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_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 test_combustion_onera_data():
""" perform the test over the combustion module but with Onera Test Data """
# ------------ Define parameters:
geometric_params = {'L': 0.235, 'rintInitial': 0.0186658954, 'rext0': 0.2}
nozzle_params = {
'At': 0.000038,
'expansion': 6.3,
'lambda_e': 0.98,
'erosion': 0
}
design_params = {
'gamma': 1.27,
'p_chamber': 4000000,
'p_exit': 100000,
'c_star': 1500,
'isp': 230,
'thrust': 30000
}
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)
# nozzle_obj.set_design(**design_params) # Do not set the design of the nozzle
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 test_combustion():
""" perform the test over the combustion module """
# ------------ Define parameters:
geometric_params = {'L': 0.5, 'rintInitial': 0.04, 'rext0': 0.1}
nozzle_params = {
'At': 0.000589,
'expansion': 5.7,
'lambda_e': 0.98,
'erosion': 0
}
design_params = {
'gamma': 1.27,
'p_chamber': 4000000,
'p_exit': 100000,
'c_star': 1500,
'isp': 230,
'thrust': 30000
}
simulation_params = {'ox_flow': 6, '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 = 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_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()