def test_geom_validity_fourier(a, b, baseRadius, branches):
json_interpreter = generate_data_layer()
combustion_table = json_interpreter.return_combustion_table()
# ------------ Define parameters:
geometric_params = {'L': 0.13,
'externalRadius': 88.5 / 2000,
'imagePixelSize': 2048,
'imageMeterSize': 0.09,
'regressionModel': Reg.MarxmanAndConstantFloodingRegimeModel(**combustion_table)}
shape_params = {'a': a,
'b': b,
'impact': 0.5,
'branches': branches,
'baseRadius': baseRadius,
'n': 20}
# ------------- Generate objects:
geometry_obj = Geom.SinglePortImageGeometry(**geometric_params)
geometry_obj.generatePolynom(**shape_params)
return geometry_obj.min_bloc_thickness() > 0.01
def test_1d_implementation_single_circular_port_balanced_nozzle():
""" test_1d_implementation_single_circular_port_balanced_nozzle intends
to test the implementation of the balanced nozzle based on the fixed point
method. """
# ------------ Generate the data-layer:
json_interpreter = generate_data_layer(
"Griffon Data - ABS - H2O2 - 36 bar.json")
combustion_table = json_interpreter.return_combustion_table()
# ------------ Define parameters:
geometric_params = {'L': 0.4, 'r_init': 0.03, 'r_ext': 0.05, 'N': 200}
nozzle_params = {
'At': 0.000589,
'expansion': 5.7,
'lambda_e': 0.98,
'erosion': 0
}
simulation_params = {
'ox_flow': 1.43,
'safety_thickness': 0.005,
'dt': 0.01,
'max_burn_time': None,
'tol_press': 1e-1
}
# ------------- Generate objects:
geometry_obj = Geom.SingleCircularPort1D(**geometric_params)
nozzle_obj = Noz.Nozzle(**nozzle_params)
regression_mod = Reg.MarxmanAndConstantFloodingRegimeModel(
**combustion_table)
# Instantiate the combustion module
combustion_obj = Combustion.CombustionObject1D(
json_interpreter=json_interpreter,
nozzle_object=nozzle_obj,
geometry_object=geometry_obj,
regression_model=regression_mod)
# -------------- Run simulation & Plot:
combustion_obj.run_balanced_nozzle_analysis(**simulation_params)
# Print the module
print(combustion_obj)
# Plot the results
combustion_obj.plot_results()
# Show plots
plt.show()
def test_combustion_image_geometry_fourier(a, b, baseRadius, branches, ox_flow):
""" Give the geometry mean Isp as an objective function """
# ------------ Generate Data Layer:
json_interpreter = generate_data_layer()
combustion_table = json_interpreter.return_combustion_table()
# ------------ Define parameters:
geometric_params = {'L': 0.13,
'externalRadius': 88.5 / 2000,
'imagePixelSize': 2048,
'imageMeterSize': 0.09,
'regressionModel': Reg.MarxmanAndConstantFloodingRegimeModel(**combustion_table)}
shape_params = {'a': a,
'b': b,
'impact' : 0.5,
'branches': branches,
'baseRadius': baseRadius,
'n': 20}
nozzle_params = {'At': 0.000038, 'expansion': 6.3, 'lambda_e': 0.98, 'erosion': 0}
simulation_params = {'ox_flow': ox_flow, 'safety_thickness': 0.005}
# ------------- Generate objects:
geometry_obj = Geom.SinglePortImageGeometry(**geometric_params)
geometry_obj.generateFourier(**shape_params)
#geometry_obj.draw_geometry()
nozzle_obj = Noz.Nozzle(**nozzle_params)
json_interpreter = generate_data_layer()
# Instantiate the combustion module
combustion_obj = CombustionObject(json_interpreter=json_interpreter,
geometry_object=geometry_obj,
nozzle_object=nozzle_obj)
# -------------- Run simulation
combustion_obj.run_simulation_constant_fuel_sliver_image_geometry(**simulation_params)
mean_isp = 0
if(len(combustion_obj.results["run_values"]['isp']) > 5):
for k in range(1, len(combustion_obj.results["run_values"]['isp'])):
mean_isp += combustion_obj.results["run_values"]['isp'][k] * (combustion_obj.results["run_values"]['time'][k] - combustion_obj.results["run_values"]['time'][k-1])
mean_isp = mean_isp / combustion_obj.results["run_values"]['time'][-1]
return mean_isp
def test_combustion_image_geometry():
""" perform the test over the combustion module """
# ------------ Generate Data Layer:
json_interpreter = generate_data_layer()
combustion_table = json_interpreter.return_combustion_table()
# ------------ Define parameters:
geometric_params = {'L': 0.4,
'externalRadius': 0.45,
'imagePixelSize': 2048,
'imageMeterSize': 0.1,
'regressionModel': Reg.MarxmanAndConstantFloodingRegimeModel(**combustion_table)}
shape_params = {'a' : [0.07552083333333333, -0.22916666666666666, 0.3151041666666667],
'b' : [],
'baseRadius' : 0.036,
'branches' : 8,
'impact' : 0.3,
'n' : 40}
nozzle_params = {'At': 0.000589, 'expansion': 5.7, 'lambda_e': 0.98, 'erosion': 0}
design_params = {'gamma': 1.27, 'p_chamber': 3200000, 'p_exit': 100000,
'c_star': 1500, 'ox_flow': 1., 'OF': 9}
simulation_params = {'ox_flow': 0.96875, 'safety_thickness': 0.000000001, 'max_burn_time' : 5, 'dt': 0.05}
# ------------- Generate objects:
geometry_obj = Geom.SinglePortImageGeometry(**geometric_params)
geometry_obj.generateFourier(**shape_params)
#geometry_obj.draw_geometry()
nozzle_obj = Noz.Nozzle(**nozzle_params)
nozzle_obj.set_design(**design_params)
json_interpreter = generate_data_layer()
# Instantiate the combustion module
combustion_obj = Comb.CombustionObjectImage(json_interpreter=json_interpreter,
geometry_object=geometry_obj,
nozzle_object=nozzle_obj)
# -------------- Run simulation & Plot:
combustion_obj.run_simulation_constant_fuel_sliver(**simulation_params)
# Print the module
print(combustion_obj)
# Plot the results
combustion_obj.plot_results()
def test_1d_implementation_single_circular_port():
""" 1D test of the Combustion Module 1D implementation """
# ------------ Generate the data-layer:
json_interpreter = generate_data_layer("Griffon Data - Mock.json")
combustion_table = json_interpreter.return_combustion_table()
# ------------ Define parameters:
geometric_params = {'L': 4.572, 'r_init': 0.152 / 2, 'r_ext': 0.5, 'N': 12}
nozzle_params = {
'At': 0.000589,
'expansion': 5.7,
'lambda_e': 0.98,
'erosion': 0
}
simulation_params = {
'ox_flow': 7.95,
'safety_thickness': 0.005,
'dt': 0.1,
'max_burn_time': 70,
'file_name': '../data/data_tests/myGeometry.txt',
'times': [0.1, 20, 60]
}
# ------------- Generate objects:
geometry_obj = Geom.SingleCircularPort1D(**geometric_params)
nozzle_obj = Noz.Nozzle(**nozzle_params)
regression_mod = Reg.SingleRegimeMarxmanModel(**combustion_table)
# Instantiate the combustion module
combustion_obj = Combustion.CombustionObject1D(
json_interpreter=json_interpreter,
nozzle_object=nozzle_obj,
geometry_object=geometry_obj,
regression_model=regression_mod)
# -------------- Run simulation & Plot:
combustion_obj.run_simulation_constant_fuel_sliver(**simulation_params)
# Print the module
print(combustion_obj)
# Plot the results
combustion_obj.plot_results()
# Show plots
plt.show()
def test_onera_three_port_geometry_with_center_port():
""" Study the potential evolution of the geometry associated to a Three Port Geometry
to be performed at ONERA. The characteristics of the Test are:
1. Three Port Geometry
2. Go range: TBD kg/m^2/sec
3. ox flow: same
4. Chamber pressure: 36 bar, closest possible to the target pressure of Griffon.
"""
# ------------ Generate the data layer:
json_interpreter = generate_data_layer() # Use same data-layer used for Griffon (same pressure)
combustion_table = json_interpreter.return_combustion_table()
# ------------ Define parameters:
# MultipleCircularPortsWithCircularCenter
# N, L, regressionModel, ringPortsIntialRadius, centralPortInitialRadius, r_ext
geometric_params = {'N': 4,
'L': 0.130,
'ringPortsIntialRadius': 9e-3 / 2,
'centralPortInitialRadius': 9e-3 / 2,
'r_ext': 94.5e-3 / 2,
'regressionModel': Reg.MarxmanAndConstantFloodingRegimeModel(**combustion_table)}
nozzle_params = {'At': 0.000038, 'expansion': 6.3, 'lambda_e': 0.98, 'erosion': 0}
simulation_params = {'ox_flow': 0.065, 'safety_thickness': 0.005, 'dt': 0.01, 'max_burn_time': 8}
# ------------- Generate objects:
geometry_obj = Geom.MultipleCircularPortsWithCircularCenter(**geometric_params)
geometry_obj.draw_geometry()
nozzle_obj = Noz.Nozzle(**nozzle_params)
json_interpreter = generate_data_layer(data_file="Thermodynamic Data Onera 41 bar H2O2 87_5.json")
# Instantiate the combustion module
combustion_obj = CombustionObject(json_interpreter=json_interpreter,
geometry_object=geometry_obj,
nozzle_object=nozzle_obj)
# -------------- Run simulation & Plot:
combustion_obj.run_simulation_constant_fuel_sliver(**simulation_params)
# Print the module
print(combustion_obj)
# Plot the results
combustion_obj.plot_results()
def define_onera_physical_hycom_14_test_combustion_object():
""" Define the ONERA physical test CombustionObject for Hycom 14 test
:return combustion object
"""
# ------------ Generate the data layer:
json_interpreter = generate_data_layer("DataLayerONERATests_Hycom14.json")
# Use same data-layer used for Griffon (same pressure)
combustion_table = json_interpreter.return_combustion_table()
# ------------ Define parameters:
geometric_params = {
'L': 0.130,
'rintInitial': 13.30e-3 / 2,
'rext0': 94.5e-3 / 2,
'regressionModel':
Reg.TwoRegimesMarxmanAndFloodedModel(**combustion_table)
}
nozzle_params = {
'At': (np.pi / 4) * 7.25e-3**2,
'expansion': 6.3,
'lambda_e': 0.98,
'erosion': 0
}
simulation_params = {
'ox_flow': 0.080,
'safety_thickness': 0.005,
'dt': 0.01,
'max_burn_time': 8.5
}
# ------------- Generate objects:
geometry_obj = Geom.OneCircularPort(**geometric_params)
nozzle_obj = Noz.Nozzle(**nozzle_params)
# Instantiate the combustion module
combustion_object = CombustionObjectClassic(
json_interpreter=json_interpreter,
geometry_object=geometry_obj,
nozzle_object=nozzle_obj)
# -------------- Run simulation & Plot:
combustion_object.run_simulation_constant_fuel_sliver(**simulation_params)
# Return the combustion object
return combustion_object
def test_onera_physical_test_1_2():
""" Study the potential evolution of the geometry associated to the 1st physical test
to be performed at ONERA (version at 36 bar). The characteristics of the Test are:
1. Single Port Geometry
2. Go range: [100 - etc] kg/m^2/sec
3. Chamber pressure: TBD, closest possible to the target pressure of Griffon.
"""
# ------------ Generate the data layer:
json_interpreter = generate_data_layer()
# Use same data-layer used for Griffon (same pressure)
combustion_table = json_interpreter.return_combustion_table()
# ------------ Define parameters:
geometric_params = {'L': 0.130,
'rintInitial': 0.015,
'rext0': 94.5e-3 / 2,
'regressionModel': Reg.MarxmanAndConstantFloodingRegimeModel(**combustion_table)}
nozzle_params = {'At': 0.000038, 'expansion': 6.3, 'lambda_e': 0.98, 'erosion': 0}
simulation_params = {'ox_flow': 0.07, 'safety_thickness': 0.005, 'dt': 0.01, 'max_burn_time': 8}
# ------------- Generate objects:
geometry_obj = Geom.OneCircularPort(**geometric_params)
nozzle_obj = Noz.Nozzle(**nozzle_params)
# Instantiate the combustion module
combustion_obj = CombustionObject(json_interpreter=json_interpreter,
geometry_object=geometry_obj,
nozzle_object=nozzle_obj)
# -------------- Run simulation & Plot:
combustion_obj.run_simulation_constant_fuel_sliver(**simulation_params)
# Print the module
print(combustion_obj)
# Plot the results
combustion_obj.plot_results()
def test_combustion():
""" perform the test over the combustion module """
# ------------ Generate Data Layer:
json_interpreter = generate_data_layer()
combustion_table = json_interpreter.return_combustion_table()
# ------------ Define parameters:
geometric_params = {'L': 0.4,
'rintInitial': 0.05,
'rext0': 0.07,
'regressionModel': Reg.MarxmanAndConstantFloodingRegimeModel(**combustion_table)}
nozzle_params = {'At': 0.000589, 'expansion': 5.7, 'lambda_e': 0.98, 'erosion': 0}
design_params = {'gamma': 1.27, 'p_chamber': 3200000, 'p_exit': 100000,
'c_star': 1500, 'ox_flow': 1.2, 'OF': 5}
simulation_params = {'ox_flow': 1.3, 'safety_thickness': 0.005, 'dt': 0.05}
# ------------- Generate objects:
geometry_obj = Geom.OneCircularPort(**geometric_params)
nozzle_obj = Noz.Nozzle(**nozzle_params)
nozzle_obj.set_design(**design_params)
json_interpreter = generate_data_layer()
# Instantiate the combustion module
combustion_obj = CombustionObjectClassic(json_interpreter=json_interpreter,
geometry_object=geometry_obj,
nozzle_object=nozzle_obj)
# -------------- Run simulation & Plot:
combustion_obj.run_simulation_constant_fuel_sliver(**simulation_params)
# Print the module
print(combustion_obj)
# Plot the results
combustion_obj.plot_results()
def test_combustion_onera_data():
""" perform the test over the combustion module but with Onera Test Data """
# ------------ Generate the data layer:
json_interpreter = generate_data_layer(data_file="Thermodynamic Data Onera 41 bar H2O2 87_5.json")
combustion_table = json_interpreter.return_combustion_table()
# ------------ Define parameters:
geometric_params = {'L': 0.235,
'rintInitial': 0.0186658954,
'rext0': 0.2,
'regressionModel': Reg.MarxmanAndConstantFloodingRegimeModel(**combustion_table)}
nozzle_params = {'At': 0.000038, 'expansion': 6.3, 'lambda_e': 0.98, 'erosion': 0}
simulation_params = {'ox_flow': 0.0855, 'safety_thickness': 0.005, 'dt': 0.05, 'max_burn_time': 8.25}
# ------------- Generate objects:
geometry_obj = Geom.OneCircularPort(**geometric_params)
nozzle_obj = Noz.Nozzle(**nozzle_params)
json_interpreter = generate_data_layer(data_file="Thermodynamic Data Onera 41 bar H2O2 87_5.json")
# Instantiate the combustion module
combustion_obj = CombustionObjectClassic(json_interpreter=json_interpreter,
geometry_object=geometry_obj,
nozzle_object=nozzle_obj)
# -------------- Run simulation & Plot:
combustion_obj.run_simulation_constant_fuel_sliver(**simulation_params)
# Print the module
print(combustion_obj)
# Plot the results
combustion_obj.plot_results()
def generate_combustion_parameters(combustion_init_dict, json_interpreter):
"""
generate_combustion_parameters performs all of the necessary calculations (if there are )required to set the
inputs for the combustion module
:param combustion_init_dict: dictionary containing the data required to prepare the inputs for the
combustion module.
:param json_interpreter: JsonInterpreter instance
:return: combustion_parameters dictionary
"""
# ------------- Generate the objects:
# Geometry
geometry_type = combustion_init_dict['geometric_params'].pop('type')
regression_obj = Reg.MarxmanAndConstantFloodingRegimeModel(
**json_interpreter.return_combustion_table())
combustion_init_dict['geometric_params'][
'regressionModel'] = regression_obj
geometry_obj = geometry_type(
**combustion_init_dict['geometric_params'])
if geometry_type == SinglePortImageGeometry:
geometry_obj.generateFourier(
**combustion_init_dict['shape_params'])
# Nozzle
nozzle_obj = Nozzle(**combustion_init_dict['nozzle_params'])
# Set the nozzle design
if combustion_init_dict['set_nozzle_design']:
nozzle_obj.set_design(**combustion_init_dict['design_params'])
# Return output
return {
'json_interpreter': json_interpreter,
'geometry_object': geometry_obj,
'nozzle_object': nozzle_obj
}
def define_onera_physical_hycom_16_test_combustion_object():
""" Define the ONERA physical test CombustionObject for Hycom 16 test
:return combustion object
"""
# ------------ Generate the data layer:
json_interpreter = generate_data_layer("DataLayerONERATests_Hycom16.json")
# Use same data-layer used for Griffon (same pressure)
combustion_table = json_interpreter.return_combustion_table()
# ------------ Define parameters:
shape_params = {
'polynom': [-0.2701822916666667, 0.15625, 0],
'baseRadius': 0.02,
'branches': 5,
'n': 50
}
geometric_params = {
'L': 0.130,
'externalRadius': 74.5 / 2000,
'imagePixelSize': 2048,
'imageMeterSize': 0.09,
'regressionModel':
Reg.TwoRegimesMarxmanAndFloodedModel(**combustion_table)
}
nozzle_params = {
'At': 4.243e-5,
'expansion': 6.3,
'lambda_e': 0.98,
'erosion': 0
}
simulation_params = {
'ox_flow': 0.0975,
'safety_thickness': 0.005,
'max_burn_time': 7.5
}
# ------------- Generate objects:
geometry_obj = Geom.SinglePortImageGeometry(**geometric_params)
geometry_obj.generatePolynom(**shape_params)
nozzle_obj = Noz.Nozzle(**nozzle_params)
# Instantiate the combustion module
combustion_object = CombustionObjectImage(
json_interpreter=json_interpreter,
geometry_object=geometry_obj,
nozzle_object=nozzle_obj)
# -------------- Run simulation & Plot:
combustion_object.run_simulation_constant_fuel_sliver_image_geometry(
**simulation_params)
# Return the combustion object
return combustion_object
