") - tot_temp_out = tot_temp_out[case_nb] - tot_pressure_out = tot_pressure_out[case_nb] + if len(alt_list) > 1: + tot_temp_out = get_value(cpacs.tixi, ENGINE_BC + "/temperatureOutlet").split(";") + tot_pressure_out = get_value(cpacs.tixi, ENGINE_BC + "/pressureOutlet").split(";") + tot_temp_out = tot_temp_out[case_nb] + tot_pressure_out = tot_pressure_out[case_nb] + else: + tot_temp_out = get_value(cpacs.tixi, ENGINE_BC + "/temperatureOutlet") + tot_pressure_out = get_value(cpacs.tixi, ENGINE_BC + "/pressureOutlet") cfg["INLET_TYPE"] = "TOTAL_CONDITIONS" cfg["MARKER_INLET"] = ( f"(INLET_ENGINE, {tot_temp_in}, {tot_pressure_in}, {1},{0},{0}, " From 7495857dd5fc5e202a258b0524ec9f553cdc8f51 Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Wed, 7 Feb 2024 13:50:15 +0100 Subject: [PATCH 11/55] solving flake8 issues --- ceasiompy/ThermoData/func/turbofan_func.py | 8 +++----- ceasiompy/ThermoData/func/turbojet_func.py | 14 ++++---------- 2 files changed, 7 insertions(+), 15 deletions(-) diff --git a/ceasiompy/ThermoData/func/turbofan_func.py b/ceasiompy/ThermoData/func/turbofan_func.py index 7f6548b8a..187afd8eb 100644 --- a/ceasiompy/ThermoData/func/turbofan_func.py +++ b/ceasiompy/ThermoData/func/turbofan_func.py @@ -241,9 +241,9 @@ def viewer(prob, pt, file=sys.stdout): FAR = prob["DESIGN.balance.FAR"] else: MN = prob[pt + ".fc.Fl_O:stat:MN"] - LPT_PR = prob[pt + ".lpt.PR"] - HPT_PR = prob[pt + ".hpt.PR"] - FAR = prob[pt + ".balance.FAR"] + # LPT_PR = prob[pt + ".lpt.PR"] + # HPT_PR = prob[pt + ".hpt.PR"] + # FAR = prob[pt + ".balance.FAR"] summary_data = ( MN, @@ -328,8 +328,6 @@ def viewer(prob, pt, file=sys.stdout): prob.set_solver_print(level=-1) prob.set_solver_print(level=2, depth=1) - flight_env = [(0.9, 6000)] - viewer_file = open("hbtf_des_view.out", "w") for PC in [1, 0.9]: diff --git a/ceasiompy/ThermoData/func/turbojet_func.py b/ceasiompy/ThermoData/func/turbojet_func.py index 371195bad..d122f96fb 100644 --- a/ceasiompy/ThermoData/func/turbojet_func.py +++ b/ceasiompy/ThermoData/func/turbojet_func.py @@ -53,9 +53,7 @@ def setup(self): "turb", pyc.Turbine(map_data=pyc.LPT2269), promotes_inputs=["Nmech"] ) self.add_subsystem("nozz", pyc.Nozzle(nozzType="CD", lossCoef="Cv")) - self.add_subsystem( - "shaft", pyc.Shaft(num_ports=2), promotes_inputs=["Nmech"] - ) + self.add_subsystem("shaft", pyc.Shaft(num_ports=2), promotes_inputs=["Nmech"]) self.add_subsystem("perf", pyc.Performance(num_nozzles=1, num_burners=1)) # Connect flow stations @@ -84,9 +82,7 @@ def setup(self): balance = self.add_subsystem("balance", om.BalanceComp()) if design: - balance.add_balance( - "W", units="lbm/s", eq_units="lbf", rhs_name="Fn_target" - ) + balance.add_balance("W", units="lbm/s", eq_units="lbf", rhs_name="Fn_target") self.connect("balance.W", "inlet.Fl_I:stat:W") self.connect("perf.Fn", "balance.lhs:W") @@ -136,7 +132,7 @@ def setup(self): prob = om.Problem() - mp_turbojet = prob.model = MPTurbojet() + prob.model = MPTurbojet() prob.setup(check=False) # define input values @@ -188,9 +184,7 @@ def setup(self): prob.get_val("DESIGN.nozz.mux.Fl_O:stat:T"), "Rankine", "Kelvin" ) # celsius massflow_stat_out = prob.get_val("DESIGN.nozz.mux.Fl_O:stat:W") * 0.45359237 # kg/s - P_tot_out = ( - prob.get_val("DESIGN.nozz.throat_total.flow.Fl_O:tot:P") * 6894.7573 - ) # Pa + P_tot_out = prob.get_val("DESIGN.nozz.throat_total.flow.Fl_O:tot:P") * 6894.7573 # Pa P_stat_out = prob.get_val("DESIGN.nozz.mux.Fl_O:stat:P") * 6894.7573 # Pa return ( From a1f72a925263bfea7c5642c1d8751accc09aa95e Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Wed, 7 Feb 2024 13:53:00 +0100 Subject: [PATCH 12/55] solving flake8 issues --- ceasiompy/ThermoData/func/turbofan_func.py | 6 +++--- 1 file changed, 3 insertions(+), 3 deletions(-) diff --git a/ceasiompy/ThermoData/func/turbofan_func.py b/ceasiompy/ThermoData/func/turbofan_func.py index 187afd8eb..9a24727dc 100644 --- a/ceasiompy/ThermoData/func/turbofan_func.py +++ b/ceasiompy/ThermoData/func/turbofan_func.py @@ -236,9 +236,9 @@ def viewer(prob, pt, file=sys.stdout): if pt == "DESIGN": MN = prob["DESIGN.fc.Fl_O:stat:MN"] - LPT_PR = prob["DESIGN.balance.lpt_PR"] - HPT_PR = prob["DESIGN.balance.hpt_PR"] - FAR = prob["DESIGN.balance.FAR"] + # LPT_PR = prob["DESIGN.balance.lpt_PR"] + # HPT_PR = prob["DESIGN.balance.hpt_PR"] + # FAR = prob["DESIGN.balance.FAR"] else: MN = prob[pt + ".fc.Fl_O:stat:MN"] # LPT_PR = prob[pt + ".lpt.PR"] From 2a600624084ee23820616b8dc94f6c1cd4e618e8 Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Wed, 7 Feb 2024 14:10:32 +0100 Subject: [PATCH 13/55] solving Codacy issues --- ceasiompy/SU2Run/func/su2config.py | 1 - ceasiompy/SU2Run/func/su2configrans.py | 566 --------------------- ceasiompy/ThermoData/__specs__.py | 2 - ceasiompy/ThermoData/func/run_func.py | 2 +- ceasiompy/ThermoData/func/turbofan_func.py | 2 - ceasiompy/ThermoData/func/turbojet_func.py | 2 - ceasiompy/ThermoData/thermodata.py | 8 - 7 files changed, 1 insertion(+), 582 deletions(-) delete mode 100644 ceasiompy/SU2Run/func/su2configrans.py diff --git a/ceasiompy/SU2Run/func/su2config.py b/ceasiompy/SU2Run/func/su2config.py index b1d5b1e0e..8e08de5ed 100644 --- a/ceasiompy/SU2Run/func/su2config.py +++ b/ceasiompy/SU2Run/func/su2config.py @@ -20,7 +20,6 @@ # IMPORTS # ================================================================================================= -import numpy as np from pathlib import Path from shutil import copyfile diff --git a/ceasiompy/SU2Run/func/su2configrans.py b/ceasiompy/SU2Run/func/su2configrans.py deleted file mode 100644 index a1feee3cd..000000000 --- a/ceasiompy/SU2Run/func/su2configrans.py +++ /dev/null @@ -1,566 +0,0 @@ -""" -CEASIOMpy: Conceptual Aircraft Design Software - -Developed by CFS ENGINEERING, 1015 Lausanne, Switzerland - -Function generate or modify SU2 configuration files - -Python version: >=3.8 - -| Author: Aidan Jungo -| Creation: 2020-02-24 - -TODO: - - * add and test control surface functions - -""" - -# ================================================================================================= -# IMPORTS -# ================================================================================================= - -from pathlib import Path -from shutil import copyfile - -from ambiance import Atmosphere -from ceasiompy.SU2Run.func.su2actuatordiskfile import ( - get_advanced_ratio, - get_radial_stations, - save_plots, - thrust_calculator, - write_actuator_disk_data, - write_header, -) -from ceasiompy.SU2Run.func.su2utils import get_mesh_markers, get_su2_config_template -from ceasiompy.utils.ceasiomlogger import get_logger -from ceasiompy.utils.commonnames import ( - ACTUATOR_DISK_FILE_NAME, - ACTUATOR_DISK_INLET_SUFFIX, - ACTUATOR_DISK_OUTLET_SUFFIX, - CONFIG_CFD_NAME, - SU2_FORCES_BREAKDOWN_NAME, -) -from ceasiompy.utils.commonxpath import ( - GMSH_SYMMETRY_XPATH, - PROP_XPATH, - RANGE_XPATH, - SU2_ACTUATOR_DISK_XPATH, - SU2_AEROMAP_UID_XPATH, - SU2_BC_FARFIELD_XPATH, - SU2_BC_WALL_XPATH, - SU2_CFL_NB_XPATH, - SU2_CFL_ADAPT_XPATH, - SU2_CFL_ADAPT_PARAM_DOWN_XPATH, - SU2_CFL_ADAPT_PARAM_UP_XPATH, - SU2_CFL_MAX_XPATH, - SU2_CFL_MIN_XPATH, - SU2_CONTROL_SURF_XPATH, - SU2_DAMPING_DER_XPATH, - SU2_DEF_MESH_XPATH, - SU2_FIXED_CL_XPATH, - SU2_MAX_ITER_XPATH, - SU2_MG_LEVEL_XPATH, - SU2_ROTATION_RATE_XPATH, - SU2_TARGET_CL_XPATH, - SU2MESH_XPATH, - ENGINE_TYPE_XPATH, - ENGINE_BC, -) -from ceasiompy.utils.configfiles import ConfigFile -from cpacspy.cpacsfunctions import ( - create_branch, - get_string_vector, - get_value, - get_value_or_default, -) -from cpacspy.cpacspy import CPACS - -log = get_logger() - -MODULE_DIR = Path(__file__).parent - - -# ================================================================================================= -# CLASSES -# ================================================================================================= - - -# ================================================================================================= -# FUNCTIONS -# ================================================================================================= - - -def add_damping_derivatives(cfg, wkdir, case_dir_name, rotation_rate): - """Add damping derivatives parameter to the config file and save them to their respective - directory. - - Args: - cfg (ConfigFile): ConfigFile object. - wkdir (Path): Path to the working directory - case_dir_name (str): Name of the case directory - rotation_rate (float): Rotation rate that will be impose to calculate damping derivatives - """ - - cfg["GRID_MOVEMENT"] = "ROTATING_FRAME" - - cfg["ROTATION_RATE"] = f"{rotation_rate} 0.0 0.0" - case_dir = Path(wkdir, f"{case_dir_name}_dp") - case_dir.mkdir() - cfg.write_file(Path(case_dir, CONFIG_CFD_NAME), overwrite=True) - - cfg["ROTATION_RATE"] = f"0.0 {rotation_rate} 0.0" - case_dir = Path(wkdir, f"{case_dir_name}_dq") - case_dir.mkdir() - cfg.write_file(Path(case_dir, CONFIG_CFD_NAME), overwrite=True) - - cfg["ROTATION_RATE"] = f"0.0 0.0 {rotation_rate}" - case_dir = Path(wkdir, f"{case_dir_name}_dr") - case_dir.mkdir() - cfg.write_file(Path(case_dir, CONFIG_CFD_NAME), overwrite=True) - - log.info("Damping derivatives cases directories has been created.") - - -def add_actuator_disk(cfg, cpacs, case_dir_path, actuator_disk_file, mesh_markers, alt, mach): - """Add actuator disk parameter to the config file. - - Args: - cfg (ConfigFile): ConfigFile object. - cpacs (CPACS): CPACS object from cpacspy library - case_dir_path (Path): Path object to the current case directory - actuator_disk_file (Path): Path to the actuator disk file - mesh_markers (dict): Dictionary containing all the mesh markers - - Returns: - cfg (ConfigFile): ConfigFile object. - """ - - ad_inlet_marker = sorted(mesh_markers["actuator_disk_inlet"]) - ad_outlet_marker = sorted(mesh_markers["actuator_disk_outlet"]) - - if "None" in ad_inlet_marker or "None" in ad_outlet_marker: - return - - if len(ad_inlet_marker) != len(ad_outlet_marker): - raise ValueError( - "The number of inlet and outlet markers of the actuator disk must be the same." - ) - - # Get rotorcraft configuration (propeller) - try: - rotorcraft_config = cpacs.rotorcraft.configuration - except AttributeError: - raise ValueError( - "The actuator disk is defined but no rotorcraft configuration is defined in " - "the CPACS file." - ) - - rotor_uid_pos = {} - for i in range(1, rotorcraft_config.get_rotor_count() + 1): - rotor = rotorcraft_config.get_rotor(i) - - rotor_uid = rotor.get_uid() - pos_x = rotor.get_translation().x - pos_y = rotor.get_translation().y - pos_z = rotor.get_translation().z - radius = rotor.get_radius() - hub_radius = 0.0 # TODO: get correctly from CPACS - - rotor_xpath = cpacs.tixi.uIDGetXPath(rotor_uid) - - number_of_blades_xpath = ( - rotor_xpath + "/rotorHub/rotorBladeAttachments/rotorBladeAttachment/numberOfBlades" - ) - number_of_blades = get_value_or_default(cpacs.tixi, number_of_blades_xpath, 3) - - # TODO: this is the nominal speed, how to get a speed which correspond to each flight cond. - rotational_velocity_xpath = rotor_xpath + "/nominalRotationsPerMinute" - rotational_velocity = ( - get_value_or_default(cpacs.tixi, rotational_velocity_xpath, 3000) / 60.0 - ) - - rotor_uid_pos[rotor_uid] = ( - pos_x, - pos_y, - pos_z, - radius, - hub_radius, - number_of_blades, - rotational_velocity, - ) - - cfg["ACTDISK_DOUBLE_SURFACE"] = "YES" - cfg["ACTDISK_TYPE"] = "VARIABLE_LOAD" - cfg["ACTDISK_FILENAME"] = ACTUATOR_DISK_FILE_NAME - cfg["MGLEVEL"] = 0 # Calculation diverges if multigrid is used with a disk actuator - - actdisk_markers = [] - - f = open(actuator_disk_file, "w") - f = write_header(f) - - for maker_inlet, marker_outlet in zip(ad_inlet_marker, ad_outlet_marker): - inlet_uid = maker_inlet.split(ACTUATOR_DISK_INLET_SUFFIX)[0] - outlet_uid = marker_outlet.split(ACTUATOR_DISK_OUTLET_SUFFIX)[0] - - if inlet_uid != outlet_uid: - raise ValueError("The inlet and outlet markers of the actuator disk must be the same.") - - if "_mirrored" in maker_inlet: - uid = inlet_uid.split("_mirrored")[0] - sym = -1 - else: - uid = inlet_uid - sym = 1 - - center = [] - center.append(round(rotor_uid_pos[uid][0], 5)) - center.append(round(sym * rotor_uid_pos[uid][1], 5)) - center.append(round(rotor_uid_pos[uid][2], 5)) - - axis = (1.0, 0.0, 0.0) # TODO: get the axis by applying the rotation matrix - radius = round(rotor_uid_pos[uid][3], 5) - hub_radius = round(rotor_uid_pos[uid][4], 5) - number_of_blades = round(rotor_uid_pos[uid][5], 5) - rotational_velocity = round(rotor_uid_pos[uid][6], 5) - - actdisk_markers.append(maker_inlet) - actdisk_markers.append(marker_outlet) - actdisk_markers.append(str(center[0])) - actdisk_markers.append(str(center[1])) - actdisk_markers.append(str(center[2])) - actdisk_markers.append(str(center[0])) - actdisk_markers.append(str(center[1])) - actdisk_markers.append(str(center[2])) - - Atm = Atmosphere(alt) - free_stream_velocity = mach * Atm.speed_of_sound[0] - - radial_stations = get_radial_stations(radius, hub_radius) - advanced_ratio = get_advanced_ratio(free_stream_velocity, rotational_velocity, radius) - - prandtl_correction_xpath = PROP_XPATH + "/propeller/blade/loss" - prandtl_correction = get_value_or_default(cpacs.tixi, prandtl_correction_xpath, True) - - thrust_xpath = PROP_XPATH + "/propeller/thrust" - thrust = get_value_or_default(cpacs.tixi, thrust_xpath, 3000) - total_thrust_coefficient = float( - thrust / (Atm.density * rotational_velocity**2 * (radius * 2) ** 4) - ) - - ( - radial_thrust_coefs, - radial_power_coefs, - non_dimensional_radius, - optimal_axial_interference_factor, - optimal_rotational_interference_factor, - prandtl_correction_values, - ) = thrust_calculator( - radial_stations, - total_thrust_coefficient, - radius, - free_stream_velocity, - prandtl_correction, - number_of_blades, - rotational_velocity, - ) - - save_plots( - radial_stations, - radial_thrust_coefs, - radial_power_coefs, - non_dimensional_radius, - optimal_axial_interference_factor, - optimal_rotational_interference_factor, - prandtl_correction_values, - case_dir_path, - inlet_uid, - ) - - f = write_actuator_disk_data( - file=f, - inlet_marker=maker_inlet, - outlet_marker=marker_outlet, - center=center, - axis=axis, - radius=radius, - advanced_ratio=advanced_ratio, - radial_stations=radial_stations, - radial_thrust_coefs=radial_thrust_coefs, - radial_power_coefs=radial_power_coefs, - ) - - cfg["MARKER_ACTDISK"] = " (" + ", ".join(actdisk_markers) + " )" - - f.close() - - -def generate_su2_cfd_config(cpacs_path, cpacs_out_path, wkdir): - """Function to create SU2 config file. - - Function 'generate_su2_cfd_config' reads data in the CPACS file and generate configuration - files for one or multiple flight conditions (alt,mach,aoa,aos) - - Source: - * SU2 config template: https://github.com/su2code/SU2/blob/master/config_template.cfg - - Args: - cpacs_path (Path): Path to CPACS file - cpacs_out_path (Path):Path to CPACS output file - wkdir (Path): Path to the working directory - - """ - - cpacs = CPACS(cpacs_path) - - su2_mesh = Path(get_value(cpacs.tixi, SU2MESH_XPATH)) - if not su2_mesh.is_file(): - raise FileNotFoundError(f"SU2 mesh file {su2_mesh} not found") - - mesh_markers = get_mesh_markers(su2_mesh) - - create_branch(cpacs.tixi, SU2_BC_WALL_XPATH) - bc_wall_str = ";".join(mesh_markers["wall"]) - cpacs.tixi.updateTextElement(SU2_BC_WALL_XPATH, bc_wall_str) - - create_branch(cpacs.tixi, SU2_BC_FARFIELD_XPATH) - bc_farfiled_str = ";".join(mesh_markers["engine_intake"] + mesh_markers["engine_exhaust"]) - cpacs.tixi.updateTextElement(SU2_BC_FARFIELD_XPATH, bc_farfiled_str) - - create_branch(cpacs.tixi, SU2_ACTUATOR_DISK_XPATH) - bc_actuator_disk_str = ";".join( - mesh_markers["actuator_disk_inlet"] + mesh_markers["actuator_disk_outlet"] - ) - cpacs.tixi.updateTextElement(SU2_ACTUATOR_DISK_XPATH, bc_actuator_disk_str) - - fixed_cl = get_value_or_default(cpacs.tixi, SU2_FIXED_CL_XPATH, "NO") - target_cl = get_value_or_default(cpacs.tixi, SU2_TARGET_CL_XPATH, 1.0) - - if fixed_cl == "NO": - # Get the first aeroMap as default one or create automatically one - aeromap_list = cpacs.get_aeromap_uid_list() - - if aeromap_list: - aeromap_default = aeromap_list[0] - log.info(f"The aeromap is {aeromap_default}") - - aeromap_uid = get_value_or_default(cpacs.tixi, SU2_AEROMAP_UID_XPATH, aeromap_default) - - activate_aeromap = cpacs.get_aeromap_by_uid(aeromap_uid) - alt_list = activate_aeromap.get("altitude").tolist() - mach_list = activate_aeromap.get("machNumber").tolist() - aoa_list = activate_aeromap.get("angleOfAttack").tolist() - aos_list = activate_aeromap.get("angleOfSideslip").tolist() - - else: - default_aeromap = cpacs.create_aeromap("DefaultAeromap") - default_aeromap.description = "AeroMap created automatically" - - mach = get_value_or_default(cpacs.tixi, RANGE_XPATH + "/cruiseMach", 0.3) - alt = get_value_or_default(cpacs.tixi, RANGE_XPATH + "/cruiseAltitude", 10000) - - default_aeromap.add_row(alt=alt, mach=mach, aos=0.0, aoa=0.0) - default_aeromap.save() - - alt_list = [alt] - mach_list = [mach] - aoa_list = [0.0] - aos_list = [0.0] - - aeromap_uid = get_value_or_default(cpacs.tixi, SU2_AEROMAP_UID_XPATH, "DefaultAeromap") - log.info(f"{aeromap_uid} has been created") - - else: # if fixed_cl == 'YES': - log.info("Configuration file for fixed CL calculation will be created.") - - fixed_cl_aeromap = cpacs.create_aeromap("aeroMap_fixedCL_SU2") - fixed_cl_aeromap.description = f"AeroMap created for SU2 fixed CL value of {target_cl}" - - mach = get_value_or_default(cpacs.tixi, RANGE_XPATH + "/cruiseMach", 0.78) - alt = get_value_or_default(cpacs.tixi, RANGE_XPATH + "/cruiseAltitude", 12000) - - fixed_cl_aeromap.add_row(alt=alt, mach=mach, aos=0.0, aoa=0.0) - fixed_cl_aeromap.save() - - alt_list = [alt] - mach_list = [mach] - aoa_list = [0.0] - aos_list = [0.0] - - cfg = ConfigFile(get_su2_config_template()) - - # Check if symmetry plane is defined (Default: False) - sym_factor = 1.0 - if get_value_or_default(cpacs.tixi, GMSH_SYMMETRY_XPATH, False): - log.info("Symmetry plane is defined. The reference area will be divided by 2.") - sym_factor = 2.0 - - # General parameters - cfg["RESTART_SOL"] = "NO" - cfg["REF_LENGTH"] = cpacs.aircraft.ref_length - cfg["REF_AREA"] = cpacs.aircraft.ref_area / sym_factor - cfg["REF_ORIGIN_MOMENT_X"] = cpacs.aircraft.ref_point_x - cfg["REF_ORIGIN_MOMENT_Y"] = cpacs.aircraft.ref_point_y - cfg["REF_ORIGIN_MOMENT_Z"] = cpacs.aircraft.ref_point_z - - # Settings - - cfl_down = get_value_or_default(cpacs.tixi, SU2_CFL_ADAPT_PARAM_DOWN_XPATH, 0.5) - cfl_up = get_value_or_default(cpacs.tixi, SU2_CFL_ADAPT_PARAM_UP_XPATH, 1.5) - cfl_min = get_value_or_default(cpacs.tixi, SU2_CFL_MIN_XPATH, 0.5) - cfl_max = get_value_or_default(cpacs.tixi, SU2_CFL_MAX_XPATH, 100) - - if get_value_or_default(cpacs.tixi, SU2_CFL_ADAPT_XPATH, True): - cfg["CFL_ADAPT"] = "YES" - - else: - cfg["CFL_ADAPT"] = "NO" - - cfg["INNER_ITER"] = int(get_value_or_default(cpacs.tixi, SU2_MAX_ITER_XPATH, 200)) - cfg["CFL_NUMBER"] = get_value_or_default(cpacs.tixi, SU2_CFL_NB_XPATH, 1.0) - cfg["CFL_ADAPT_PARAM"] = f"( {cfl_down}, {cfl_up}, {cfl_min}, {cfl_max} )" - cfg["MGLEVEL"] = int(get_value_or_default(cpacs.tixi, SU2_MG_LEVEL_XPATH, 3)) - - # Fixed CL mode (AOA will not be taken into account) - cfg["FIXED_CL_MODE"] = fixed_cl - cfg["TARGET_CL"] = target_cl - cfg["DCL_DALPHA"] = "0.1" - cfg["UPDATE_AOA_ITER_LIMIT"] = "50" - cfg["ITER_DCL_DALPHA"] = "80" - - # Mesh Marker - bc_wall_str = f"( {','.join(mesh_markers['wall'])} )" - - # ThermoData config file adding for engine BC - - if cpacs.tixi.checkElement(ENGINE_TYPE_XPATH): - log.info("adding engine BC to the SU2 config file") - engine_type = get_value(cpacs.tixi, ENGINE_TYPE_XPATH) - log.info(f"engine type {engine_type}") - alt = alt_list[0] - Atm = Atmosphere(alt) - tot_temp_in = Atm.temperature[0] - tot_pressure_in = Atm.pressure[0] - print(tot_pressure_in) - - if engine_type == 0: - log.info("turbojet boundary conditions") - tot_temp_out = get_value(cpacs.tixi, ENGINE_BC + "/temperatureOutlet") - tot_pressure_out = get_value(cpacs.tixi, ENGINE_BC + "/pressureOutlet") - cfg["INLET_TYPE"] = "TOTAL_CONDITIONS" - cfg["MARKER_INLET"] = ( - f"(INLET_ENGINE, {tot_temp_in}, {tot_pressure_in}, {1},{0},{0}, " - f"OUTLET_ENGINE,{tot_temp_out},{tot_pressure_out}, {1},{0},{0})" - ) - - elif engine_type == 1: - log.info("turbofan boundary conditions") - tot_temp_out = get_value(cpacs.tixi, ENGINE_BC + "/temperatureOutlet") - tot_pressure_out = get_value(cpacs.tixi, ENGINE_BC + "/pressureOutlet") - cfg["INLET_TYPE"] = "TOTAL_CONDITIONS" - cfg["MARKER_INLET"] = ( - f"(INLET_ENGINE, {tot_temp_in}, {tot_pressure_in}, {1},{0},{0}, " - f"OUTLET_ENGINE,{tot_temp_out},{tot_pressure_out}, {1},{0},{0})" - ) - - cfg["MARKER_EULER"] = bc_wall_str - farfield_bc = ( - mesh_markers["farfield"] + mesh_markers["engine_intake"] + mesh_markers["engine_exhaust"] - ) - cfg["MARKER_FAR"] = f"( {','.join(farfield_bc)} )" - cfg["MARKER_SYM"] = f"( {','.join(mesh_markers['symmetry'])} )" - cfg["MARKER_PLOTTING"] = bc_wall_str - cfg["MARKER_MONITORING"] = bc_wall_str - cfg["MARKER_MOVING"] = "( NONE )" # TODO: when do we need to define MARKER_MOVING? - cfg["DV_MARKER"] = bc_wall_str - - # Output - cfg["WRT_FORCES_BREAKDOWN"] = "YES" - cfg["BREAKDOWN_FILENAME"] = SU2_FORCES_BREAKDOWN_NAME - cfg["OUTPUT_FILES"] = "(RESTART, PARAVIEW, SURFACE_PARAVIEW)" - cfg["HISTORY_OUTPUT"] = "(INNER_ITER, RMS_RES, AERO_COEFF)" - - # Parameters which will vary for the different cases (alt,mach,aoa,aos) - for case_nb in range(len(alt_list)): - cfg["MESH_FILENAME"] = str(su2_mesh) - - alt = alt_list[case_nb] - mach = mach_list[case_nb] - aoa = aoa_list[case_nb] - aos = aos_list[case_nb] - - Atm = Atmosphere(alt) - - cfg["MACH_NUMBER"] = mach - cfg["AOA"] = aoa - cfg["SIDESLIP_ANGLE"] = aos - cfg["FREESTREAM_PRESSURE"] = Atm.pressure[0] - cfg["FREESTREAM_TEMPERATURE"] = Atm.temperature[0] - cfg["ROTATION_RATE"] = "0.0 0.0 0.0" - - case_dir_name = ( - f"Case{str(case_nb).zfill(2)}_alt{alt}_mach{round(mach, 2)}" - f"_aoa{round(aoa, 1)}_aos{round(aos, 1)}" - ) - - case_dir_path = Path(wkdir, case_dir_name) - if not case_dir_path.exists(): - case_dir_path.mkdir() - - if get_value_or_default(cpacs.tixi, SU2_ACTUATOR_DISK_XPATH, False): - actuator_disk_file = Path(wkdir, ACTUATOR_DISK_FILE_NAME) - add_actuator_disk( - cfg, cpacs, case_dir_path, actuator_disk_file, mesh_markers, alt, mach - ) - - if actuator_disk_file.exists(): - case_actuator_disk_file = Path(case_dir_path, ACTUATOR_DISK_FILE_NAME) - copyfile(actuator_disk_file, case_actuator_disk_file) - - bc_wall_str = ( - "(" - + ",".join( - mesh_markers["wall"] - + mesh_markers["actuator_disk_inlet"] - + mesh_markers["actuator_disk_outlet"] - ) - + ")" - ) - - cfg["MARKER_PLOTTING"] = bc_wall_str - cfg["MARKER_MONITORING"] = bc_wall_str - - config_output_path = Path(case_dir_path, CONFIG_CFD_NAME) - cfg.write_file(config_output_path, overwrite=True) - - if get_value_or_default(cpacs.tixi, SU2_DAMPING_DER_XPATH, False): - rotation_rate = get_value_or_default(cpacs.tixi, SU2_ROTATION_RATE_XPATH, 1.0) - add_damping_derivatives(cfg, wkdir, case_dir_name, rotation_rate) - - # Control surfaces deflections (TODO: create a subfunctions) - if get_value_or_default(cpacs.tixi, SU2_CONTROL_SURF_XPATH, False): - # Get deformed mesh list - if cpacs.tixi.checkElement(SU2_DEF_MESH_XPATH): - su2_def_mesh_list = get_string_vector(cpacs.tixi, SU2_DEF_MESH_XPATH) - else: - log.warning("No SU2 deformed mesh has been found!") - su2_def_mesh_list = [] - - for su2_def_mesh in su2_def_mesh_list: - mesh_path = Path(wkdir, "MESH", su2_def_mesh) - config_dir_path = Path(wkdir, case_dir_name + "_" + su2_def_mesh.split(".")[0]) - config_dir_path.mkdir() - cfg["MESH_FILENAME"] = mesh_path - - cfg.write_file(Path(config_dir_path, CONFIG_CFD_NAME), overwrite=True) - - cpacs.save_cpacs(cpacs_out_path, overwrite=True) - - -# ================================================================================================= -# MAIN -# ================================================================================================= - -if __name__ == "__main__": - log.info("Nothing to execute!") diff --git a/ceasiompy/ThermoData/__specs__.py b/ceasiompy/ThermoData/__specs__.py index 86c68fb89..09a5cfa02 100644 --- a/ceasiompy/ThermoData/__specs__.py +++ b/ceasiompy/ThermoData/__specs__.py @@ -1,8 +1,6 @@ from pathlib import Path from ceasiompy.utils.moduleinterfaces import CPACSInOut from ceasiompy.utils.commonxpath import ( - REF_XPATH, - CLCALC_XPATH, SU2_FIXED_CL_XPATH, SU2_TARGET_CL_XPATH, ENGINE_TYPE_XPATH, diff --git a/ceasiompy/ThermoData/func/run_func.py b/ceasiompy/ThermoData/func/run_func.py index 45bf617bf..0a5aea6b4 100644 --- a/ceasiompy/ThermoData/func/run_func.py +++ b/ceasiompy/ThermoData/func/run_func.py @@ -78,7 +78,7 @@ def thermo_data_run(cpacs_path, cpacs_out_path, wkdir): T_tot_out_array = [] P_tot_out_array = [] - for case_nb in range(len(alt_list)): + for case_nb, alt in enumerate(alt_list): alt = alt_list[case_nb] MN = mach_list[case_nb] case_dir_name = f"Case{str(case_nb).zfill(2)}_alt{alt}_mach{round(MN, 2)}" diff --git a/ceasiompy/ThermoData/func/turbofan_func.py b/ceasiompy/ThermoData/func/turbofan_func.py index 9a24727dc..90fc36fc4 100644 --- a/ceasiompy/ThermoData/func/turbofan_func.py +++ b/ceasiompy/ThermoData/func/turbofan_func.py @@ -291,8 +291,6 @@ def viewer(prob, pt, file=sys.stdout): fs_full_names = [f"{pt}.{fs}" for fs in fs_names] pyc.print_flow_station(prob, fs_full_names, file=file) - import time - prob = om.Problem() prob.model = MPhbtf() diff --git a/ceasiompy/ThermoData/func/turbojet_func.py b/ceasiompy/ThermoData/func/turbojet_func.py index d122f96fb..630cfd343 100644 --- a/ceasiompy/ThermoData/func/turbojet_func.py +++ b/ceasiompy/ThermoData/func/turbojet_func.py @@ -126,8 +126,6 @@ def setup(self): super().setup() - import time - # defining the optimization problem prob = om.Problem() diff --git a/ceasiompy/ThermoData/thermodata.py b/ceasiompy/ThermoData/thermodata.py index 5c624caf6..613cab2e6 100644 --- a/ceasiompy/ThermoData/thermodata.py +++ b/ceasiompy/ThermoData/thermodata.py @@ -27,14 +27,6 @@ get_toolinput_file_path, get_tooloutput_file_path, ) -from ceasiompy.utils.commonxpath import ( - REF_XPATH, - CLCALC_XPATH, - ENGINE_TYPE_XPATH, -) -from ceasiompy.utils.commonnames import ( - ENGINE_BOUNDARY_CONDITIONS, -) from ceasiompy.utils.ceasiompyutils import get_results_directory From 59c640d17e5f1959b350190d8e122fd3d8d3663a Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Wed, 7 Feb 2024 14:48:47 +0100 Subject: [PATCH 14/55] solving Codacy issues --- ceasiompy/ThermoData/func/turbofan_func.py | 10 ++++++---- 1 file changed, 6 insertions(+), 4 deletions(-) diff --git a/ceasiompy/ThermoData/func/turbofan_func.py b/ceasiompy/ThermoData/func/turbofan_func.py index 90fc36fc4..5973e42b0 100644 --- a/ceasiompy/ThermoData/func/turbofan_func.py +++ b/ceasiompy/ThermoData/func/turbofan_func.py @@ -328,11 +328,13 @@ def viewer(prob, pt, file=sys.stdout): viewer_file = open("hbtf_des_view.out", "w") - for PC in [1, 0.9]: - viewer(prob, "DESIGN", file=viewer_file) - prob.run_model() + # for PC in [1, 0.9]: + # viewer(prob, "DESIGN", file=viewer_file) + # prob.run_model() + # print() - print() + viewer(prob, "DESIGN", file=viewer_file) + prob.run_model() # Obtaining variables names From 46472dc558c38f4aa0376d20ec299632bdc5c6c9 Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Wed, 7 Feb 2024 16:40:22 +0100 Subject: [PATCH 15/55] removing complexity from the code --- ceasiompy/ThermoData/func/run_func.py | 160 -------------------------- ceasiompy/ThermoData/thermodata.py | 136 +++++++++++++++++++++- 2 files changed, 134 insertions(+), 162 deletions(-) delete mode 100644 ceasiompy/ThermoData/func/run_func.py diff --git a/ceasiompy/ThermoData/func/run_func.py b/ceasiompy/ThermoData/func/run_func.py deleted file mode 100644 index 0a5aea6b4..000000000 --- a/ceasiompy/ThermoData/func/run_func.py +++ /dev/null @@ -1,160 +0,0 @@ -""" -CEASIOMpy: Conceptual Aircraft Design Software - -Developed by CFS ENGINEERING, 1015 Lausanne, Switzerland - -Function to run the PyCycle code in order to obtain turbojet and turbofan boundary conditions -at given altitude, mach number and net force = thrust of the engine - -Python version: >=3.8 - -| Author: Giacomo Benedetti and Francesco Marcucci -| Creation: 2023-12-12 - -""" - -from pathlib import Path - -from ceasiompy.ThermoData.func.turbofan_func import ( - turbofan_analysis, - write_hbtf_file, -) - -from ceasiompy.ThermoData.func.turbojet_func import ( - turbojet_analysis, - write_turbojet_file, -) - -from ceasiompy.utils.ceasiomlogger import get_logger - -from ceasiompy.utils.commonxpath import ( - ENGINE_TYPE_XPATH, - ENGINE_BC, - RANGE_XPATH, - SU2_AEROMAP_UID_XPATH, -) -from ceasiompy.utils.commonnames import ( - ENGINE_BOUNDARY_CONDITIONS, -) -from cpacspy.cpacsfunctions import ( - get_value_or_default, - add_float_vector, - create_branch, -) -from cpacspy.cpacspy import CPACS - -log = get_logger() - -MODULE_DIR = Path(__file__).parent -MODULE_NAME = MODULE_DIR.name - - -def thermo_data_run(cpacs_path, cpacs_out_path, wkdir): - """Running the PyCycle code by choosing between turbojet or turbofan engine - - Args - cpacs_path (Path): Path to CPACS file - cpacs_out_path (Path):Path to CPACS output file - wkdir (str): Path to the working directory - """ - - if not wkdir.exists(): - raise OSError(f"The working directory : {wkdir} does not exit!") - - cpacs = CPACS(cpacs_path) - tixi = cpacs.tixi - - Fn = get_value_or_default(tixi, RANGE_XPATH + "/NetForce", 2000) - - aeromap_list = cpacs.get_aeromap_uid_list() - - if aeromap_list: - aeromap_default = aeromap_list[0] - log.info(f"The aeromap is {aeromap_default}") - aeromap_uid = get_value_or_default(cpacs.tixi, SU2_AEROMAP_UID_XPATH, aeromap_default) - activate_aeromap = cpacs.get_aeromap_by_uid(aeromap_uid) - alt_list = activate_aeromap.get("altitude").tolist() - mach_list = activate_aeromap.get("machNumber").tolist() - T_tot_out_array = [] - P_tot_out_array = [] - - for case_nb, alt in enumerate(alt_list): - alt = alt_list[case_nb] - MN = mach_list[case_nb] - case_dir_name = f"Case{str(case_nb).zfill(2)}_alt{alt}_mach{round(MN, 2)}" - case_dir_path = Path(wkdir, case_dir_name) - - if not case_dir_path.exists(): - case_dir_path.mkdir() - - EngineBC = Path(case_dir_path, ENGINE_BOUNDARY_CONDITIONS) - - f = open(EngineBC, "w") - - engine_type = get_value_or_default(tixi, ENGINE_TYPE_XPATH, 0) - create_branch(cpacs.tixi, ENGINE_BC) - - if engine_type == 0: - ( - T_tot_out, - V_stat_out, - MN_out, - P_tot_out, - massflow_stat_out, - T_stat_out, - P_stat_out, - ) = turbojet_analysis(alt, MN, Fn) - - T_tot_out_array.append(T_tot_out) - P_tot_out_array.append(P_tot_out) - - f = write_turbojet_file( - file=f, - T_tot_out=T_tot_out, - V_stat_out=V_stat_out, - MN_out=MN_out, - P_tot_out=P_tot_out, - massflow_stat_out=massflow_stat_out, - T_stat_out=T_stat_out, - P_stat_out=P_stat_out, - ) - - else: - - ( - T_tot_out_byp, - V_stat_out_byp, - MN_out_byp, - P_tot_out_byp, - massflow_stat_out_byp, - T_stat_out_byp, - T_tot_out_core, - V_stat_out_core, - MN_out_core, - P_tot_out_core, - massflow_stat_out_core, - T_stat_out_core, - ) = turbofan_analysis(alt, MN, Fn) - - T_tot_out_array.append(T_tot_out_core) - P_tot_out_array.append(P_tot_out_core) - - f = write_hbtf_file( - file=f, - T_tot_out_byp=T_tot_out_byp, - V_stat_out_byp=V_stat_out_byp, - MN_out_byp=MN_out_byp, - P_tot_out_byp=P_tot_out_byp, - massflow_stat_out_byp=massflow_stat_out_byp, - T_stat_out_byp=T_stat_out_byp, - T_tot_out_core=T_tot_out_core, - V_stat_out_core=V_stat_out_core, - MN_out_core=MN_out_core, - P_tot_out_core=P_tot_out_core, - massflow_stat_out_core=massflow_stat_out_core, - T_stat_out_core=T_stat_out_core, - ) - add_float_vector(tixi, ENGINE_BC + "/temperatureOutlet", T_tot_out_array) - add_float_vector(tixi, ENGINE_BC + "/pressureOutlet", P_tot_out_array) - - cpacs.save_cpacs(cpacs_out_path, overwrite=True) diff --git a/ceasiompy/ThermoData/thermodata.py b/ceasiompy/ThermoData/thermodata.py index 613cab2e6..32eff3efc 100644 --- a/ceasiompy/ThermoData/thermodata.py +++ b/ceasiompy/ThermoData/thermodata.py @@ -17,8 +17,14 @@ import shutil from pathlib import Path -from ceasiompy.ThermoData.func.run_func import ( - thermo_data_run, +from ceasiompy.ThermoData.func.turbofan_func import ( + turbofan_analysis, + write_hbtf_file, +) + +from ceasiompy.ThermoData.func.turbojet_func import ( + turbojet_analysis, + write_turbojet_file, ) from ceasiompy.utils.ceasiomlogger import get_logger @@ -28,6 +34,21 @@ get_tooloutput_file_path, ) from ceasiompy.utils.ceasiompyutils import get_results_directory +from ceasiompy.utils.commonxpath import ( + ENGINE_TYPE_XPATH, + ENGINE_BC, + RANGE_XPATH, + SU2_AEROMAP_UID_XPATH, +) +from ceasiompy.utils.commonnames import ( + ENGINE_BOUNDARY_CONDITIONS, +) +from cpacspy.cpacsfunctions import ( + get_value_or_default, + add_float_vector, + create_branch, +) +from cpacspy.cpacspy import CPACS log = get_logger() @@ -46,6 +67,117 @@ # ================================================================================================= +def thermo_data_run(cpacs_path, cpacs_out_path, wkdir): + """Running the PyCycle code by choosing between turbojet or turbofan engine + + Args + cpacs_path (Path): Path to CPACS file + cpacs_out_path (Path):Path to CPACS output file + wkdir (str): Path to the working directory + """ + + if not wkdir.exists(): + raise OSError(f"The working directory : {wkdir} does not exit!") + + cpacs = CPACS(cpacs_path) + tixi = cpacs.tixi + + Fn = get_value_or_default(tixi, RANGE_XPATH + "/NetForce", 2000) + + aeromap_list = cpacs.get_aeromap_uid_list() + + if aeromap_list: + aeromap_default = aeromap_list[0] + log.info(f"The aeromap is {aeromap_default}") + aeromap_uid = get_value_or_default(cpacs.tixi, SU2_AEROMAP_UID_XPATH, aeromap_default) + activate_aeromap = cpacs.get_aeromap_by_uid(aeromap_uid) + alt_list = activate_aeromap.get("altitude").tolist() + mach_list = activate_aeromap.get("machNumber").tolist() + T_tot_out_array = [] + P_tot_out_array = [] + + for case_nb, alt in enumerate(alt_list): + alt = alt_list[case_nb] + MN = mach_list[case_nb] + case_dir_name = f"Case{str(case_nb).zfill(2)}_alt{alt}_mach{round(MN, 2)}" + case_dir_path = Path(wkdir, case_dir_name) + + if not case_dir_path.exists(): + case_dir_path.mkdir() + + EngineBC = Path(case_dir_path, ENGINE_BOUNDARY_CONDITIONS) + + f = open(EngineBC, "w") + + engine_type = get_value_or_default(tixi, ENGINE_TYPE_XPATH, 0) + create_branch(cpacs.tixi, ENGINE_BC) + + if engine_type == 0: + ( + T_tot_out, + V_stat_out, + MN_out, + P_tot_out, + massflow_stat_out, + T_stat_out, + P_stat_out, + ) = turbojet_analysis(alt, MN, Fn) + + T_tot_out_array.append(T_tot_out) + P_tot_out_array.append(P_tot_out) + + f = write_turbojet_file( + file=f, + T_tot_out=T_tot_out, + V_stat_out=V_stat_out, + MN_out=MN_out, + P_tot_out=P_tot_out, + massflow_stat_out=massflow_stat_out, + T_stat_out=T_stat_out, + P_stat_out=P_stat_out, + ) + + else: + + ( + T_tot_out_byp, + V_stat_out_byp, + MN_out_byp, + P_tot_out_byp, + massflow_stat_out_byp, + T_stat_out_byp, + T_tot_out_core, + V_stat_out_core, + MN_out_core, + P_tot_out_core, + massflow_stat_out_core, + T_stat_out_core, + ) = turbofan_analysis(alt, MN, Fn) + + T_tot_out_array.append(T_tot_out_core) + P_tot_out_array.append(P_tot_out_core) + + f = write_hbtf_file( + file=f, + T_tot_out_byp=T_tot_out_byp, + V_stat_out_byp=V_stat_out_byp, + MN_out_byp=MN_out_byp, + P_tot_out_byp=P_tot_out_byp, + massflow_stat_out_byp=massflow_stat_out_byp, + T_stat_out_byp=T_stat_out_byp, + T_tot_out_core=T_tot_out_core, + V_stat_out_core=V_stat_out_core, + MN_out_core=MN_out_core, + P_tot_out_core=P_tot_out_core, + massflow_stat_out_core=massflow_stat_out_core, + T_stat_out_core=T_stat_out_core, + ) + add_float_vector(tixi, ENGINE_BC + "/temperatureOutlet", T_tot_out_array) + add_float_vector(tixi, ENGINE_BC + "/pressureOutlet", P_tot_out_array) + + cpacs.save_cpacs(cpacs_out_path, overwrite=True) + + # ================================================================================================= # MAIN # ================================================================================================= From 1b96559d6fe46219411acbb1f4f1d29a11855609 Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Thu, 8 Feb 2024 10:05:04 +0100 Subject: [PATCH 16/55] start adding rans cfg file --- .../SU2Run/files/config_template_rans.cfg | 198 ++++++ ceasiompy/SU2Run/func/su2configrans.py | 564 ++++++++++++++++++ ceasiompy/SU2Run/func/su2utils.py | 8 + ceasiompy/SU2Run/su2run.py | 3 +- 4 files changed, 772 insertions(+), 1 deletion(-) create mode 100644 ceasiompy/SU2Run/files/config_template_rans.cfg create mode 100644 ceasiompy/SU2Run/func/su2configrans.py diff --git a/ceasiompy/SU2Run/files/config_template_rans.cfg b/ceasiompy/SU2Run/files/config_template_rans.cfg new file mode 100644 index 000000000..3da3b4d9e --- /dev/null +++ b/ceasiompy/SU2Run/files/config_template_rans.cfg @@ -0,0 +1,198 @@ +%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% +% % +% SU2 configuration file % +% Case description: VKI turbine % +% Author: Francisco Palacios, Thomas D. Economon % +% Institution: Stanford University % +% Date: Feb 18th, 2013 % +% File Version 8.0.0 "Harrier" % +% % +%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% + +% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------% +% +SOLVER= RANS +% +KIND_TURB_MODEL= SA +% +MATH_PROBLEM= DIRECT +% +RESTART_SOL= NO +% +SYSTEM_MEASUREMENTS= SI + +% -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------% +% +MACH_NUMBER= 0.3 +% +AOA= 0.0 +% +FREESTREAM_PRESSURE= 1.013E5 +% +FREESTREAM_OPTION= DENSITY_FS +% +FREESTREAM_DENSITY = 1.255 +% +FREESTREAM_TEMPERATURE =288.15 +% +REYNOLDS_NUMBER= 4E6 +% +REYNOLDS_LENGTH= 1.0 + +% ---------------------- REFERENCE VALUE DEFINITION ---------------------------% +% +REF_ORIGIN_MOMENT_X = 0.00 +% +REF_ORIGIN_MOMENT_Y = 0.00 +% +REF_ORIGIN_MOMENT_Z = 0.00 +% +REF_LENGTH= 45.0 +% +REF_AREA= 1 +% Compressible flow non-dimensionalization (DIMENSIONAL, FREESTREAM_PRESS_EQ_ONE, +% FREESTREAM_VEL_EQ_MACH, FREESTREAM_VEL_EQ_ONE) +REF_DIMENSIONALIZATION= FREESTREAM_PRESS_EQ_ONE +% +% ----------------------- BOUNDARY CONDITION DEFINITION -----------------------% +% +MARKER_HEATFLUX = (S4CreatedbyGmsh, 0.0) +% +MARKER_FAR= (S3Farfield) +% +%MARKER_SYM =() +% +% ------------------------ SURFACES IDENTIFICATION ----------------------------% +% +% Marker(s) of the surface to be plotted or designed +MARKER_PLOTTING= (S4CreatedbyGmsh) +% +% Marker(s) of the surface where the functional (Cd, Cl, etc.) will be evaluated +MARKER_MONITORING= (S4CreatedbyGmsh) + +% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------% +% +NUM_METHOD_GRAD= GREEN_GAUSS +% +CFL_NUMBER= 20 +% +CFL_ADAPT= NO +% +CFL_ADAPT_PARAM= ( 0.5, 1, 1.0, 100.0 ) +% +ITER = 10000 + +% Objective function in gradient evaluation (DRAG, LIFT, SIDEFORCE, MOMENT_X, +% MOMENT_Y, MOMENT_Z, EFFICIENCY, BUFFET, +% EQUIVALENT_AREA, NEARFIELD_PRESSURE, +% FORCE_X, FORCE_Y, FORCE_Z, THRUST, +% TORQUE, TOTAL_HEATFLUX, +% MAXIMUM_HEATFLUX, INVERSE_DESIGN_PRESSURE, +% INVERSE_DESIGN_HEATFLUX, SURFACE_TOTAL_PRESSURE, +% SURFACE_MASSFLOW, SURFACE_STATIC_PRESSURE, SURFACE_MACH) +% For a weighted sum of objectives: separate by commas, add OBJECTIVE_WEIGHT and MARKER_MONITORING in matching order. +OBJECTIVE_FUNCTION= DRAG + +% ------------------------ LINEAR SOLVER DEFINITION ---------------------------% +% Linear solver or smoother for implicit formulations: +% BCGSTAB, FGMRES, RESTARTED_FGMRES, CONJUGATE_GRADIENT (self-adjoint problems only), SMOOTHER. +LINEAR_SOLVER= FGMRES +% +% Preconditioner of the Krylov linear solver or type of smoother (ILU, LU_SGS, LINELET, JACOBI) +LINEAR_SOLVER_PREC= ILU +% +% Minimum error of the linear solver for implicit formulations +LINEAR_SOLVER_ERROR= 1E-12 +% +% Max number of iterations of the linear solver for the implicit formulation +LINEAR_SOLVER_ITER= 3 +% +% Number of elements to apply the criteria +CONV_CAUCHY_ELEMS= 1000 +% +% Epsilon to control the series convergence +CONV_CAUCHY_EPS= 1E-10 +% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------% +% Convective numerical method (JST, LAX-FRIEDRICH, CUSP, ROE, AUSM, AUSMPLUSUP, +% AUSMPLUSUP2, HLLC, TURKEL_PREC, MSW, FDS, SLAU, SLAU2) +CONV_NUM_METHOD_FLOW= JST +% +% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT, EULER_EXPLICIT) +TIME_DISCRE_FLOW= EULER_IMPLICIT +% +% -------------------- TURBULENT NUMERICAL METHOD DEFINITION ------------------% +% Convective numerical method (SCALAR_UPWIND) +CONV_NUM_METHOD_TURB= SCALAR_UPWIND +% +% Monotonic Upwind Scheme for Conservation Laws (TVD) in the turbulence equations. +% Required for 2nd order upwind schemes (NO, YES) +MUSCL_TURB= NO +% +% Slope limiter (NONE, VENKATAKRISHNAN, VENKATAKRISHNAN_WANG, +% BARTH_JESPERSEN, VAN_ALBADA_EDGE) +SLOPE_LIMITER_TURB= VENKATAKRISHNAN +% +% Time discretization (EULER_IMPLICIT) +TIME_DISCRE_TURB= EULER_IMPLICIT +% -------------------------- MULTIGRID PARAMETERS -----------------------------% +% +% Multi-Grid Levels (0 = no multi-grid) +MGLEVEL = 3 +% +% Multi-grid cycle (V_CYCLE, W_CYCLE, FULLMG_CYCLE) +MGCYCLE = W_CYCLE +% +% Multi-Grid PreSmoothing Level +MG_PRE_SMOOTH = ( 1.0, 2.0, 3.0, 3.0 ) +% +% Multi-Grid PostSmoothing Level +MG_POST_SMOOTH = ( 0.0, 0.0, 0.0, 0.0 ) +% +% Jacobi implicit smoothing of the correction +MG_CORRECTION_SMOOTH = ( 0.0, 0.0, 0.0, 0.0 ) +% +% Damping factor for the residual restriction +MG_DAMP_RESTRICTION = 0.9 +% +% Damping factor for the correction prolongation +MG_DAMP_PROLONGATION = 0.9 +% --------------------------- CONVERGENCE PARAMETERS --------------------------% +% +% Min value of the residual (log10 of the residual) +CONV_RESIDUAL_MINVAL= -12 +% +% Start convergence criteria at iteration number +CONV_STARTITER= 10 +% + +% ------------------------- INPUT/OUTPUT INFORMATION --------------------------% +% +MESH_FILENAME= labair_penta.cgns +% +MESH_FORMAT= CGNS +% +MESH_OUT_FILENAME= mesh_out.su2 +% +SOLUTION_FILENAME= solution_flow.dat +% +HISTORY_OUTPUT = (INNER_ITER, RMS_RES, AERO_COEFF) +% +TABULAR_FORMAT= CSV +% +CONV_FILENAME= history +% +RESTART_FILENAME= restart_flow.dat +% +RESTART_ADJ_FILENAME= restart_adj.dat +% +VOLUME_FILENAME= flow +% +SURFACE_FILENAME= surface_flow_mesh +% +OUTPUT_WRT_FREQ= 100 +% +BREAKDOWN_FILENAME = forces_breakdown_def.dat +% +WRT_FORCES_BREAKDOWN = YES +% +SCREEN_OUTPUT= (INNER_ITER, RMS_DENSITY, RMS_ENERGY, LIFT, DRAG) \ No newline at end of file diff --git a/ceasiompy/SU2Run/func/su2configrans.py b/ceasiompy/SU2Run/func/su2configrans.py new file mode 100644 index 000000000..52f15ea22 --- /dev/null +++ b/ceasiompy/SU2Run/func/su2configrans.py @@ -0,0 +1,564 @@ +""" +CEASIOMpy: Conceptual Aircraft Design Software + +Developed by CFS ENGINEERING, 1015 Lausanne, Switzerland + +Function generate or modify SU2 configuration files + +Python version: >=3.8 + +| Author: Aidan Jungo +| Creation: 2020-02-24 + +TODO: + + * add and test control surface functions + +""" + +# ================================================================================================= +# IMPORTS +# ================================================================================================= + +from pathlib import Path +from shutil import copyfile + +from ambiance import Atmosphere +from ceasiompy.SU2Run.func.su2actuatordiskfile import ( + get_advanced_ratio, + get_radial_stations, + save_plots, + thrust_calculator, + write_actuator_disk_data, + write_header, +) +from ceasiompy.SU2Run.func.su2utils import get_mesh_markers, get_cgns_config_template +from ceasiompy.utils.ceasiomlogger import get_logger +from ceasiompy.utils.commonnames import ( + ACTUATOR_DISK_FILE_NAME, + ACTUATOR_DISK_INLET_SUFFIX, + ACTUATOR_DISK_OUTLET_SUFFIX, + CONFIG_CFD_NAME, + SU2_FORCES_BREAKDOWN_NAME, +) +from ceasiompy.utils.commonxpath import ( + GMSH_SYMMETRY_XPATH, + PROP_XPATH, + RANGE_XPATH, + SU2_ACTUATOR_DISK_XPATH, + SU2_AEROMAP_UID_XPATH, + SU2_BC_FARFIELD_XPATH, + SU2_BC_WALL_XPATH, + SU2_CFL_NB_XPATH, + SU2_CFL_ADAPT_XPATH, + SU2_CFL_ADAPT_PARAM_DOWN_XPATH, + SU2_CFL_ADAPT_PARAM_UP_XPATH, + SU2_CFL_MAX_XPATH, + SU2_CFL_MIN_XPATH, + SU2_CONTROL_SURF_XPATH, + SU2_DAMPING_DER_XPATH, + SU2_DEF_MESH_XPATH, + SU2_FIXED_CL_XPATH, + SU2_MAX_ITER_XPATH, + SU2_MG_LEVEL_XPATH, + SU2_ROTATION_RATE_XPATH, + SU2_TARGET_CL_XPATH, + SU2MESH_XPATH, + ENGINE_TYPE_XPATH, + ENGINE_BC, +) +from ceasiompy.utils.configfiles import ConfigFile +from cpacspy.cpacsfunctions import ( + create_branch, + get_string_vector, + get_value, + get_value_or_default, +) +from cpacspy.cpacspy import CPACS + +log = get_logger() + +MODULE_DIR = Path(__file__).parent + + +# ================================================================================================= +# CLASSES +# ================================================================================================= + + +# ================================================================================================= +# FUNCTIONS +# ================================================================================================= + + +def add_damping_derivatives(cfg, wkdir, case_dir_name, rotation_rate): + """Add damping derivatives parameter to the config file and save them to their respective + directory. + + Args: + cfg (ConfigFile): ConfigFile object. + wkdir (Path): Path to the working directory + case_dir_name (str): Name of the case directory + rotation_rate (float): Rotation rate that will be impose to calculate damping derivatives + """ + + cfg["GRID_MOVEMENT"] = "ROTATING_FRAME" + + cfg["ROTATION_RATE"] = f"{rotation_rate} 0.0 0.0" + case_dir = Path(wkdir, f"{case_dir_name}_dp") + case_dir.mkdir() + cfg.write_file(Path(case_dir, CONFIG_CFD_NAME), overwrite=True) + + cfg["ROTATION_RATE"] = f"0.0 {rotation_rate} 0.0" + case_dir = Path(wkdir, f"{case_dir_name}_dq") + case_dir.mkdir() + cfg.write_file(Path(case_dir, CONFIG_CFD_NAME), overwrite=True) + + cfg["ROTATION_RATE"] = f"0.0 0.0 {rotation_rate}" + case_dir = Path(wkdir, f"{case_dir_name}_dr") + case_dir.mkdir() + cfg.write_file(Path(case_dir, CONFIG_CFD_NAME), overwrite=True) + + log.info("Damping derivatives cases directories has been created.") + + +def add_actuator_disk(cfg, cpacs, case_dir_path, actuator_disk_file, mesh_markers, alt, mach): + """Add actuator disk parameter to the config file. + + Args: + cfg (ConfigFile): ConfigFile object. + cpacs (CPACS): CPACS object from cpacspy library + case_dir_path (Path): Path object to the current case directory + actuator_disk_file (Path): Path to the actuator disk file + mesh_markers (dict): Dictionary containing all the mesh markers + + Returns: + cfg (ConfigFile): ConfigFile object. + """ + + ad_inlet_marker = sorted(mesh_markers["actuator_disk_inlet"]) + ad_outlet_marker = sorted(mesh_markers["actuator_disk_outlet"]) + + if "None" in ad_inlet_marker or "None" in ad_outlet_marker: + return + + if len(ad_inlet_marker) != len(ad_outlet_marker): + raise ValueError( + "The number of inlet and outlet markers of the actuator disk must be the same." + ) + + # Get rotorcraft configuration (propeller) + try: + rotorcraft_config = cpacs.rotorcraft.configuration + except AttributeError: + raise ValueError( + "The actuator disk is defined but no rotorcraft configuration is defined in " + "the CPACS file." + ) + + rotor_uid_pos = {} + for i in range(1, rotorcraft_config.get_rotor_count() + 1): + rotor = rotorcraft_config.get_rotor(i) + + rotor_uid = rotor.get_uid() + pos_x = rotor.get_translation().x + pos_y = rotor.get_translation().y + pos_z = rotor.get_translation().z + radius = rotor.get_radius() + hub_radius = 0.0 # TODO: get correctly from CPACS + + rotor_xpath = cpacs.tixi.uIDGetXPath(rotor_uid) + + number_of_blades_xpath = ( + rotor_xpath + "/rotorHub/rotorBladeAttachments/rotorBladeAttachment/numberOfBlades" + ) + number_of_blades = get_value_or_default(cpacs.tixi, number_of_blades_xpath, 3) + + # TODO: this is the nominal speed, how to get a speed which correspond to each flight cond. + rotational_velocity_xpath = rotor_xpath + "/nominalRotationsPerMinute" + rotational_velocity = ( + get_value_or_default(cpacs.tixi, rotational_velocity_xpath, 3000) / 60.0 + ) + + rotor_uid_pos[rotor_uid] = ( + pos_x, + pos_y, + pos_z, + radius, + hub_radius, + number_of_blades, + rotational_velocity, + ) + + cfg["ACTDISK_DOUBLE_SURFACE"] = "YES" + cfg["ACTDISK_TYPE"] = "VARIABLE_LOAD" + cfg["ACTDISK_FILENAME"] = ACTUATOR_DISK_FILE_NAME + cfg["MGLEVEL"] = 0 # Calculation diverges if multigrid is used with a disk actuator + + actdisk_markers = [] + + f = open(actuator_disk_file, "w") + f = write_header(f) + + for maker_inlet, marker_outlet in zip(ad_inlet_marker, ad_outlet_marker): + inlet_uid = maker_inlet.split(ACTUATOR_DISK_INLET_SUFFIX)[0] + outlet_uid = marker_outlet.split(ACTUATOR_DISK_OUTLET_SUFFIX)[0] + + if inlet_uid != outlet_uid: + raise ValueError("The inlet and outlet markers of the actuator disk must be the same.") + + if "_mirrored" in maker_inlet: + uid = inlet_uid.split("_mirrored")[0] + sym = -1 + else: + uid = inlet_uid + sym = 1 + + center = [] + center.append(round(rotor_uid_pos[uid][0], 5)) + center.append(round(sym * rotor_uid_pos[uid][1], 5)) + center.append(round(rotor_uid_pos[uid][2], 5)) + + axis = (1.0, 0.0, 0.0) # TODO: get the axis by applying the rotation matrix + radius = round(rotor_uid_pos[uid][3], 5) + hub_radius = round(rotor_uid_pos[uid][4], 5) + number_of_blades = round(rotor_uid_pos[uid][5], 5) + rotational_velocity = round(rotor_uid_pos[uid][6], 5) + + actdisk_markers.append(maker_inlet) + actdisk_markers.append(marker_outlet) + actdisk_markers.append(str(center[0])) + actdisk_markers.append(str(center[1])) + actdisk_markers.append(str(center[2])) + actdisk_markers.append(str(center[0])) + actdisk_markers.append(str(center[1])) + actdisk_markers.append(str(center[2])) + + Atm = Atmosphere(alt) + free_stream_velocity = mach * Atm.speed_of_sound[0] + + radial_stations = get_radial_stations(radius, hub_radius) + advanced_ratio = get_advanced_ratio(free_stream_velocity, rotational_velocity, radius) + + prandtl_correction_xpath = PROP_XPATH + "/propeller/blade/loss" + prandtl_correction = get_value_or_default(cpacs.tixi, prandtl_correction_xpath, True) + + thrust_xpath = PROP_XPATH + "/propeller/thrust" + thrust = get_value_or_default(cpacs.tixi, thrust_xpath, 3000) + total_thrust_coefficient = float( + thrust / (Atm.density * rotational_velocity**2 * (radius * 2) ** 4) + ) + + ( + radial_thrust_coefs, + radial_power_coefs, + non_dimensional_radius, + optimal_axial_interference_factor, + optimal_rotational_interference_factor, + prandtl_correction_values, + ) = thrust_calculator( + radial_stations, + total_thrust_coefficient, + radius, + free_stream_velocity, + prandtl_correction, + number_of_blades, + rotational_velocity, + ) + + save_plots( + radial_stations, + radial_thrust_coefs, + radial_power_coefs, + non_dimensional_radius, + optimal_axial_interference_factor, + optimal_rotational_interference_factor, + prandtl_correction_values, + case_dir_path, + inlet_uid, + ) + + f = write_actuator_disk_data( + file=f, + inlet_marker=maker_inlet, + outlet_marker=marker_outlet, + center=center, + axis=axis, + radius=radius, + advanced_ratio=advanced_ratio, + radial_stations=radial_stations, + radial_thrust_coefs=radial_thrust_coefs, + radial_power_coefs=radial_power_coefs, + ) + + cfg["MARKER_ACTDISK"] = " (" + ", ".join(actdisk_markers) + " )" + + f.close() + + +def add_thermodata(cfg, cpacs, alt, case_nb, alt_list): + + if cpacs.tixi.checkElement(ENGINE_TYPE_XPATH): + log.info("adding engine BC to the SU2 config file") + engine_type = get_value(cpacs.tixi, ENGINE_TYPE_XPATH) + log.info(f"engine type {engine_type}") + alt = alt_list[case_nb] + Atm = Atmosphere(alt) + tot_temp_in = Atm.temperature[0] + tot_pressure_in = Atm.pressure[0] + if len(alt_list) > 1: + tot_temp_out = get_value(cpacs.tixi, ENGINE_BC + "/temperatureOutlet").split(";") + tot_pressure_out = get_value(cpacs.tixi, ENGINE_BC + "/pressureOutlet").split(";") + tot_temp_out = tot_temp_out[case_nb] + tot_pressure_out = tot_pressure_out[case_nb] + else: + tot_temp_out = get_value(cpacs.tixi, ENGINE_BC + "/temperatureOutlet") + tot_pressure_out = get_value(cpacs.tixi, ENGINE_BC + "/pressureOutlet") + cfg["INLET_TYPE"] = "TOTAL_CONDITIONS" + cfg["MARKER_INLET"] = ( + f"(INLET_ENGINE, {tot_temp_in}, {tot_pressure_in}, {1},{0},{0}, " + f"OUTLET_ENGINE,{tot_temp_out},{tot_pressure_out}, {1},{0},{0})" + ) + + +def generate_su2_cfd_config_rans(cpacs_path, cpacs_out_path, wkdir): + """Function to create SU2 config file. + + Function 'generate_su2_cfd_config' reads data in the CPACS file and generate configuration + files for one or multiple flight conditions (alt,mach,aoa,aos) + + Source: + * SU2 config template: https://github.com/su2code/SU2/blob/master/config_template.cfg + + Args: + cpacs_path (Path): Path to CPACS file + cpacs_out_path (Path):Path to CPACS output file + wkdir (Path): Path to the working directory + + """ + + cpacs = CPACS(cpacs_path) + + # creare delle nuove xpath per la mesh cgns + + cgns_mesh = Path(get_value(cpacs.tixi, SU2MESH_XPATH)) + if not cgns_mesh.is_file(): + raise FileNotFoundError(f"CGNS mesh file {cgns_mesh} not found") + + mesh_markers = get_mesh_markers(cgns_mesh) + + create_branch(cpacs.tixi, SU2_BC_WALL_XPATH) + bc_wall_str = ";".join(mesh_markers["wall"]) + cpacs.tixi.updateTextElement(SU2_BC_WALL_XPATH, bc_wall_str) + + create_branch(cpacs.tixi, SU2_BC_FARFIELD_XPATH) + bc_farfiled_str = ";".join(mesh_markers["engine_intake"] + mesh_markers["engine_exhaust"]) + cpacs.tixi.updateTextElement(SU2_BC_FARFIELD_XPATH, bc_farfiled_str) + + create_branch(cpacs.tixi, SU2_ACTUATOR_DISK_XPATH) + bc_actuator_disk_str = ";".join( + mesh_markers["actuator_disk_inlet"] + mesh_markers["actuator_disk_outlet"] + ) + cpacs.tixi.updateTextElement(SU2_ACTUATOR_DISK_XPATH, bc_actuator_disk_str) + + fixed_cl = get_value_or_default(cpacs.tixi, SU2_FIXED_CL_XPATH, "NO") + target_cl = get_value_or_default(cpacs.tixi, SU2_TARGET_CL_XPATH, 1.0) + + if fixed_cl == "NO": + # Get the first aeroMap as default one or create automatically one + aeromap_list = cpacs.get_aeromap_uid_list() + + if aeromap_list: + aeromap_default = aeromap_list[0] + log.info(f"The aeromap is {aeromap_default}") + + aeromap_uid = get_value_or_default(cpacs.tixi, SU2_AEROMAP_UID_XPATH, aeromap_default) + + activate_aeromap = cpacs.get_aeromap_by_uid(aeromap_uid) + alt_list = activate_aeromap.get("altitude").tolist() + mach_list = activate_aeromap.get("machNumber").tolist() + aoa_list = activate_aeromap.get("angleOfAttack").tolist() + aos_list = activate_aeromap.get("angleOfSideslip").tolist() + + else: + default_aeromap = cpacs.create_aeromap("DefaultAeromap") + default_aeromap.description = "AeroMap created automatically" + + mach = get_value_or_default(cpacs.tixi, RANGE_XPATH + "/cruiseMach", 0.3) + alt = get_value_or_default(cpacs.tixi, RANGE_XPATH + "/cruiseAltitude", 10000) + + default_aeromap.add_row(alt=alt, mach=mach, aos=0.0, aoa=0.0) + default_aeromap.save() + + alt_list = [alt] + mach_list = [mach] + aoa_list = [0.0] + aos_list = [0.0] + + aeromap_uid = get_value_or_default(cpacs.tixi, SU2_AEROMAP_UID_XPATH, "DefaultAeromap") + log.info(f"{aeromap_uid} has been created") + + else: # if fixed_cl == 'YES': + log.info("Configuration file for fixed CL calculation will be created.") + + fixed_cl_aeromap = cpacs.create_aeromap("aeroMap_fixedCL_SU2") + fixed_cl_aeromap.description = f"AeroMap created for SU2 fixed CL value of {target_cl}" + + mach = get_value_or_default(cpacs.tixi, RANGE_XPATH + "/cruiseMach", 0.78) + alt = get_value_or_default(cpacs.tixi, RANGE_XPATH + "/cruiseAltitude", 12000) + + fixed_cl_aeromap.add_row(alt=alt, mach=mach, aos=0.0, aoa=0.0) + fixed_cl_aeromap.save() + + alt_list = [alt] + mach_list = [mach] + aoa_list = [0.0] + aos_list = [0.0] + + cfg = ConfigFile(get_cgns_config_template()) + + # Check if symmetry plane is defined (Default: False) + sym_factor = 1.0 + if get_value_or_default(cpacs.tixi, GMSH_SYMMETRY_XPATH, False): + log.info("Symmetry plane is defined. The reference area will be divided by 2.") + sym_factor = 2.0 + + # General parameters + cfg["RESTART_SOL"] = "NO" + cfg["REF_LENGTH"] = cpacs.aircraft.ref_length + cfg["REF_AREA"] = cpacs.aircraft.ref_area / sym_factor + cfg["REF_ORIGIN_MOMENT_X"] = cpacs.aircraft.ref_point_x + cfg["REF_ORIGIN_MOMENT_Y"] = cpacs.aircraft.ref_point_y + cfg["REF_ORIGIN_MOMENT_Z"] = cpacs.aircraft.ref_point_z + + # Settings + + cfl_down = get_value_or_default(cpacs.tixi, SU2_CFL_ADAPT_PARAM_DOWN_XPATH, 0.5) + cfl_up = get_value_or_default(cpacs.tixi, SU2_CFL_ADAPT_PARAM_UP_XPATH, 1.5) + cfl_min = get_value_or_default(cpacs.tixi, SU2_CFL_MIN_XPATH, 0.5) + cfl_max = get_value_or_default(cpacs.tixi, SU2_CFL_MAX_XPATH, 100) + + if get_value_or_default(cpacs.tixi, SU2_CFL_ADAPT_XPATH, True): + cfg["CFL_ADAPT"] = "YES" + + else: + cfg["CFL_ADAPT"] = "NO" + + cfg["INNER_ITER"] = int(get_value_or_default(cpacs.tixi, SU2_MAX_ITER_XPATH, 200)) + cfg["CFL_NUMBER"] = get_value_or_default(cpacs.tixi, SU2_CFL_NB_XPATH, 1.0) + cfg["CFL_ADAPT_PARAM"] = f"( {cfl_down}, {cfl_up}, {cfl_min}, {cfl_max} )" + cfg["MGLEVEL"] = int(get_value_or_default(cpacs.tixi, SU2_MG_LEVEL_XPATH, 3)) + + # Fixed CL mode (AOA will not be taken into account) + cfg["FIXED_CL_MODE"] = fixed_cl + cfg["TARGET_CL"] = target_cl + cfg["DCL_DALPHA"] = "0.1" + cfg["UPDATE_AOA_ITER_LIMIT"] = "50" + cfg["ITER_DCL_DALPHA"] = "80" + + # Mesh Marker + bc_wall_str = f"( {','.join(mesh_markers['wall'])} )" + + cfg["MARKER_EULER"] = bc_wall_str + farfield_bc = ( + mesh_markers["farfield"] + mesh_markers["engine_intake"] + mesh_markers["engine_exhaust"] + ) + cfg["MARKER_FAR"] = f"( {','.join(farfield_bc)} )" + cfg["MARKER_SYM"] = f"( {','.join(mesh_markers['symmetry'])} )" + cfg["MARKER_PLOTTING"] = bc_wall_str + cfg["MARKER_MONITORING"] = bc_wall_str + cfg["MARKER_MOVING"] = "( NONE )" # TODO: when do we need to define MARKER_MOVING? + cfg["DV_MARKER"] = bc_wall_str + + # Output + cfg["WRT_FORCES_BREAKDOWN"] = "YES" + cfg["BREAKDOWN_FILENAME"] = SU2_FORCES_BREAKDOWN_NAME + cfg["OUTPUT_FILES"] = "(RESTART, PARAVIEW, SURFACE_PARAVIEW)" + cfg["HISTORY_OUTPUT"] = "(INNER_ITER, RMS_RES, AERO_COEFF)" + + # Parameters which will vary for the different cases (alt,mach,aoa,aos) + + for case_nb in range(len(alt_list)): + cfg["MESH_FILENAME"] = str(cgns_mesh) + + alt = alt_list[case_nb] + mach = mach_list[case_nb] + aoa = aoa_list[case_nb] + aos = aos_list[case_nb] + + Atm = Atmosphere(alt) + + cfg["MACH_NUMBER"] = mach + cfg["AOA"] = aoa + cfg["SIDESLIP_ANGLE"] = aos + cfg["FREESTREAM_PRESSURE"] = Atm.pressure[0] + cfg["FREESTREAM_TEMPERATURE"] = Atm.temperature[0] + cfg["ROTATION_RATE"] = "0.0 0.0 0.0" + + case_dir_name = ( + f"Case{str(case_nb).zfill(2)}_alt{alt}_mach{round(mach, 2)}" + f"_aoa{round(aoa, 1)}_aos{round(aos, 1)}" + ) + + add_thermodata(cfg, cpacs, alt, case_nb, alt_list) + + case_dir_path = Path(wkdir, case_dir_name) + if not case_dir_path.exists(): + case_dir_path.mkdir() + + if get_value_or_default(cpacs.tixi, SU2_ACTUATOR_DISK_XPATH, False): + actuator_disk_file = Path(wkdir, ACTUATOR_DISK_FILE_NAME) + add_actuator_disk( + cfg, cpacs, case_dir_path, actuator_disk_file, mesh_markers, alt, mach + ) + + if actuator_disk_file.exists(): + case_actuator_disk_file = Path(case_dir_path, ACTUATOR_DISK_FILE_NAME) + copyfile(actuator_disk_file, case_actuator_disk_file) + + bc_wall_str = ( + "(" + + ",".join( + mesh_markers["wall"] + + mesh_markers["actuator_disk_inlet"] + + mesh_markers["actuator_disk_outlet"] + ) + + ")" + ) + + cfg["MARKER_PLOTTING"] = bc_wall_str + cfg["MARKER_MONITORING"] = bc_wall_str + + config_output_path = Path(case_dir_path, CONFIG_CFD_NAME) + cfg.write_file(config_output_path, overwrite=True) + + if get_value_or_default(cpacs.tixi, SU2_DAMPING_DER_XPATH, False): + rotation_rate = get_value_or_default(cpacs.tixi, SU2_ROTATION_RATE_XPATH, 1.0) + add_damping_derivatives(cfg, wkdir, case_dir_name, rotation_rate) + + # Control surfaces deflections (TODO: create a subfunctions) + if get_value_or_default(cpacs.tixi, SU2_CONTROL_SURF_XPATH, False): + # Get deformed mesh list + if cpacs.tixi.checkElement(SU2_DEF_MESH_XPATH): + su2_def_mesh_list = get_string_vector(cpacs.tixi, SU2_DEF_MESH_XPATH) + else: + log.warning("No SU2 deformed mesh has been found!") + su2_def_mesh_list = [] + + for su2_def_mesh in su2_def_mesh_list: + mesh_path = Path(wkdir, "MESH", su2_def_mesh) + config_dir_path = Path(wkdir, case_dir_name + "_" + su2_def_mesh.split(".")[0]) + config_dir_path.mkdir() + cfg["MESH_FILENAME"] = mesh_path + + cfg.write_file(Path(config_dir_path, CONFIG_CFD_NAME), overwrite=True) + + cpacs.save_cpacs(cpacs_out_path, overwrite=True) + + +# ================================================================================================= +# MAIN +# ================================================================================================= + +if __name__ == "__main__": + log.info("Nothing to execute!") diff --git a/ceasiompy/SU2Run/func/su2utils.py b/ceasiompy/SU2Run/func/su2utils.py index ab08a43ef..96878d67f 100644 --- a/ceasiompy/SU2Run/func/su2utils.py +++ b/ceasiompy/SU2Run/func/su2utils.py @@ -170,6 +170,14 @@ def get_su2_config_template(): return su2_config_template_path +def get_cgns_config_template(): + + su2_dir = get_module_path("SU2Run") + su2_config_template_path_rans = Path(su2_dir, "files", f"config_template_rans.cfg") + + return su2_config_template_path_rans + + def get_su2_aerocoefs(force_file): """Get aerodynamic coefficients and velocity from SU2 forces file (forces_breakdown.dat) diff --git a/ceasiompy/SU2Run/su2run.py b/ceasiompy/SU2Run/su2run.py index 4b103b22c..46971f117 100644 --- a/ceasiompy/SU2Run/su2run.py +++ b/ceasiompy/SU2Run/su2run.py @@ -26,6 +26,7 @@ from pathlib import Path from ceasiompy.SU2Run.func.su2config import generate_su2_cfd_config +from ceasiompy.SU2Run.func.su2configrans import generate_su2_cfd_config_rans from ceasiompy.SU2Run.func.su2results import get_su2_results from ceasiompy.utils.ceasiomlogger import get_logger from ceasiompy.utils.ceasiompyutils import ( @@ -114,7 +115,7 @@ def main(cpacs_path, cpacs_out_path): # Temporary CPACS to be stored after "generate_su2_cfd_config" cpacs_tmp_cfg = Path(cpacs_out_path.parent, "ConfigTMP.xml") - generate_su2_cfd_config(cpacs_path, cpacs_tmp_cfg, results_dir) + generate_su2_cfd_config_rans(cpacs_path, cpacs_tmp_cfg, results_dir) run_SU2_multi(results_dir, nb_proc) get_su2_results(cpacs_tmp_cfg, cpacs_out_path, results_dir) From ef7afb1823bf6dcd7aa088ee658729a65a65f47b Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Thu, 8 Feb 2024 10:50:08 +0100 Subject: [PATCH 17/55] working on the rans config file --- ceasiompy/SU2Run/files/config_template_rans.cfg | 8 ++++---- ceasiompy/SU2Run/func/su2configrans.py | 10 +++++----- 2 files changed, 9 insertions(+), 9 deletions(-) diff --git a/ceasiompy/SU2Run/files/config_template_rans.cfg b/ceasiompy/SU2Run/files/config_template_rans.cfg index 3da3b4d9e..a0b92f31b 100644 --- a/ceasiompy/SU2Run/files/config_template_rans.cfg +++ b/ceasiompy/SU2Run/files/config_template_rans.cfg @@ -74,13 +74,13 @@ MARKER_MONITORING= (S4CreatedbyGmsh) % NUM_METHOD_GRAD= GREEN_GAUSS % -CFL_NUMBER= 20 +CFL_NUMBER= 1 % CFL_ADAPT= NO % CFL_ADAPT_PARAM= ( 0.5, 1, 1.0, 100.0 ) % -ITER = 10000 +ITER = 5000 % Objective function in gradient evaluation (DRAG, LIFT, SIDEFORCE, MOMENT_X, % MOMENT_Y, MOMENT_Z, EFFICIENCY, BUFFET, @@ -167,9 +167,9 @@ CONV_STARTITER= 10 % ------------------------- INPUT/OUTPUT INFORMATION --------------------------% % -MESH_FILENAME= labair_penta.cgns +MESH_FILENAME= labair_penta.su2 % -MESH_FORMAT= CGNS +MESH_FORMAT= SU2 % MESH_OUT_FILENAME= mesh_out.su2 % diff --git a/ceasiompy/SU2Run/func/su2configrans.py b/ceasiompy/SU2Run/func/su2configrans.py index 52f15ea22..ebe9d4b0c 100644 --- a/ceasiompy/SU2Run/func/su2configrans.py +++ b/ceasiompy/SU2Run/func/su2configrans.py @@ -341,11 +341,11 @@ def generate_su2_cfd_config_rans(cpacs_path, cpacs_out_path, wkdir): # creare delle nuove xpath per la mesh cgns - cgns_mesh = Path(get_value(cpacs.tixi, SU2MESH_XPATH)) - if not cgns_mesh.is_file(): - raise FileNotFoundError(f"CGNS mesh file {cgns_mesh} not found") + su2_mesh = Path(get_value(cpacs.tixi, SU2MESH_XPATH)) + if not su2_mesh.is_file(): + raise FileNotFoundError(f"CGNS mesh file {su2_mesh} not found") - mesh_markers = get_mesh_markers(cgns_mesh) + mesh_markers = get_mesh_markers(su2_mesh) create_branch(cpacs.tixi, SU2_BC_WALL_XPATH) bc_wall_str = ";".join(mesh_markers["wall"]) @@ -479,7 +479,7 @@ def generate_su2_cfd_config_rans(cpacs_path, cpacs_out_path, wkdir): # Parameters which will vary for the different cases (alt,mach,aoa,aos) for case_nb in range(len(alt_list)): - cfg["MESH_FILENAME"] = str(cgns_mesh) + cfg["MESH_FILENAME"] = str(su2_mesh) alt = alt_list[case_nb] mach = mach_list[case_nb] From 166182c4cdbd7f0376a9c9f270bd6913fbd5d094 Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Thu, 8 Feb 2024 10:55:43 +0100 Subject: [PATCH 18/55] trying to solve issues with flake8 --- ceasiompy/SU2Run/func/su2utils.py | 2 +- 1 file changed, 1 insertion(+), 1 deletion(-) diff --git a/ceasiompy/SU2Run/func/su2utils.py b/ceasiompy/SU2Run/func/su2utils.py index 96878d67f..63b8d633c 100644 --- a/ceasiompy/SU2Run/func/su2utils.py +++ b/ceasiompy/SU2Run/func/su2utils.py @@ -173,7 +173,7 @@ def get_su2_config_template(): def get_cgns_config_template(): su2_dir = get_module_path("SU2Run") - su2_config_template_path_rans = Path(su2_dir, "files", f"config_template_rans.cfg") + su2_config_template_path_rans = Path(su2_dir, "files", "config_template_rans.cfg") return su2_config_template_path_rans From 24123539554c6f54a02635b45ee58bcbaffaff03 Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Thu, 8 Feb 2024 13:58:50 +0100 Subject: [PATCH 19/55] adding rans simulation --- ceasiompy/SU2Run/__specs__.py | 13 +++++++++++++ ceasiompy/SU2Run/files/config_template_rans.cfg | 2 +- ceasiompy/SU2Run/su2run.py | 10 ++++++++-- ceasiompy/utils/commonxpath.py | 1 + 4 files changed, 23 insertions(+), 3 deletions(-) diff --git a/ceasiompy/SU2Run/__specs__.py b/ceasiompy/SU2Run/__specs__.py index ecd05f417..f4fde02fe 100644 --- a/ceasiompy/SU2Run/__specs__.py +++ b/ceasiompy/SU2Run/__specs__.py @@ -28,6 +28,7 @@ SU2_TARGET_CL_XPATH, SU2_UPDATE_WETTED_AREA_XPATH, SU2MESH_XPATH, + SU2_RANS_XPATH, ) from ceasiompy.utils.moduleinterfaces import CPACSInOut @@ -167,6 +168,18 @@ gui_group="Aeromap Options", ) +cpacs_inout.add_input( + var_name="RANS calculation", + var_type=bool, + default_value=False, + unit="1", + descr="To check if is needed to run a RANS simulation or a normal EULER", + xpath=SU2_RANS_XPATH, + gui=True, + gui_name="Rans simulation", + gui_group="Aeromap Options", +) + cpacs_inout.add_input( var_name="rotation_rate", var_type=float, diff --git a/ceasiompy/SU2Run/files/config_template_rans.cfg b/ceasiompy/SU2Run/files/config_template_rans.cfg index a0b92f31b..1af0ceee0 100644 --- a/ceasiompy/SU2Run/files/config_template_rans.cfg +++ b/ceasiompy/SU2Run/files/config_template_rans.cfg @@ -187,7 +187,7 @@ RESTART_ADJ_FILENAME= restart_adj.dat % VOLUME_FILENAME= flow % -SURFACE_FILENAME= surface_flow_mesh +SURFACE_FILENAME= surface_flow % OUTPUT_WRT_FREQ= 100 % diff --git a/ceasiompy/SU2Run/su2run.py b/ceasiompy/SU2Run/su2run.py index 46971f117..52e49e14e 100644 --- a/ceasiompy/SU2Run/su2run.py +++ b/ceasiompy/SU2Run/su2run.py @@ -35,7 +35,7 @@ run_software, ) from ceasiompy.utils.commonnames import CONFIG_CFD_NAME, SU2_FORCES_BREAKDOWN_NAME -from ceasiompy.utils.commonxpath import SU2_NB_CPU_XPATH +from ceasiompy.utils.commonxpath import SU2_NB_CPU_XPATH, SU2_RANS_XPATH from ceasiompy.utils.moduleinterfaces import get_toolinput_file_path, get_tooloutput_file_path from cpacspy.cpacsfunctions import get_value_or_default, open_tixi @@ -115,7 +115,13 @@ def main(cpacs_path, cpacs_out_path): # Temporary CPACS to be stored after "generate_su2_cfd_config" cpacs_tmp_cfg = Path(cpacs_out_path.parent, "ConfigTMP.xml") - generate_su2_cfd_config_rans(cpacs_path, cpacs_tmp_cfg, results_dir) + if tixi.getTextElement(SU2_RANS_XPATH) == "True": + print("hello rans") + generate_su2_cfd_config_rans(cpacs_path, cpacs_tmp_cfg, results_dir) + else: + print("hello euler") + generate_su2_cfd_config(cpacs_path, cpacs_tmp_cfg, results_dir) + run_SU2_multi(results_dir, nb_proc) get_su2_results(cpacs_tmp_cfg, cpacs_out_path, results_dir) diff --git a/ceasiompy/utils/commonxpath.py b/ceasiompy/utils/commonxpath.py index 19e0b646f..2164f36d8 100644 --- a/ceasiompy/utils/commonxpath.py +++ b/ceasiompy/utils/commonxpath.py @@ -138,6 +138,7 @@ SU2_DEF_MESH_XPATH = SU2_XPATH + "/availableDeformedMesh" SU2_ACTUATOR_DISK_XPATH = SU2_XPATH + "/options/includeActuatorDisk" +SU2_RANS_XPATH = SU2_XPATH + "/options/ransRun" # RANGE RANGE_LD_RATIO_XPATH = CEASIOMPY_XPATH + "/ranges/lDRatio" From 7f1ce4ddf5b830926cd67ea0d007be14df8279e1 Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Thu, 8 Feb 2024 14:30:40 +0100 Subject: [PATCH 20/55] improving rans su2run --- ceasiompy/SU2Run/su2run.py | 2 +- 1 file changed, 1 insertion(+), 1 deletion(-) diff --git a/ceasiompy/SU2Run/su2run.py b/ceasiompy/SU2Run/su2run.py index 52e49e14e..05e2ed32a 100644 --- a/ceasiompy/SU2Run/su2run.py +++ b/ceasiompy/SU2Run/su2run.py @@ -115,7 +115,7 @@ def main(cpacs_path, cpacs_out_path): # Temporary CPACS to be stored after "generate_su2_cfd_config" cpacs_tmp_cfg = Path(cpacs_out_path.parent, "ConfigTMP.xml") - if tixi.getTextElement(SU2_RANS_XPATH) == "True": + if get_value_or_default(tixi, SU2_RANS_XPATH, False): print("hello rans") generate_su2_cfd_config_rans(cpacs_path, cpacs_tmp_cfg, results_dir) else: From c045d2a51cea6554468a817ba8934418925de2e3 Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Thu, 8 Feb 2024 14:53:54 +0100 Subject: [PATCH 21/55] improving rans simulations --- ceasiompy/SU2Run/__specs__.py | 8 ++++---- ceasiompy/SU2Run/su2run.py | 6 +++--- 2 files changed, 7 insertions(+), 7 deletions(-) diff --git a/ceasiompy/SU2Run/__specs__.py b/ceasiompy/SU2Run/__specs__.py index f4fde02fe..c5ed84fab 100644 --- a/ceasiompy/SU2Run/__specs__.py +++ b/ceasiompy/SU2Run/__specs__.py @@ -170,13 +170,13 @@ cpacs_inout.add_input( var_name="RANS calculation", - var_type=bool, - default_value=False, + var_type=list, + default_value=["EULER", "RANS"], unit="1", - descr="To check if is needed to run a RANS simulation or a normal EULER", + descr="Running a Rans or an Euler calculation", xpath=SU2_RANS_XPATH, gui=True, - gui_name="Rans simulation", + gui_name="Choosing between Rans or Euler simulation", gui_group="Aeromap Options", ) diff --git a/ceasiompy/SU2Run/su2run.py b/ceasiompy/SU2Run/su2run.py index 05e2ed32a..ce0e1d769 100644 --- a/ceasiompy/SU2Run/su2run.py +++ b/ceasiompy/SU2Run/su2run.py @@ -115,11 +115,11 @@ def main(cpacs_path, cpacs_out_path): # Temporary CPACS to be stored after "generate_su2_cfd_config" cpacs_tmp_cfg = Path(cpacs_out_path.parent, "ConfigTMP.xml") - if get_value_or_default(tixi, SU2_RANS_XPATH, False): - print("hello rans") + if get_value_or_default(tixi, SU2_RANS_XPATH, "EULER") == "RANS": + log.info("Rans simulation") generate_su2_cfd_config_rans(cpacs_path, cpacs_tmp_cfg, results_dir) else: - print("hello euler") + log.info("Euler simulation") generate_su2_cfd_config(cpacs_path, cpacs_tmp_cfg, results_dir) run_SU2_multi(results_dir, nb_proc) From 345627f2997bbb0eea50a3d793467831041bd49a Mon Sep 17 00:00:00 2001 From: Giacomo Benedetti Date: Thu, 8 Feb 2024 15:25:08 +0100 Subject: [PATCH 22/55] reordered --- ceasiompy/SU2Run/__specs__.py | 26 +++++++++++++------------- ceasiompy/SU2Run/su2run.py | 8 +++++--- 2 files changed, 18 insertions(+), 16 deletions(-) diff --git a/ceasiompy/SU2Run/__specs__.py b/ceasiompy/SU2Run/__specs__.py index c5ed84fab..68f3f64ee 100644 --- a/ceasiompy/SU2Run/__specs__.py +++ b/ceasiompy/SU2Run/__specs__.py @@ -28,7 +28,7 @@ SU2_TARGET_CL_XPATH, SU2_UPDATE_WETTED_AREA_XPATH, SU2MESH_XPATH, - SU2_RANS_XPATH, + SU2_CONFIG_RANS_XPATH, ) from ceasiompy.utils.moduleinterfaces import CPACSInOut @@ -168,18 +168,6 @@ gui_group="Aeromap Options", ) -cpacs_inout.add_input( - var_name="RANS calculation", - var_type=list, - default_value=["EULER", "RANS"], - unit="1", - descr="Running a Rans or an Euler calculation", - xpath=SU2_RANS_XPATH, - gui=True, - gui_name="Choosing between Rans or Euler simulation", - gui_group="Aeromap Options", -) - cpacs_inout.add_input( var_name="rotation_rate", var_type=float, @@ -216,6 +204,18 @@ gui_group="CPU", ) +cpacs_inout.add_input( + var_name="RANS calculation", + var_type=list, + default_value=["Euler", "RANS"], + unit="1", + descr="Running an Euler or a RANS calculation", + xpath=SU2_CONFIG_RANS_XPATH, + gui=True, + gui_name="Choosing between Euler or RANS simulation", + gui_group="SU2 Parameters", +) + cpacs_inout.add_input( var_name="max_iter", var_type=int, diff --git a/ceasiompy/SU2Run/su2run.py b/ceasiompy/SU2Run/su2run.py index ce0e1d769..a7deada1a 100644 --- a/ceasiompy/SU2Run/su2run.py +++ b/ceasiompy/SU2Run/su2run.py @@ -35,7 +35,7 @@ run_software, ) from ceasiompy.utils.commonnames import CONFIG_CFD_NAME, SU2_FORCES_BREAKDOWN_NAME -from ceasiompy.utils.commonxpath import SU2_NB_CPU_XPATH, SU2_RANS_XPATH +from ceasiompy.utils.commonxpath import SU2_NB_CPU_XPATH, SU2_CONFIG_RANS_XPATH from ceasiompy.utils.moduleinterfaces import get_toolinput_file_path, get_tooloutput_file_path from cpacspy.cpacsfunctions import get_value_or_default, open_tixi @@ -115,8 +115,10 @@ def main(cpacs_path, cpacs_out_path): # Temporary CPACS to be stored after "generate_su2_cfd_config" cpacs_tmp_cfg = Path(cpacs_out_path.parent, "ConfigTMP.xml") - if get_value_or_default(tixi, SU2_RANS_XPATH, "EULER") == "RANS": - log.info("Rans simulation") + config_file_type = get_value_or_default(tixi, SU2_CONFIG_RANS_XPATH, "Euler") + + if config_file_type == "RANS": + log.info("RANS simulation") generate_su2_cfd_config_rans(cpacs_path, cpacs_tmp_cfg, results_dir) else: log.info("Euler simulation") From 28bf2a1e47d19fe162ccf79a0650eae7dd8b7ac6 Mon Sep 17 00:00:00 2001 From: Giacomo Benedetti Date: Thu, 8 Feb 2024 15:31:15 +0100 Subject: [PATCH 23/55] fix tests --- ceasiompy/utils/commonxpath.py | 2 +- 1 file changed, 1 insertion(+), 1 deletion(-) diff --git a/ceasiompy/utils/commonxpath.py b/ceasiompy/utils/commonxpath.py index 2164f36d8..a297e734e 100644 --- a/ceasiompy/utils/commonxpath.py +++ b/ceasiompy/utils/commonxpath.py @@ -138,7 +138,7 @@ SU2_DEF_MESH_XPATH = SU2_XPATH + "/availableDeformedMesh" SU2_ACTUATOR_DISK_XPATH = SU2_XPATH + "/options/includeActuatorDisk" -SU2_RANS_XPATH = SU2_XPATH + "/options/ransRun" +SU2_CONFIG_RANS_XPATH = SU2_XPATH + "/options/config_type" # RANGE RANGE_LD_RATIO_XPATH = CEASIOMPY_XPATH + "/ranges/lDRatio" From c22ed030b1cb98cbc37d76d17eea18f6a119eef6 Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Fri, 9 Feb 2024 10:35:04 +0100 Subject: [PATCH 24/55] start adding tests --- .../tests/test_turbofan/test_turbofan.py | 59 +++++++++++++++++++ .../ThermoData/tests/test_turbojet/test1.py | 44 ++++++++++++++ .../tests/test_turbojet/test_turbojet.py | 59 +++++++++++++++++++ 3 files changed, 162 insertions(+) create mode 100644 ceasiompy/ThermoData/tests/test_turbofan/test_turbofan.py create mode 100644 ceasiompy/ThermoData/tests/test_turbojet/test1.py create mode 100644 ceasiompy/ThermoData/tests/test_turbojet/test_turbojet.py diff --git a/ceasiompy/ThermoData/tests/test_turbofan/test_turbofan.py b/ceasiompy/ThermoData/tests/test_turbofan/test_turbofan.py new file mode 100644 index 000000000..88dea37cb --- /dev/null +++ b/ceasiompy/ThermoData/tests/test_turbofan/test_turbofan.py @@ -0,0 +1,59 @@ +""" +CEASIOMpy: Conceptual Aircraft Design Software + +Developed by CFS ENGINEERING, 1015 Lausanne, Switzerland + +Test functions of 'ceasiompy/ThermoData/func/turbofan_func.py' + +Python version: >=3.8 + + +| Author : Giacomo Benedetti and Francesco Marcucci +| Creation: 2024-02-09 + +""" +# ================================================================================================= +# IMPORTS +# ================================================================================================= + +import os +from pathlib import Path + +import pytest +from ceasiompy.SU2Run.func.su2results import save_screenshot +from ceasiompy.utils.commonpaths import TEST_RESULTS_FILES_PATH + +MODULE_DIR = Path(__file__).parent + + +# ================================================================================================= +# CLASSES +# ================================================================================================= + + +# ================================================================================================= +# FUNCTIONS +# ================================================================================================= + + +@pytest.mark.skipif("DISPLAY" not in os.environ, reason="requires display") +def test_save_screenshot(): + """Test the function 'save_screenshot'""" + + surface_flow_file = Path(TEST_RESULTS_FILES_PATH, "surface_flow.vtu") + screenshot_file = save_screenshot(surface_flow_file, "Mach") + assert screenshot_file.exists() + + if screenshot_file.exists(): + screenshot_file.unlink() + + +# ================================================================================================= +# MAIN +# ================================================================================================= + +if __name__ == "__main__": + + print("Test configfile.py") + print("To run test use the following command:") + print(">> pytest -v") diff --git a/ceasiompy/ThermoData/tests/test_turbojet/test1.py b/ceasiompy/ThermoData/tests/test_turbojet/test1.py new file mode 100644 index 000000000..36db907dd --- /dev/null +++ b/ceasiompy/ThermoData/tests/test_turbojet/test1.py @@ -0,0 +1,44 @@ +from pathlib import Path + +import sys + +sys.path.append("/home/cfse/Stage_Francesco/Thermodata") + +from ceasiompy.ThermoData.func.turbofan_func import ( + turbofan_analysis, +) + +from ceasiompy.ThermoData.func.turbojet_func import ( + turbojet_analysis, +) + +import pytest + +import numpy as np + + +def test_turbojet(): + alt = 4000 # [ft] + MN = 0.6 + Fn = 11800 # [lbf] + new_sol = turbojet_analysis(alt, MN, Fn) + correct_sol = np.array([717.59577021, 818.40663844, 1.57394908]).reshape((3, 1)) + np.testing.assert_almost_equal(new_sol, correct_sol, 5) + + +def test_turbofan(): + alt = 4000 # [ft] + MN = 0.6 + Fn = 11800 # [lbf] + new_sol_tf = turbofan_analysis(alt, MN) + correct_sol_tf = np.array( + [ + 8.11328662e01, + 3.44500820e02, + 1.00000000e00, + 4.19439630e02, + 5.64233274e01, + 1.08865912e-01, + ] + ).reshape((6, 1)) + np.testing.assert_almost_equal(new_sol_tf, correct_sol_tf, 5) diff --git a/ceasiompy/ThermoData/tests/test_turbojet/test_turbojet.py b/ceasiompy/ThermoData/tests/test_turbojet/test_turbojet.py new file mode 100644 index 000000000..a2c1e76c4 --- /dev/null +++ b/ceasiompy/ThermoData/tests/test_turbojet/test_turbojet.py @@ -0,0 +1,59 @@ +""" +CEASIOMpy: Conceptual Aircraft Design Software + +Developed by CFS ENGINEERING, 1015 Lausanne, Switzerland + +Test functions of 'ceasiompy/ThermoData/func/turbojet_func.py' + +Python version: >=3.8 + + +| Author : Giacomo Benedetti and Francesco Marcucci +| Creation: 2024-02-09 + +""" +# ================================================================================================= +# IMPORTS +# ================================================================================================= + +import os +from pathlib import Path + +import pytest +from ceasiompy.SU2Run.func.su2results import save_screenshot +from ceasiompy.utils.commonpaths import TEST_RESULTS_FILES_PATH + +MODULE_DIR = Path(__file__).parent + + +# ================================================================================================= +# CLASSES +# ================================================================================================= + + +# ================================================================================================= +# FUNCTIONS +# ================================================================================================= + + +@pytest.mark.skipif("DISPLAY" not in os.environ, reason="requires display") +def test_save_screenshot(): + """Test the function 'save_screenshot'""" + + surface_flow_file = Path(TEST_RESULTS_FILES_PATH, "surface_flow.vtu") + screenshot_file = save_screenshot(surface_flow_file, "Mach") + assert screenshot_file.exists() + + if screenshot_file.exists(): + screenshot_file.unlink() + + +# ================================================================================================= +# MAIN +# ================================================================================================= + +if __name__ == "__main__": + + print("Test configfile.py") + print("To run test use the following command:") + print(">> pytest -v") From 543e5c7ad41c00e96a74c41e5528dcede0a8ab57 Mon Sep 17 00:00:00 2001 From: Giacomo Benedetti Date: Fri, 9 Feb 2024 10:58:16 +0100 Subject: [PATCH 25/55] mod --- ceasiompy/SU2Run/__specs__.py | 2 +- ceasiompy/ThermoData/func/turbofan_func.py | 2 +- ceasiompy/ThermoData/func/turbojet_func.py | 2 +- ceasiompy/ThermoData/tests/test_turbofan/test_turbofan.py | 2 +- ceasiompy/ThermoData/tests/test_turbojet/test_turbojet.py | 2 +- ceasiompy/ThermoData/thermodata.py | 2 +- 6 files changed, 6 insertions(+), 6 deletions(-) diff --git a/ceasiompy/SU2Run/__specs__.py b/ceasiompy/SU2Run/__specs__.py index 68f3f64ee..243ad926b 100644 --- a/ceasiompy/SU2Run/__specs__.py +++ b/ceasiompy/SU2Run/__specs__.py @@ -212,7 +212,7 @@ descr="Running an Euler or a RANS calculation", xpath=SU2_CONFIG_RANS_XPATH, gui=True, - gui_name="Choosing between Euler or RANS simulation", + gui_name="Euler or RANS simulation", gui_group="SU2 Parameters", ) diff --git a/ceasiompy/ThermoData/func/turbofan_func.py b/ceasiompy/ThermoData/func/turbofan_func.py index 5973e42b0..fa5fa6fcc 100644 --- a/ceasiompy/ThermoData/func/turbofan_func.py +++ b/ceasiompy/ThermoData/func/turbofan_func.py @@ -7,7 +7,7 @@ Python version: >=3.8 -| Author: Giacomo Benedetti and Francesco Marcucci +| Author: Francesco Marcucci | Creation: 2023-12-12 """ diff --git a/ceasiompy/ThermoData/func/turbojet_func.py b/ceasiompy/ThermoData/func/turbojet_func.py index 630cfd343..4562cb6b3 100644 --- a/ceasiompy/ThermoData/func/turbojet_func.py +++ b/ceasiompy/ThermoData/func/turbojet_func.py @@ -7,7 +7,7 @@ Python version: >=3.8 -| Author: Giacomo Benedetti and Francesco Marcucci +| Author: Francesco Marcucci | Creation: 2023-12-12 """ diff --git a/ceasiompy/ThermoData/tests/test_turbofan/test_turbofan.py b/ceasiompy/ThermoData/tests/test_turbofan/test_turbofan.py index 88dea37cb..7b6469285 100644 --- a/ceasiompy/ThermoData/tests/test_turbofan/test_turbofan.py +++ b/ceasiompy/ThermoData/tests/test_turbofan/test_turbofan.py @@ -8,7 +8,7 @@ Python version: >=3.8 -| Author : Giacomo Benedetti and Francesco Marcucci +| Author : Francesco Marcucci | Creation: 2024-02-09 """ diff --git a/ceasiompy/ThermoData/tests/test_turbojet/test_turbojet.py b/ceasiompy/ThermoData/tests/test_turbojet/test_turbojet.py index a2c1e76c4..c216e8855 100644 --- a/ceasiompy/ThermoData/tests/test_turbojet/test_turbojet.py +++ b/ceasiompy/ThermoData/tests/test_turbojet/test_turbojet.py @@ -8,7 +8,7 @@ Python version: >=3.8 -| Author : Giacomo Benedetti and Francesco Marcucci +| Author : Francesco Marcucci | Creation: 2024-02-09 """ diff --git a/ceasiompy/ThermoData/thermodata.py b/ceasiompy/ThermoData/thermodata.py index 32eff3efc..e69e1f594 100644 --- a/ceasiompy/ThermoData/thermodata.py +++ b/ceasiompy/ThermoData/thermodata.py @@ -6,7 +6,7 @@ Calculate outlet conditions fot turbojet and turbofan engines by using the open source code PyCycle and saving those conditions in a text file -| Author: Giacomo Benedetti and Francesco Marcucci +| Author: Francesco Marcucci | Creation: 2023-12-12 """ From da5397344b08d094af0728e6ee5605ecae5fffd1 Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Fri, 9 Feb 2024 12:07:02 +0100 Subject: [PATCH 26/55] solving test issues --- ceasiompy/ThermoData/tests/test_turbojet/test1.py | 10 +++++----- 1 file changed, 5 insertions(+), 5 deletions(-) diff --git a/ceasiompy/ThermoData/tests/test_turbojet/test1.py b/ceasiompy/ThermoData/tests/test_turbojet/test1.py index 36db907dd..75c42b259 100644 --- a/ceasiompy/ThermoData/tests/test_turbojet/test1.py +++ b/ceasiompy/ThermoData/tests/test_turbojet/test1.py @@ -2,6 +2,10 @@ import sys +import pytest + +import numpy as np + sys.path.append("/home/cfse/Stage_Francesco/Thermodata") from ceasiompy.ThermoData.func.turbofan_func import ( @@ -12,10 +16,6 @@ turbojet_analysis, ) -import pytest - -import numpy as np - def test_turbojet(): alt = 4000 # [ft] @@ -29,7 +29,7 @@ def test_turbojet(): def test_turbofan(): alt = 4000 # [ft] MN = 0.6 - Fn = 11800 # [lbf] + # Fn = 11800 # [lbf] new_sol_tf = turbofan_analysis(alt, MN) correct_sol_tf = np.array( [ From e77a3611b78dc9992171ac64e7faf1b84132a9d0 Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Fri, 9 Feb 2024 12:13:45 +0100 Subject: [PATCH 27/55] solving flake8 issues --- ceasiompy/ThermoData/tests/test_turbojet/test1.py | 4 ++-- 1 file changed, 2 insertions(+), 2 deletions(-) diff --git a/ceasiompy/ThermoData/tests/test_turbojet/test1.py b/ceasiompy/ThermoData/tests/test_turbojet/test1.py index 75c42b259..96495a0e9 100644 --- a/ceasiompy/ThermoData/tests/test_turbojet/test1.py +++ b/ceasiompy/ThermoData/tests/test_turbojet/test1.py @@ -6,8 +6,6 @@ import numpy as np -sys.path.append("/home/cfse/Stage_Francesco/Thermodata") - from ceasiompy.ThermoData.func.turbofan_func import ( turbofan_analysis, ) @@ -16,6 +14,8 @@ turbojet_analysis, ) +sys.path.append("/home/cfse/Stage_Francesco/Thermodata") + def test_turbojet(): alt = 4000 # [ft] From 01eb338952213c2aa202c3a3663eae39e1b85ec7 Mon Sep 17 00:00:00 2001 From: GBenedett Date: Tue, 13 Feb 2024 13:31:25 +0100 Subject: [PATCH 28/55] codacy and names --- .../SU2Run/func/{su2configrans.py => su2config_rans.py} | 3 +-- ceasiompy/SU2Run/su2run.py | 5 +---- 2 files changed, 2 insertions(+), 6 deletions(-) rename ceasiompy/SU2Run/func/{su2configrans.py => su2config_rans.py} (99%) diff --git a/ceasiompy/SU2Run/func/su2configrans.py b/ceasiompy/SU2Run/func/su2config_rans.py similarity index 99% rename from ceasiompy/SU2Run/func/su2configrans.py rename to ceasiompy/SU2Run/func/su2config_rans.py index ebe9d4b0c..45b095e4d 100644 --- a/ceasiompy/SU2Run/func/su2configrans.py +++ b/ceasiompy/SU2Run/func/su2config_rans.py @@ -297,7 +297,6 @@ def add_actuator_disk(cfg, cpacs, case_dir_path, actuator_disk_file, mesh_marker def add_thermodata(cfg, cpacs, alt, case_nb, alt_list): - if cpacs.tixi.checkElement(ENGINE_TYPE_XPATH): log.info("adding engine BC to the SU2 config file") engine_type = get_value(cpacs.tixi, ENGINE_TYPE_XPATH) @@ -478,7 +477,7 @@ def generate_su2_cfd_config_rans(cpacs_path, cpacs_out_path, wkdir): # Parameters which will vary for the different cases (alt,mach,aoa,aos) - for case_nb in range(len(alt_list)): + for case_nb, alt_value in enumerate(alt_list): cfg["MESH_FILENAME"] = str(su2_mesh) alt = alt_list[case_nb] diff --git a/ceasiompy/SU2Run/su2run.py b/ceasiompy/SU2Run/su2run.py index a7deada1a..ea8499714 100644 --- a/ceasiompy/SU2Run/su2run.py +++ b/ceasiompy/SU2Run/su2run.py @@ -26,7 +26,7 @@ from pathlib import Path from ceasiompy.SU2Run.func.su2config import generate_su2_cfd_config -from ceasiompy.SU2Run.func.su2configrans import generate_su2_cfd_config_rans +from ceasiompy.SU2Run.func.su2config_rans import generate_su2_cfd_config_rans from ceasiompy.SU2Run.func.su2results import get_su2_results from ceasiompy.utils.ceasiomlogger import get_logger from ceasiompy.utils.ceasiompyutils import ( @@ -73,7 +73,6 @@ def run_SU2_multi(wkdir, nb_proc=1): raise OSError(f"No Case directory has been found in the working directory: {wkdir}") for config_dir in sorted(case_dir_list): - config_cfd = [c for c in config_dir.iterdir() if c.name == CONFIG_CFD_NAME] if not config_cfd: @@ -104,7 +103,6 @@ def run_SU2_multi(wkdir, nb_proc=1): def main(cpacs_path, cpacs_out_path): - log.info("----- Start of " + MODULE_NAME + " -----") tixi = open_tixi(cpacs_path) @@ -131,7 +129,6 @@ def main(cpacs_path, cpacs_out_path): if __name__ == "__main__": - cpacs_path = get_toolinput_file_path(MODULE_NAME) cpacs_out_path = get_tooloutput_file_path(MODULE_NAME) From ae393713028d3b47e2c9f3b19dc86d0a26e90e11 Mon Sep 17 00:00:00 2001 From: GBenedett Date: Tue, 13 Feb 2024 13:35:58 +0100 Subject: [PATCH 29/55] codacy enumerate --- ceasiompy/SU2Run/func/su2config_rans.py | 2 +- 1 file changed, 1 insertion(+), 1 deletion(-) diff --git a/ceasiompy/SU2Run/func/su2config_rans.py b/ceasiompy/SU2Run/func/su2config_rans.py index 45b095e4d..513d23abb 100644 --- a/ceasiompy/SU2Run/func/su2config_rans.py +++ b/ceasiompy/SU2Run/func/su2config_rans.py @@ -477,7 +477,7 @@ def generate_su2_cfd_config_rans(cpacs_path, cpacs_out_path, wkdir): # Parameters which will vary for the different cases (alt,mach,aoa,aos) - for case_nb, alt_value in enumerate(alt_list): + for case_nb in enumerate(alt_list): cfg["MESH_FILENAME"] = str(su2_mesh) alt = alt_list[case_nb] From c20d387931991106e31c1987bef034de6df647a7 Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Wed, 14 Feb 2024 15:11:44 +0100 Subject: [PATCH 30/55] adding correct unit to net force --- ceasiompy/ThermoData/__specs__.py | 4 ++-- ceasiompy/ThermoData/func/turbofan_func.py | 2 +- ceasiompy/ThermoData/func/turbojet_func.py | 4 +++- 3 files changed, 6 insertions(+), 4 deletions(-) diff --git a/ceasiompy/ThermoData/__specs__.py b/ceasiompy/ThermoData/__specs__.py index 09a5cfa02..2d526d86f 100644 --- a/ceasiompy/ThermoData/__specs__.py +++ b/ceasiompy/ThermoData/__specs__.py @@ -26,8 +26,8 @@ cpacs_inout.add_input( var_name="net_force", var_type=float, - default_value=2000, - unit="1", # AGGIUNGERE UNITA DI MISURA + default_value=5000, + unit="[N]", descr="Engine net force", xpath=RANGE_XPATH + "/NetForce", gui=True, diff --git a/ceasiompy/ThermoData/func/turbofan_func.py b/ceasiompy/ThermoData/func/turbofan_func.py index fa5fa6fcc..8d3a3f491 100644 --- a/ceasiompy/ThermoData/func/turbofan_func.py +++ b/ceasiompy/ThermoData/func/turbofan_func.py @@ -313,7 +313,7 @@ def viewer(prob, pt, file=sys.stdout): prob.set_val("DESIGN.fc.MN", MN) prob.set_val("DESIGN.T4_MAX", 2857, units="degR") - prob.set_val("DESIGN.Fn_DES", Fn, units="lbf") + prob.set_val("DESIGN.Fn_DES", Fn * 0.2248089431, units="lbf") # 1 N = 0.2248089431 lbf # Set initial guesses for balances prob["DESIGN.balance.FAR"] = 0.1 diff --git a/ceasiompy/ThermoData/func/turbojet_func.py b/ceasiompy/ThermoData/func/turbojet_func.py index 4562cb6b3..0e0337de3 100644 --- a/ceasiompy/ThermoData/func/turbojet_func.py +++ b/ceasiompy/ThermoData/func/turbojet_func.py @@ -136,7 +136,9 @@ def setup(self): # define input values prob.set_val("DESIGN.fc.alt", alt, units="ft") prob.set_val("DESIGN.fc.MN", MN) - prob.set_val("DESIGN.balance.Fn_target", Fn, units="lbf") + prob.set_val( + "DESIGN.balance.Fn_target", Fn * 0.2248089431, units="lbf" + ) # 1 N = 0.2248089431 lbf prob.set_val("DESIGN.balance.T4_target", 2370.0, units="degR") prob.set_val("DESIGN.comp.PR", 13.5) prob.set_val("DESIGN.comp.eff", 0.83) From 2751a67761834559532761f678ec6d209385e728 Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Thu, 15 Feb 2024 14:05:53 +0100 Subject: [PATCH 31/55] setting correct units --- ceasiompy/ThermoData/func/turbofan_func.py | 2 +- ceasiompy/ThermoData/func/turbojet_func.py | 2 +- 2 files changed, 2 insertions(+), 2 deletions(-) diff --git a/ceasiompy/ThermoData/func/turbofan_func.py b/ceasiompy/ThermoData/func/turbofan_func.py index 8d3a3f491..27481771f 100644 --- a/ceasiompy/ThermoData/func/turbofan_func.py +++ b/ceasiompy/ThermoData/func/turbofan_func.py @@ -309,7 +309,7 @@ def viewer(prob, pt, file=sys.stdout): prob.set_val("DESIGN.hpt.eff", 0.8888) prob.set_val("DESIGN.lpt.eff", 0.8996) - prob.set_val("DESIGN.fc.alt", alt, units="ft") + prob.set_val("DESIGN.fc.alt", alt * 3.2808399, units="ft") prob.set_val("DESIGN.fc.MN", MN) prob.set_val("DESIGN.T4_MAX", 2857, units="degR") diff --git a/ceasiompy/ThermoData/func/turbojet_func.py b/ceasiompy/ThermoData/func/turbojet_func.py index 0e0337de3..1e02b3550 100644 --- a/ceasiompy/ThermoData/func/turbojet_func.py +++ b/ceasiompy/ThermoData/func/turbojet_func.py @@ -134,7 +134,7 @@ def setup(self): prob.setup(check=False) # define input values - prob.set_val("DESIGN.fc.alt", alt, units="ft") + prob.set_val("DESIGN.fc.alt", alt * 3.2808399, units="ft") prob.set_val("DESIGN.fc.MN", MN) prob.set_val( "DESIGN.balance.Fn_target", Fn * 0.2248089431, units="lbf" From f7322425c0ac714e6c9151d8a2b8b68be25a1c8c Mon Sep 17 00:00:00 2001 From: GBenedett Date: Mon, 19 Feb 2024 11:43:40 +0100 Subject: [PATCH 32/55] pycycle module added to python environment --- environment.yml | 1 + 1 file changed, 1 insertion(+) diff --git a/environment.yml b/environment.yml index b191c3297..d798c246f 100644 --- a/environment.yml +++ b/environment.yml @@ -47,3 +47,4 @@ dependencies: - smt==1.2.0 - streamlit==1.14.0 - streamlit-autorefresh + - om-pycycle From b3d896418673d96614850bc905a2b377c87c237b Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Mon, 19 Feb 2024 14:37:17 +0100 Subject: [PATCH 33/55] fixing pycycle issues --- ceasiompy/ThermoData/__specs__.py | 4 ++-- 1 file changed, 2 insertions(+), 2 deletions(-) diff --git a/ceasiompy/ThermoData/__specs__.py b/ceasiompy/ThermoData/__specs__.py index 2d526d86f..7fe6bb9b5 100644 --- a/ceasiompy/ThermoData/__specs__.py +++ b/ceasiompy/ThermoData/__specs__.py @@ -26,8 +26,8 @@ cpacs_inout.add_input( var_name="net_force", var_type=float, - default_value=5000, - unit="[N]", + default_value=2000, + unit="N", descr="Engine net force", xpath=RANGE_XPATH + "/NetForce", gui=True, From bc998d1550556c9b3c918ffe3c913aec85ff1a18 Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Mon, 19 Feb 2024 14:42:53 +0100 Subject: [PATCH 34/55] cpacs files --- test_files/CPACSfiles/busjet0903mod.xml | 2975 +++++++ test_files/CPACSfiles/concorde1014.xml | 2263 ++++++ test_files/CPACSfiles/j280904scaled.xml | 3096 +++++++ test_files/CPACSfiles/j35vort0903cfscaled.xml | 7140 +++++++++++++++++ test_files/CPACSfiles/labARscaled.xml | 933 +++ 5 files changed, 16407 insertions(+) create mode 100644 test_files/CPACSfiles/busjet0903mod.xml create mode 100644 test_files/CPACSfiles/concorde1014.xml create mode 100644 test_files/CPACSfiles/j280904scaled.xml create mode 100644 test_files/CPACSfiles/j35vort0903cfscaled.xml create mode 100644 test_files/CPACSfiles/labARscaled.xml diff --git a/test_files/CPACSfiles/busjet0903mod.xml b/test_files/CPACSfiles/busjet0903mod.xml new file mode 100644 index 000000000..4dddaa07e --- /dev/null +++ b/test_files/CPACSfiles/busjet0903mod.xml @@ -0,0 +1,2975 @@ + + +
+ busjet0903mod + Simple Wing for unit testing + Martin Siggel + 2012-10-09T15:12:47 + 0.2 + 3.0 + + + Converted to cpacs 3.0 using cpacs2to3 - does not include structure update + cpacs2to3 + 2018-01-15T09:22:57 + 0.2 + 3.0 + + + Add this update + Aidan + 2018-10-03T09:00:01 + 0.3 + 3.0 + + +
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;0.041032 ;0.045919 ;0.049452 ;0.051842 ;0.053150 ;0.053253 ;0.051949 ;0.049506 ;0.046177 ;0.042148 ;0.037536 ;0.032470 ;0.027121 ;0.021714 ;0.016321 ;0.010942 ;0.005576 ;0.000224 + + + + + + From 2c404abf98fce0c7e224c4690aba0833a8bc070c Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Tue, 20 Feb 2024 12:09:41 +0100 Subject: [PATCH 35/55] add redmi to ThermoData --- ceasiompy/ThermoData/README.md | 37 +++++++++++++++++++++++++++++++++- 1 file changed, 36 insertions(+), 1 deletion(-) diff --git a/ceasiompy/ThermoData/README.md b/ceasiompy/ThermoData/README.md index 77e55d5ff..5edcb662d 100644 --- a/ceasiompy/ThermoData/README.md +++ b/ceasiompy/ThermoData/README.md @@ -1 +1,36 @@ -# Thermo_Data \ No newline at end of file + + +# ThermoData + +**Categories:** Engine Boundary conditions + +**State**: :heavy_check_mark: + + + +
+ +`ThermoData` is a module to provide the outlet conditions of a given engine. It can calculate different operating conditions and save the results in a text file. This module is derived starting from the OpenSource code [pyCycle](https://github.com/OpenMDAO/pycycle) developed by Eric S. Hendricks and Justin S. Gray. It can perform calculations on both turbojet and turbofan engines, with the possibility to customize the parameters. The results are automatically written inside the config file of the module `SU2Run` to be able to perform the calculations. + +## Inputs +`ThermoData` can be run on is own by giving the altitude the Mach number and the Net force. Otherwise it can take as an input the values from `CPACS2GMSH` module. + +## Analyses +`ThermoData` compute the values obtained at the engine outlet giving a "EngineBC.dat" file as an output. if the workflow continues with the `SU2Run` run module the results are added to the config file to perform the simulation. + +## Outputs +`ThermoData` output is the "EngineBC.dat" file with stored inside: T_tot_out, V_stat_out, MN_out, P_tot_out, massflow_stat_out, T_stat_out, P_stat_out for the chosen engine configuration. + +## Installation or requirements +`ThermoData` needs the installation of the openmdao and pycycle suite that are included in the python environment of CEASIOMpy. + +## Limitations + +To be able to change the engine parameters other than those given as input (altitude, mach, net force) the turbojet and turbofan functions in the module must be modified by coding. + +## More information + +* [pyCycle Github repository](https://github.com/OpenMDAO/pycycle) + +* [OpenMDAO documentation ](https://openmdao.org/newdocs/versions/latest/main.html) + From 0ca7ffb93ae8f3d9c4160c4a52cf95dda7900b4b Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Tue, 20 Feb 2024 12:23:06 +0100 Subject: [PATCH 36/55] changing first page redmi to add thermodata module --- README.md | 1 + 1 file changed, 1 insertion(+) diff --git a/README.md b/README.md index cfaa5572c..b117f0fb2 100644 --- a/README.md +++ b/README.md @@ -116,6 +116,7 @@ warning: : The module does not work completely as expected. It is not a bug, but - [Optimisation](ceasiompy/Optimisation/README.md) :x: - [SMTrain](ceasiompy/SMTrain/README.md) :x: - [SMUse](ceasiompy/SMUse/README.md) :x: +- [ThermoData](ceasiompy/ThermoData/README.md) :heavy_check_mark: From 8d72d11ed1f97fb3118ffe49e1516d1338b4cc98 Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Tue, 20 Feb 2024 12:25:42 +0100 Subject: [PATCH 37/55] changing redmi Thermodata logo --- ceasiompy/ThermoData/README.md | 2 +- 1 file changed, 1 insertion(+), 1 deletion(-) diff --git a/ceasiompy/ThermoData/README.md b/ceasiompy/ThermoData/README.md index 5edcb662d..a92647d30 100644 --- a/ceasiompy/ThermoData/README.md +++ b/ceasiompy/ThermoData/README.md @@ -1,4 +1,4 @@ - + # ThermoData From 33056d72d4cc0efa62ddc4eb55389196e454ef2b Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Tue, 20 Feb 2024 16:18:20 +0100 Subject: [PATCH 38/55] fixing rans issues --- ceasiompy/SU2Run/func/su2config_rans.py | 10 +++++----- ceasiompy/SU2Run/func/su2utils.py | 2 +- 2 files changed, 6 insertions(+), 6 deletions(-) diff --git a/ceasiompy/SU2Run/func/su2config_rans.py b/ceasiompy/SU2Run/func/su2config_rans.py index 513d23abb..b650ae83e 100644 --- a/ceasiompy/SU2Run/func/su2config_rans.py +++ b/ceasiompy/SU2Run/func/su2config_rans.py @@ -32,7 +32,7 @@ write_actuator_disk_data, write_header, ) -from ceasiompy.SU2Run.func.su2utils import get_mesh_markers, get_cgns_config_template +from ceasiompy.SU2Run.func.su2utils import get_mesh_markers, get_su2_config_template_rans from ceasiompy.utils.ceasiomlogger import get_logger from ceasiompy.utils.commonnames import ( ACTUATOR_DISK_FILE_NAME, @@ -338,11 +338,11 @@ def generate_su2_cfd_config_rans(cpacs_path, cpacs_out_path, wkdir): cpacs = CPACS(cpacs_path) - # creare delle nuove xpath per la mesh cgns + # creare delle nuove xpath per la mesh su2 su2_mesh = Path(get_value(cpacs.tixi, SU2MESH_XPATH)) if not su2_mesh.is_file(): - raise FileNotFoundError(f"CGNS mesh file {su2_mesh} not found") + raise FileNotFoundError(f"SU2 mesh file {su2_mesh} not found") mesh_markers = get_mesh_markers(su2_mesh) @@ -414,7 +414,7 @@ def generate_su2_cfd_config_rans(cpacs_path, cpacs_out_path, wkdir): aoa_list = [0.0] aos_list = [0.0] - cfg = ConfigFile(get_cgns_config_template()) + cfg = ConfigFile(get_su2_config_template_rans()) # Check if symmetry plane is defined (Default: False) sym_factor = 1.0 @@ -477,7 +477,7 @@ def generate_su2_cfd_config_rans(cpacs_path, cpacs_out_path, wkdir): # Parameters which will vary for the different cases (alt,mach,aoa,aos) - for case_nb in enumerate(alt_list): + for case_nb in range(len(alt_list)): cfg["MESH_FILENAME"] = str(su2_mesh) alt = alt_list[case_nb] diff --git a/ceasiompy/SU2Run/func/su2utils.py b/ceasiompy/SU2Run/func/su2utils.py index 63b8d633c..24db788bf 100644 --- a/ceasiompy/SU2Run/func/su2utils.py +++ b/ceasiompy/SU2Run/func/su2utils.py @@ -170,7 +170,7 @@ def get_su2_config_template(): return su2_config_template_path -def get_cgns_config_template(): +def get_su2_config_template_rans(): su2_dir = get_module_path("SU2Run") su2_config_template_path_rans = Path(su2_dir, "files", "config_template_rans.cfg") From d83727001da203466d91301778fef94910697d5f Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Wed, 21 Feb 2024 15:45:48 +0100 Subject: [PATCH 39/55] changing the redmi --- ceasiompy/ThermoData/README.md | 14 +++++++++++--- 1 file changed, 11 insertions(+), 3 deletions(-) diff --git a/ceasiompy/ThermoData/README.md b/ceasiompy/ThermoData/README.md index a92647d30..f8c58d3a9 100644 --- a/ceasiompy/ThermoData/README.md +++ b/ceasiompy/ThermoData/README.md @@ -10,16 +10,24 @@
-`ThermoData` is a module to provide the outlet conditions of a given engine. It can calculate different operating conditions and save the results in a text file. This module is derived starting from the OpenSource code [pyCycle](https://github.com/OpenMDAO/pycycle) developed by Eric S. Hendricks and Justin S. Gray. It can perform calculations on both turbojet and turbofan engines, with the possibility to customize the parameters. The results are automatically written inside the config file of the module `SU2Run` to be able to perform the calculations. +`ThermoData` is a module to provide the outlet conditions of a given engine. It can calculate different operating conditions and save the results in a text file. This module is derived starting from the OpenSource code [pyCycle](https://github.com/OpenMDAO/pycycle) developed by Eric S. Hendricks and Justin S. Gray. It can perform calculations on both turbojet and turbofan engines, with the possibility to customize the parameters. The main parameters that can be modified are: the rotational speed of the shaft/s, the temperature at the inlet of the turbine/s, the efficiency of compressor/s and turbine/s (HP and LP) and the compressor/s pressure ratio. The results are automatically written inside the configuration file of the module `SU2Run` to be able to perform the calculations. ## Inputs -`ThermoData` can be run on is own by giving the altitude the Mach number and the Net force. Otherwise it can take as an input the values from `CPACS2GMSH` module. +`ThermoData` can be run on is own by giving an Aeromap that contains Altitude and Mach number with the addition of the Net force that needs to be chosen. Otherwise it can take as an input the values from `CPACS2GMSH` module. ## Analyses `ThermoData` compute the values obtained at the engine outlet giving a "EngineBC.dat" file as an output. if the workflow continues with the `SU2Run` run module the results are added to the config file to perform the simulation. ## Outputs -`ThermoData` output is the "EngineBC.dat" file with stored inside: T_tot_out, V_stat_out, MN_out, P_tot_out, massflow_stat_out, T_stat_out, P_stat_out for the chosen engine configuration. +`ThermoData` output is the "EngineBC.dat" file with stored inside: +* T_tot_out= Nozzle total temperature outlet[K], +* T_stat_out= Nozzle static temperature outlet[K], +* P_tot_out= Nozzle total pressure outlet [Pa], +* P_stat_out= Nozzle static pressure outlet [Pa]. +* V_stat_out= Nozzle static velocity outlet[m/s], +* MN_out= Nozzle Mach number outlet [adim], +* massflow_stat_out= Nozzle massflow outlet [Kg/s], + ## Installation or requirements `ThermoData` needs the installation of the openmdao and pycycle suite that are included in the python environment of CEASIOMpy. From bef87b6cc80b7bd56cc25d8a0457156ecb2e066b Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Thu, 22 Feb 2024 09:56:24 +0100 Subject: [PATCH 40/55] ThermoData README changes --- ceasiompy/ThermoData/README.md | 20 +++++++++++++------- 1 file changed, 13 insertions(+), 7 deletions(-) diff --git a/ceasiompy/ThermoData/README.md b/ceasiompy/ThermoData/README.md index f8c58d3a9..487f2aa30 100644 --- a/ceasiompy/ThermoData/README.md +++ b/ceasiompy/ThermoData/README.md @@ -6,31 +6,32 @@ **State**: :heavy_check_mark: - -
-`ThermoData` is a module to provide the outlet conditions of a given engine. It can calculate different operating conditions and save the results in a text file. This module is derived starting from the OpenSource code [pyCycle](https://github.com/OpenMDAO/pycycle) developed by Eric S. Hendricks and Justin S. Gray. It can perform calculations on both turbojet and turbofan engines, with the possibility to customize the parameters. The main parameters that can be modified are: the rotational speed of the shaft/s, the temperature at the inlet of the turbine/s, the efficiency of compressor/s and turbine/s (HP and LP) and the compressor/s pressure ratio. The results are automatically written inside the configuration file of the module `SU2Run` to be able to perform the calculations. +`ThermoData` is a module to provide the outlet conditions of a given engine. It can calculate different operating conditions and save the results in a text file. This module is derived starting from the OpenSource code [pyCycle](https://github.com/OpenMDAO/pycycle) developed by Eric S. Hendricks and Justin S. Gray. It can perform calculations on both turbojet and turbofan engines, with the possibility to customize the parameters. The main parameters that can be modified are: the rotational speed of the shaft/s, the temperature at the inlet of the turbine/s, the efficiency of compressor/s and turbine/s (HP and LP) and the compressor/s pressure ratio. The results are automatically written inside the configuration file of the module `SU2Run` to be able to perform the CFD calculations if needed. ## Inputs `ThermoData` can be run on is own by giving an Aeromap that contains Altitude and Mach number with the addition of the Net force that needs to be chosen. Otherwise it can take as an input the values from `CPACS2GMSH` module. ## Analyses -`ThermoData` compute the values obtained at the engine outlet giving a "EngineBC.dat" file as an output. if the workflow continues with the `SU2Run` run module the results are added to the config file to perform the simulation. +`ThermoData` compute the values obtained at the engine outlet giving a "EngineBC.dat" file as an output. If the workflow continues with the `SU2Run` run module the results are added to the config file of `SU2` to perform the simulation. ## Outputs -`ThermoData` output is the "EngineBC.dat" file with stored inside: +`ThermoData` output is the "EngineBC.dat" file with stored inside for the turbojet engine: * T_tot_out= Nozzle total temperature outlet[K], * T_stat_out= Nozzle static temperature outlet[K], * P_tot_out= Nozzle total pressure outlet [Pa], * P_stat_out= Nozzle static pressure outlet [Pa]. * V_stat_out= Nozzle static velocity outlet[m/s], * MN_out= Nozzle Mach number outlet [adim], -* massflow_stat_out= Nozzle massflow outlet [Kg/s], +* massflow_stat_out= Nozzle massflow outlet [Kg/s]\\ + +For the turbofan engine are added also the values at the exit of the bypass nozzle. + ## Installation or requirements -`ThermoData` needs the installation of the openmdao and pycycle suite that are included in the python environment of CEASIOMpy. +`ThermoData` needs the installation of the openMDAO and pycycle suite that are included in the python environment of CEASIOMpy. ## Limitations @@ -42,3 +43,8 @@ To be able to change the engine parameters other than those given as input (alti * [OpenMDAO documentation ](https://openmdao.org/newdocs/versions/latest/main.html) +* [SU2 website](https://su2code.github.io/) + +* [SU2 Github repository](https://github.com/su2code/SU2) + + From 9deb3f1131284ed973d8a2f51c90c52a6653bc0d Mon Sep 17 00:00:00 2001 From: GBenedett <113425078+GBenedett@users.noreply.github.com> Date: Thu, 22 Feb 2024 12:10:39 +0100 Subject: [PATCH 41/55] Update README.md --- ceasiompy/CPACS2GMSH/README.md | 2 +- 1 file changed, 1 insertion(+), 1 deletion(-) diff --git a/ceasiompy/CPACS2GMSH/README.md b/ceasiompy/CPACS2GMSH/README.md index 37b8fc312..f80e80ab2 100644 --- a/ceasiompy/CPACS2GMSH/README.md +++ b/ceasiompy/CPACS2GMSH/README.md @@ -40,7 +40,7 @@ Multiple options are available with `CPACS2GMSH`, you can see these options if y General options: -* `Display mesh with GMSHl : False` +* `Display mesh with GMSH : False` Open the gmsh GUI after the generation of the surface mesh (2D) and the domain mesh (3D). This option is usefully to control the quality of the automated generated mesh or make extra operation with gmsh GUI. Domain: From 4e6404e77b34ebdd68b082fa944dc3ae1dacbae8 Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Thu, 22 Feb 2024 12:12:00 +0100 Subject: [PATCH 42/55] small change to README --- ceasiompy/ThermoData/README.md | 2 +- 1 file changed, 1 insertion(+), 1 deletion(-) diff --git a/ceasiompy/ThermoData/README.md b/ceasiompy/ThermoData/README.md index 487f2aa30..a4bd6082f 100644 --- a/ceasiompy/ThermoData/README.md +++ b/ceasiompy/ThermoData/README.md @@ -14,7 +14,7 @@ `ThermoData` can be run on is own by giving an Aeromap that contains Altitude and Mach number with the addition of the Net force that needs to be chosen. Otherwise it can take as an input the values from `CPACS2GMSH` module. ## Analyses -`ThermoData` compute the values obtained at the engine outlet giving a "EngineBC.dat" file as an output. If the workflow continues with the `SU2Run` run module the results are added to the config file of `SU2` to perform the simulation. +`ThermoData` compute the values obtained at the engine outlet giving a "EngineBC.dat" file as an output. If the workflow continues with the `SU2Run` run module the results are added to the config file of SU2 to perform the simulation. ## Outputs `ThermoData` output is the "EngineBC.dat" file with stored inside for the turbojet engine: From 2cbbfcf69f2e13e6166eff45bb543ade18d6f299 Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Fri, 23 Feb 2024 12:11:21 +0100 Subject: [PATCH 43/55] adding automatic reynolds calculation --- ceasiompy/SU2Run/func/su2config_rans.py | 18 ++++++++++++++++++ 1 file changed, 18 insertions(+) diff --git a/ceasiompy/SU2Run/func/su2config_rans.py b/ceasiompy/SU2Run/func/su2config_rans.py index b650ae83e..e2bfa35bc 100644 --- a/ceasiompy/SU2Run/func/su2config_rans.py +++ b/ceasiompy/SU2Run/func/su2config_rans.py @@ -320,6 +320,22 @@ def add_thermodata(cfg, cpacs, alt, case_nb, alt_list): ) +def add_reynods_number(alt, mach, cfg): + + Atm = Atmosphere(alt) + + # Get speed from Mach Number + speed = mach * Atm.speed_of_sound[0] + print(speed) + print(Atm.kinematic_viscosity[0]) + log.info(f"Mach number: {mach} [-] -> Velocity: {round(speed)} [m/s]") + + # Reynolds number based on the ratio Wetted Area / Wing Span + reynolds = 1 * speed / Atm.kinematic_viscosity[0] + print(reynolds) + cfg["REYNOLDS_NUMBER"] = int(reynolds) + + def generate_su2_cfd_config_rans(cpacs_path, cpacs_out_path, wkdir): """Function to create SU2 config file. @@ -501,6 +517,8 @@ def generate_su2_cfd_config_rans(cpacs_path, cpacs_out_path, wkdir): add_thermodata(cfg, cpacs, alt, case_nb, alt_list) + add_reynods_number(alt, mach, cfg) + case_dir_path = Path(wkdir, case_dir_name) if not case_dir_path.exists(): case_dir_path.mkdir() From c0406e995ff14ec7b5d28291d7ed5fd4ff97740d Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Fri, 23 Feb 2024 12:23:39 +0100 Subject: [PATCH 44/55] improving the code --- ceasiompy/SU2Run/func/su2config_rans.py | 5 +---- 1 file changed, 1 insertion(+), 4 deletions(-) diff --git a/ceasiompy/SU2Run/func/su2config_rans.py b/ceasiompy/SU2Run/func/su2config_rans.py index e2bfa35bc..4eca907d9 100644 --- a/ceasiompy/SU2Run/func/su2config_rans.py +++ b/ceasiompy/SU2Run/func/su2config_rans.py @@ -326,13 +326,10 @@ def add_reynods_number(alt, mach, cfg): # Get speed from Mach Number speed = mach * Atm.speed_of_sound[0] - print(speed) - print(Atm.kinematic_viscosity[0]) - log.info(f"Mach number: {mach} [-] -> Velocity: {round(speed)} [m/s]") # Reynolds number based on the ratio Wetted Area / Wing Span reynolds = 1 * speed / Atm.kinematic_viscosity[0] - print(reynolds) + log.info(f"Reynolds number= {int(reynolds)}") cfg["REYNOLDS_NUMBER"] = int(reynolds) From b2146a0145a6c0ed1124f2fffa1a9bfdceaffceb Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Tue, 27 Feb 2024 12:09:50 +0100 Subject: [PATCH 45/55] adding reynolds number calculation --- ceasiompy/SU2Run/func/su2config_rans.py | 12 ++++++++---- 1 file changed, 8 insertions(+), 4 deletions(-) diff --git a/ceasiompy/SU2Run/func/su2config_rans.py b/ceasiompy/SU2Run/func/su2config_rans.py index 4eca907d9..77b6bbeb6 100644 --- a/ceasiompy/SU2Run/func/su2config_rans.py +++ b/ceasiompy/SU2Run/func/su2config_rans.py @@ -32,6 +32,7 @@ write_actuator_disk_data, write_header, ) +from ceasiompy.CPACS2GMSH.func.mesh_sizing import wings_size from ceasiompy.SU2Run.func.su2utils import get_mesh_markers, get_su2_config_template_rans from ceasiompy.utils.ceasiomlogger import get_logger from ceasiompy.utils.commonnames import ( @@ -320,15 +321,18 @@ def add_thermodata(cfg, cpacs, alt, case_nb, alt_list): ) -def add_reynods_number(alt, mach, cfg): +def add_reynods_number(alt, mach, cfg, cpacs_path): Atm = Atmosphere(alt) # Get speed from Mach Number speed = mach * Atm.speed_of_sound[0] - # Reynolds number based on the ratio Wetted Area / Wing Span - reynolds = 1 * speed / Atm.kinematic_viscosity[0] + ref_chord = wings_size(cpacs_path)[0] / 0.15 + print(ref_chord) + + # Reynolds number based on the mean chord + reynolds = ref_chord * speed / Atm.kinematic_viscosity[0] log.info(f"Reynolds number= {int(reynolds)}") cfg["REYNOLDS_NUMBER"] = int(reynolds) @@ -514,7 +518,7 @@ def generate_su2_cfd_config_rans(cpacs_path, cpacs_out_path, wkdir): add_thermodata(cfg, cpacs, alt, case_nb, alt_list) - add_reynods_number(alt, mach, cfg) + add_reynods_number(alt, mach, cfg, cpacs_path) case_dir_path = Path(wkdir, case_dir_name) if not case_dir_path.exists(): From 95095c6f5b0ed553c8144c7f2ed5059e781c32ad Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Thu, 14 Mar 2024 15:13:33 +0100 Subject: [PATCH 46/55] adding test --- .../tests/test_thermodata/test_thermodata.py | 114 ++++++++++++++++++ .../tests/test_turbofan/test_turbofan.py | 59 --------- .../ThermoData/tests/test_turbojet/test1.py | 44 ------- .../tests/test_turbojet/test_turbojet.py | 59 --------- 4 files changed, 114 insertions(+), 162 deletions(-) create mode 100644 ceasiompy/ThermoData/tests/test_thermodata/test_thermodata.py delete mode 100644 ceasiompy/ThermoData/tests/test_turbofan/test_turbofan.py delete mode 100644 ceasiompy/ThermoData/tests/test_turbojet/test1.py delete mode 100644 ceasiompy/ThermoData/tests/test_turbojet/test_turbojet.py diff --git a/ceasiompy/ThermoData/tests/test_thermodata/test_thermodata.py b/ceasiompy/ThermoData/tests/test_thermodata/test_thermodata.py new file mode 100644 index 000000000..badfab3a8 --- /dev/null +++ b/ceasiompy/ThermoData/tests/test_thermodata/test_thermodata.py @@ -0,0 +1,114 @@ +""" +CEASIOMpy: Conceptual Aircraft Design Software + +Developed by CFS ENGINEERING, 1015 Lausanne, Switzerland + +Test functions of 'ceasiompy/ThermoData/func/turbojet_func.py' + +Python version: >=3.8 + + +| Author : Francesco Marcucci +| Creation: 2024-02-09 + +""" +# ================================================================================================= +# IMPORTS +# ================================================================================================= + +from pathlib import Path + +import sys + +import pytest + +import numpy as np + +from ceasiompy.ThermoData.func.turbofan_func import ( + turbofan_analysis, + write_hbtf_file, +) + +from ceasiompy.ThermoData.func.turbojet_func import ( + turbojet_analysis, + write_turbojet_file, +) + +sys.path.append("/home/cfse/Stage_Francesco/Thermodata") + +# ================================================================================================= +# CLASSES +# ================================================================================================= + + +# ================================================================================================= +# FUNCTIONS +# ================================================================================================= + + +def test_turbojet_func(): + alt = 1000 + MN = 0.3 + Fn = 2000 + new_sol = turbojet_analysis(alt, MN, Fn) + correct_sol = np.array( + [ + 1006.6296749, + 798.79704119, + 1.50478324, + 326886.19429314, + 2.89168807, + 727.76800186, + 89874.50518856, + ] + ).reshape((7, 1)) + np.testing.assert_almost_equal(new_sol, correct_sol, 3) + + +""" + T_tot_out, + V_stat_out, + MN_out, + P_tot_out, + massflow_stat_out, + T_stat_out, + P_stat_out, + + + + +def test_write_turbojet_file(): + ll = 2 + + +def test_turbofan(): + alt = 4000 # [ft] + MN = 0.6 + # Fn = 11800 # [lbf] + new_sol_tf = turbofan_analysis(alt, MN) + correct_sol_tf = np.array( + [ + 8.11328662e01, + 3.44500820e02, + 1.00000000e00, + 4.19439630e02, + 5.64233274e01, + 1.08865912e-01, + ] + ).reshape((6, 1)) + np.testing.assert_almost_equal(new_sol_tf, correct_sol_tf, 5) + + +def test_write_hbtf_file(): + ll = 1 + +""" +# ================================================================================================= +# MAIN +# ================================================================================================= + +if __name__ == "__main__": + + print("Test configfile.py") + print("To run test use the following command:") + print(">> pytest -v") diff --git a/ceasiompy/ThermoData/tests/test_turbofan/test_turbofan.py b/ceasiompy/ThermoData/tests/test_turbofan/test_turbofan.py deleted file mode 100644 index 7b6469285..000000000 --- a/ceasiompy/ThermoData/tests/test_turbofan/test_turbofan.py +++ /dev/null @@ -1,59 +0,0 @@ -""" -CEASIOMpy: Conceptual Aircraft Design Software - -Developed by CFS ENGINEERING, 1015 Lausanne, Switzerland - -Test functions of 'ceasiompy/ThermoData/func/turbofan_func.py' - -Python version: >=3.8 - - -| Author : Francesco Marcucci -| Creation: 2024-02-09 - -""" -# ================================================================================================= -# IMPORTS -# ================================================================================================= - -import os -from pathlib import Path - -import pytest -from ceasiompy.SU2Run.func.su2results import save_screenshot -from ceasiompy.utils.commonpaths import TEST_RESULTS_FILES_PATH - -MODULE_DIR = Path(__file__).parent - - -# ================================================================================================= -# CLASSES -# ================================================================================================= - - -# ================================================================================================= -# FUNCTIONS -# ================================================================================================= - - -@pytest.mark.skipif("DISPLAY" not in os.environ, reason="requires display") -def test_save_screenshot(): - """Test the function 'save_screenshot'""" - - surface_flow_file = Path(TEST_RESULTS_FILES_PATH, "surface_flow.vtu") - screenshot_file = save_screenshot(surface_flow_file, "Mach") - assert screenshot_file.exists() - - if screenshot_file.exists(): - screenshot_file.unlink() - - -# ================================================================================================= -# MAIN -# ================================================================================================= - -if __name__ == "__main__": - - print("Test configfile.py") - print("To run test use the following command:") - print(">> pytest -v") diff --git a/ceasiompy/ThermoData/tests/test_turbojet/test1.py b/ceasiompy/ThermoData/tests/test_turbojet/test1.py deleted file mode 100644 index 96495a0e9..000000000 --- a/ceasiompy/ThermoData/tests/test_turbojet/test1.py +++ /dev/null @@ -1,44 +0,0 @@ -from pathlib import Path - -import sys - -import pytest - -import numpy as np - -from ceasiompy.ThermoData.func.turbofan_func import ( - turbofan_analysis, -) - -from ceasiompy.ThermoData.func.turbojet_func import ( - turbojet_analysis, -) - -sys.path.append("/home/cfse/Stage_Francesco/Thermodata") - - -def test_turbojet(): - alt = 4000 # [ft] - MN = 0.6 - Fn = 11800 # [lbf] - new_sol = turbojet_analysis(alt, MN, Fn) - correct_sol = np.array([717.59577021, 818.40663844, 1.57394908]).reshape((3, 1)) - np.testing.assert_almost_equal(new_sol, correct_sol, 5) - - -def test_turbofan(): - alt = 4000 # [ft] - MN = 0.6 - # Fn = 11800 # [lbf] - new_sol_tf = turbofan_analysis(alt, MN) - correct_sol_tf = np.array( - [ - 8.11328662e01, - 3.44500820e02, - 1.00000000e00, - 4.19439630e02, - 5.64233274e01, - 1.08865912e-01, - ] - ).reshape((6, 1)) - np.testing.assert_almost_equal(new_sol_tf, correct_sol_tf, 5) diff --git a/ceasiompy/ThermoData/tests/test_turbojet/test_turbojet.py b/ceasiompy/ThermoData/tests/test_turbojet/test_turbojet.py deleted file mode 100644 index c216e8855..000000000 --- a/ceasiompy/ThermoData/tests/test_turbojet/test_turbojet.py +++ /dev/null @@ -1,59 +0,0 @@ -""" -CEASIOMpy: Conceptual Aircraft Design Software - -Developed by CFS ENGINEERING, 1015 Lausanne, Switzerland - -Test functions of 'ceasiompy/ThermoData/func/turbojet_func.py' - -Python version: >=3.8 - - -| Author : Francesco Marcucci -| Creation: 2024-02-09 - -""" -# ================================================================================================= -# IMPORTS -# ================================================================================================= - -import os -from pathlib import Path - -import pytest -from ceasiompy.SU2Run.func.su2results import save_screenshot -from ceasiompy.utils.commonpaths import TEST_RESULTS_FILES_PATH - -MODULE_DIR = Path(__file__).parent - - -# ================================================================================================= -# CLASSES -# ================================================================================================= - - -# ================================================================================================= -# FUNCTIONS -# ================================================================================================= - - -@pytest.mark.skipif("DISPLAY" not in os.environ, reason="requires display") -def test_save_screenshot(): - """Test the function 'save_screenshot'""" - - surface_flow_file = Path(TEST_RESULTS_FILES_PATH, "surface_flow.vtu") - screenshot_file = save_screenshot(surface_flow_file, "Mach") - assert screenshot_file.exists() - - if screenshot_file.exists(): - screenshot_file.unlink() - - -# ================================================================================================= -# MAIN -# ================================================================================================= - -if __name__ == "__main__": - - print("Test configfile.py") - print("To run test use the following command:") - print(">> pytest -v") From afddc940c1d9dc3823c75c89c83e880f3903ced1 Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Thu, 14 Mar 2024 15:17:53 +0100 Subject: [PATCH 47/55] changing folders --- .../ThermoData/tests/{test_thermodata => }/test_thermodata.py | 0 1 file changed, 0 insertions(+), 0 deletions(-) rename ceasiompy/ThermoData/tests/{test_thermodata => }/test_thermodata.py (100%) diff --git a/ceasiompy/ThermoData/tests/test_thermodata/test_thermodata.py b/ceasiompy/ThermoData/tests/test_thermodata.py similarity index 100% rename from ceasiompy/ThermoData/tests/test_thermodata/test_thermodata.py rename to ceasiompy/ThermoData/tests/test_thermodata.py From 35645df10132bada538cba7e50736ef0e440c3c1 Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Fri, 15 Mar 2024 15:02:46 +0100 Subject: [PATCH 48/55] improving tests --- ceasiompy/ThermoData/tests/test_thermodata.py | 60 ++++++++++--------- 1 file changed, 31 insertions(+), 29 deletions(-) diff --git a/ceasiompy/ThermoData/tests/test_thermodata.py b/ceasiompy/ThermoData/tests/test_thermodata.py index badfab3a8..3c79da16e 100644 --- a/ceasiompy/ThermoData/tests/test_thermodata.py +++ b/ceasiompy/ThermoData/tests/test_thermodata.py @@ -22,6 +22,8 @@ import pytest +import os + import numpy as np from ceasiompy.ThermoData.func.turbofan_func import ( @@ -65,44 +67,44 @@ def test_turbojet_func(): np.testing.assert_almost_equal(new_sol, correct_sol, 3) -""" - T_tot_out, - V_stat_out, - MN_out, - P_tot_out, - massflow_stat_out, - T_stat_out, - P_stat_out, +def test_write_turbojet_file(tmp_path): + T_tot_out = 300 + V_stat_out = 200 + MN_out = 0.5 + P_tot_out = 100000 + massflow_stat_out = 50 + T_stat_out = 400 + P_stat_out = 200000 + test_thermodata_path = Path(tmp_path, "EngineBC.dat") + with open(test_thermodata_path, "w") as file: + write_turbojet_file( + file, + T_tot_out, + V_stat_out, + MN_out, + P_tot_out, + massflow_stat_out, + T_stat_out, + P_stat_out, + ) + with open(test_thermodata_path, "r") as file: + content = [ + line.strip() for line in file.readlines() + ] # Rimuovi il carattere di nuova linea -def test_write_turbojet_file(): - ll = 2 + content.append("") + print("Contenuto letto dal file:", content) -def test_turbofan(): - alt = 4000 # [ft] - MN = 0.6 - # Fn = 11800 # [lbf] - new_sol_tf = turbofan_analysis(alt, MN) - correct_sol_tf = np.array( - [ - 8.11328662e01, - 3.44500820e02, - 1.00000000e00, - 4.19439630e02, - 5.64233274e01, - 1.08865912e-01, - ] - ).reshape((6, 1)) - np.testing.assert_almost_equal(new_sol_tf, correct_sol_tf, 5) + expected_content = test_thermodata_path.read_text().split("\n") + print("Contenuto atteso:", expected_content) + assert test_thermodata_path.read_text().split("\n") == content -def test_write_hbtf_file(): - ll = 1 -""" # ================================================================================================= # MAIN # ================================================================================================= From a8317a176237700e253a75669276b065e19d497d Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Fri, 15 Mar 2024 15:13:36 +0100 Subject: [PATCH 49/55] improving_test --- ceasiompy/ThermoData/tests/test_thermodata.py | 12 ++++-------- 1 file changed, 4 insertions(+), 8 deletions(-) diff --git a/ceasiompy/ThermoData/tests/test_thermodata.py b/ceasiompy/ThermoData/tests/test_thermodata.py index 3c79da16e..c38c00eab 100644 --- a/ceasiompy/ThermoData/tests/test_thermodata.py +++ b/ceasiompy/ThermoData/tests/test_thermodata.py @@ -91,16 +91,12 @@ def test_write_turbojet_file(tmp_path): ) with open(test_thermodata_path, "r") as file: - content = [ - line.strip() for line in file.readlines() - ] # Rimuovi il carattere di nuova linea - + content = [line.strip() for line in file.readlines()] content.append("") - print("Contenuto letto dal file:", content) - - expected_content = test_thermodata_path.read_text().split("\n") - print("Contenuto atteso:", expected_content) + # print("content=", content) + # expected_content = test_thermodata_path.read_text().split("\n") + # print("expected_content=", expected_content) assert test_thermodata_path.read_text().split("\n") == content From 48581e1dfec6fd50a37b27c73ef4aa27f3a46e04 Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Mon, 18 Mar 2024 11:42:50 +0100 Subject: [PATCH 50/55] fixing codacy issues --- ceasiompy/ThermoData/tests/test_thermodata.py | 9 --------- 1 file changed, 9 deletions(-) diff --git a/ceasiompy/ThermoData/tests/test_thermodata.py b/ceasiompy/ThermoData/tests/test_thermodata.py index c38c00eab..741f8dab8 100644 --- a/ceasiompy/ThermoData/tests/test_thermodata.py +++ b/ceasiompy/ThermoData/tests/test_thermodata.py @@ -20,17 +20,8 @@ import sys -import pytest - -import os - import numpy as np -from ceasiompy.ThermoData.func.turbofan_func import ( - turbofan_analysis, - write_hbtf_file, -) - from ceasiompy.ThermoData.func.turbojet_func import ( turbojet_analysis, write_turbojet_file, From 39f1a3e604542129125d27bbba244c9952756b09 Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Mon, 18 Mar 2024 15:30:04 +0100 Subject: [PATCH 51/55] finishing test implementation --- ceasiompy/ThermoData/tests/test_thermodata.py | 77 +++++++++++++++++++ 1 file changed, 77 insertions(+) diff --git a/ceasiompy/ThermoData/tests/test_thermodata.py b/ceasiompy/ThermoData/tests/test_thermodata.py index 741f8dab8..882161e32 100644 --- a/ceasiompy/ThermoData/tests/test_thermodata.py +++ b/ceasiompy/ThermoData/tests/test_thermodata.py @@ -27,6 +27,11 @@ write_turbojet_file, ) +from ceasiompy.ThermoData.func.turbofan_func import ( + turbofan_analysis, + write_hbtf_file, +) + sys.path.append("/home/cfse/Stage_Francesco/Thermodata") # ================================================================================================= @@ -92,6 +97,78 @@ def test_write_turbojet_file(tmp_path): assert test_thermodata_path.read_text().split("\n") == content +def test_turbofan_func(): + alt = 1000 + MN = 0.3 + Fn = 2000 + new_sol_tuple = turbofan_analysis(alt, MN, Fn) + new_sol = np.concatenate(new_sol_tuple) + correct_sol = np.array( + [ + 65.04136793, + 323.23292298, + 0.95295201, + 161198.12289882, + 1.78761453, + 13.08931717, + 1270.61685498, + 724.51083329, + 1.0, + 964349.32127573, + 1.42155524, + 1139.22870449, + ] + ) + print(new_sol) + print("hello") + print(correct_sol) + np.testing.assert_almost_equal(new_sol, correct_sol, 3) + + +def test_write_hbtf_file(tmp_path): + T_tot_out_core = 300 + V_stat_out_core = 200 + MN_out_core = 0.5 + P_tot_out_core = 100000 + massflow_out_core = 50 + T_stat_out_core = 400 + T_tot_out_byp = 200000 + V_stat_out_byp = 300 + MN_out_byp = 1.2 + P_tot_out_byp = 100000 + massflow_stat_out_byp = 1.6 + T_stat_out_byp = 13 + + test_thermodata_path = Path(tmp_path, "EngineBC.dat") + + with open(test_thermodata_path, "w") as file: + write_hbtf_file( + file, + T_tot_out_core, + V_stat_out_core, + MN_out_core, + P_tot_out_core, + massflow_out_core, + T_stat_out_core, + T_tot_out_byp, + V_stat_out_byp, + MN_out_byp, + P_tot_out_byp, + massflow_stat_out_byp, + T_stat_out_byp, + ) + + with open(test_thermodata_path, "r") as file: + content = [line.strip() for line in file.readlines()] + content.append("") + + print("content=", content) + expected_content = test_thermodata_path.read_text().split("\n") + print("expected_content=", expected_content) + + assert test_thermodata_path.read_text().split("\n") == content + + # ================================================================================================= # MAIN # ================================================================================================= From 2ac0da9c444e7372b17477de00fd034bb3051220 Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Mon, 18 Mar 2024 15:43:23 +0100 Subject: [PATCH 52/55] adding comments to tests --- ceasiompy/ThermoData/tests/test_thermodata.py | 13 +++++-------- 1 file changed, 5 insertions(+), 8 deletions(-) diff --git a/ceasiompy/ThermoData/tests/test_thermodata.py b/ceasiompy/ThermoData/tests/test_thermodata.py index 882161e32..38ba491a7 100644 --- a/ceasiompy/ThermoData/tests/test_thermodata.py +++ b/ceasiompy/ThermoData/tests/test_thermodata.py @@ -45,6 +45,7 @@ def test_turbojet_func(): + """Test function 'turbojet_analysis'""" alt = 1000 MN = 0.3 Fn = 2000 @@ -64,6 +65,7 @@ def test_turbojet_func(): def test_write_turbojet_file(tmp_path): + """Test function 'write_turbojet_file'""" T_tot_out = 300 V_stat_out = 200 MN_out = 0.5 @@ -98,6 +100,7 @@ def test_write_turbojet_file(tmp_path): def test_turbofan_func(): + """Test function 'turbofan_analysis'""" alt = 1000 MN = 0.3 Fn = 2000 @@ -119,13 +122,11 @@ def test_turbofan_func(): 1139.22870449, ] ) - print(new_sol) - print("hello") - print(correct_sol) np.testing.assert_almost_equal(new_sol, correct_sol, 3) def test_write_hbtf_file(tmp_path): + """Test function 'write_hbtf_file'""" T_tot_out_core = 300 V_stat_out_core = 200 MN_out_core = 0.5 @@ -162,10 +163,6 @@ def test_write_hbtf_file(tmp_path): content = [line.strip() for line in file.readlines()] content.append("") - print("content=", content) - expected_content = test_thermodata_path.read_text().split("\n") - print("expected_content=", expected_content) - assert test_thermodata_path.read_text().split("\n") == content @@ -175,6 +172,6 @@ def test_write_hbtf_file(tmp_path): if __name__ == "__main__": - print("Test configfile.py") + print("Test ThermoData") print("To run test use the following command:") print(">> pytest -v") From dd968dd062cd8cb704da3571d586ac82661ca5d8 Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Wed, 20 Mar 2024 10:28:23 +0100 Subject: [PATCH 53/55] adding default aeromap to ThermoData module --- ceasiompy/ThermoData/thermodata.py | 13 +++++++++++++ 1 file changed, 13 insertions(+) diff --git a/ceasiompy/ThermoData/thermodata.py b/ceasiompy/ThermoData/thermodata.py index e69e1f594..42989dfd3 100644 --- a/ceasiompy/ThermoData/thermodata.py +++ b/ceasiompy/ThermoData/thermodata.py @@ -84,8 +84,21 @@ def thermo_data_run(cpacs_path, cpacs_out_path, wkdir): Fn = get_value_or_default(tixi, RANGE_XPATH + "/NetForce", 2000) + """Creating a default Aeromap to be used when one is not defined""" + default_aeromap = cpacs.create_aeromap("DefaultAeromap") + default_aeromap.description = "AeroMap created automatically" + mach = get_value_or_default(cpacs.tixi, RANGE_XPATH + "/cruiseMach", 0.3) + alt = get_value_or_default(cpacs.tixi, RANGE_XPATH + "/cruiseAltitude", 10000) + default_aeromap.add_row(alt=alt, mach=mach, aos=0.0, aoa=0.0) + default_aeromap.save() + alt_list = [alt] + mach_list = [mach] + aeromap_uid = get_value_or_default(cpacs.tixi, SU2_AEROMAP_UID_XPATH, "DefaultAeromap") + log.info(f"{aeromap_uid} has been created") + aeromap_list = cpacs.get_aeromap_uid_list() + """Executing the code by taking the correct Aeromap""" if aeromap_list: aeromap_default = aeromap_list[0] log.info(f"The aeromap is {aeromap_default}") From 3a3bda32c7226d8dd1b5825df9642bfeb1f0feb3 Mon Sep 17 00:00:00 2001 From: Francesco-Marcucci Date: Wed, 20 Mar 2024 10:34:26 +0100 Subject: [PATCH 54/55] solving codacy issues --- ceasiompy/ThermoData/thermodata.py | 2 -- 1 file changed, 2 deletions(-) diff --git a/ceasiompy/ThermoData/thermodata.py b/ceasiompy/ThermoData/thermodata.py index 42989dfd3..9b31e3b5c 100644 --- a/ceasiompy/ThermoData/thermodata.py +++ b/ceasiompy/ThermoData/thermodata.py @@ -84,7 +84,6 @@ def thermo_data_run(cpacs_path, cpacs_out_path, wkdir): Fn = get_value_or_default(tixi, RANGE_XPATH + "/NetForce", 2000) - """Creating a default Aeromap to be used when one is not defined""" default_aeromap = cpacs.create_aeromap("DefaultAeromap") default_aeromap.description = "AeroMap created automatically" mach = get_value_or_default(cpacs.tixi, RANGE_XPATH + "/cruiseMach", 0.3) @@ -98,7 +97,6 @@ def thermo_data_run(cpacs_path, cpacs_out_path, wkdir): aeromap_list = cpacs.get_aeromap_uid_list() - """Executing the code by taking the correct Aeromap""" if aeromap_list: aeromap_default = aeromap_list[0] log.info(f"The aeromap is {aeromap_default}") From 2611e15f5c3bc965316a07693a545084a7b4b305 Mon Sep 17 00:00:00 2001 From: GBenedett Date: Mon, 15 Apr 2024 08:56:45 +0200 Subject: [PATCH 55/55] cpacs file removed --- test_files/CPACSfiles/busjet0903mod.xml | 2975 ------- test_files/CPACSfiles/concorde1014.xml | 2263 ------ test_files/CPACSfiles/j280904scaled.xml | 3096 ------- test_files/CPACSfiles/j35vort0903cfscaled.xml | 7140 ----------------- test_files/CPACSfiles/labARscaled.xml | 933 --- 5 files changed, 16407 deletions(-) delete mode 100644 test_files/CPACSfiles/busjet0903mod.xml delete mode 100644 test_files/CPACSfiles/concorde1014.xml delete mode 100644 test_files/CPACSfiles/j280904scaled.xml delete mode 100644 test_files/CPACSfiles/j35vort0903cfscaled.xml delete mode 100644 test_files/CPACSfiles/labARscaled.xml diff --git a/test_files/CPACSfiles/busjet0903mod.xml b/test_files/CPACSfiles/busjet0903mod.xml deleted file mode 100644 index 4dddaa07e..000000000 --- a/test_files/CPACSfiles/busjet0903mod.xml +++ /dev/null @@ -1,2975 +0,0 @@ - - -
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