def _build_problem(self, designed_stream=1, complex=False): p = Problem() p.model.set_input_defaults('start1.P', 9.218, units='psi') p.model.set_input_defaults('start1.T', 1524.32, units='degR') p.model.set_input_defaults('start1.MN', 0.4463) p.model.set_input_defaults('start1.W', 161.49, units='lbm/s') p.model.set_input_defaults('start2.P', 8.68, units='psi') p.model.set_input_defaults('start2.T', 524., units='degR') p.model.set_input_defaults('start2.MN', 0.4463) p.model.set_input_defaults('start2.W', 158., units='lbm/s') p.model.add_subsystem('start1', FlowStart(elements=AIR_FUEL_MIX)) p.model.add_subsystem('start2', FlowStart(elements=AIR_MIX)) p.model.add_subsystem( 'mixer', Mixer(design=True, designed_stream=designed_stream, Fl_I1_elements=AIR_FUEL_MIX, Fl_I2_elements=AIR_MIX)) connect_flow(p.model, 'start1.Fl_O', 'mixer.Fl_I1') connect_flow(p.model, 'start2.Fl_O', 'mixer.Fl_I2') p.setup(force_alloc_complex=complex) p.set_solver_print(level=-1) return p
def __init__(self): super(SteadyStateVacuum, self).__init__() des_vars = (('ram_recovery', 0.99), ('effDes', 0.8), ('duct_MN', 0.0), ('duct_dPqP', 0.), ('nozzle_Cfg', 1.0), ('nozzle_dPqP', 0.), ('shaft_Nmech', 10000.), ('inlet_MN', 0.0), ('comp_MN', 0.5), ('vehicle_mach', 0.8), ('Pa', 101.3e3, { 'units': 'Pa' })) self.add('input_vars', IndepVarComp(des_vars)) self.add('fl_start', FlowStart(thermo_data=janaf, elements=AIR_MIX)) # internal flow self.add('comp', Compressor(thermo_data=janaf, elements=AIR_MIX)) self.add('q', ExecComp('Prc = Pa/Ps'), promotes=['Prc', 'Pa']) self.add('q1', ExecComp('m_dot = 3*(A_tube*L_pod)*(1/pod_period)'), promotes=['m_dot', 'pod_period', 'A_tube', 'L_pod']) # connect components connect_flow(self, 'fl_start.Fl_O', 'comp.Fl_I') self.connect('input_vars.effDes', 'comp.map.effDes') self.connect('input_vars.comp_MN', 'comp.MN_target') self.connect('input_vars.shaft_Nmech', 'comp.Nmech') self.connect('input_vars.vehicle_mach', 'fl_start.MN_target') self.connect('input_vars.Pa', 'Pa') self.connect('Prc', 'comp.map.PRdes') self.connect('m_dot', 'fl_start.W') self.connect('fl_start.P', 'q.Ps')
def setUp(self): thermo = Thermo(janaf, AIR_FUEL_MIX) self.prob = Problem() self.prob.model.add_subsystem( 'flow_start', FlowStart(thermo_data=janaf, elements=AIR_MIX)) self.prob.model.add_subsystem( 'burner', Combustor(thermo_data=janaf, inflow_elements=AIR_MIX, air_fuel_elements=AIR_FUEL_MIX, fuel_type="JP-7")) self.prob.model.add_subsystem( 'turbine', Turbine(map_data=LPT2269, design=False, elements=AIR_FUEL_MIX)) self.prob.model.set_input_defaults('burner.MN', .01, units=None) self.prob.model.set_input_defaults('burner.Fl_I:FAR', .01, units=None) self.prob.model.set_input_defaults('turbine.Nmech', 1000., units='rpm'), self.prob.model.set_input_defaults('flow_start.P', 17., units='psi'), self.prob.model.set_input_defaults('flow_start.T', 500.0, units='degR'), self.prob.model.set_input_defaults('flow_start.W', 0., units='lbm/s'), self.prob.model.set_input_defaults('turbine.area', 150., units='inch**2') connect_flow(self.prob.model, "flow_start.Fl_O", "burner.Fl_I") connect_flow(self.prob.model, "burner.Fl_O", "turbine.Fl_I") self.prob.set_solver_print(level=-1) self.prob.setup(check=False)
def setUp(self): self.prob = Problem() des_vars = self.prob.model.add_subsystem('des_vars', IndepVarComp(), promotes=['*']) des_vars.add_output('P', 17., units='psi') des_vars.add_output('T', 500., units='degR') des_vars.add_output('MN', 0.5) des_vars.add_output('W', 10., units='lbm/s') des_vars.add_output('PR', 6.) des_vars.add_output('eff', 0.9) self.prob.model.connect("P", "flow_start.P") self.prob.model.connect("T", "flow_start.T") self.prob.model.connect("W", "flow_start.W") self.prob.model.connect("MN", "compressor.MN") self.prob.model.connect('PR', 'compressor.PR') self.prob.model.connect('eff', 'compressor.eff') self.prob.model.add_subsystem('flow_start', FlowStart(thermo_data=janaf, elements=AIR_MIX)) self.prob.model.add_subsystem('compressor', Compressor(design=True, elements=AIR_MIX)) connect_flow(self.prob.model, "flow_start.Fl_O", "compressor.Fl_I") self.prob.set_solver_print(level=-1) self.prob.setup(check=False)
def test_mix_diff(self): # mix two identical streams and make sure you get twice the area and the same total pressure thermo = Thermo(janaf, AIR_MIX) p = Problem() p.model.set_input_defaults('start1.P', 17., units='psi') p.model.set_input_defaults('start2.P', 15., units='psi') p.model.set_input_defaults('T', 500., units='degR') p.model.set_input_defaults('MN', 0.5) p.model.set_input_defaults('W', 100., units='lbm/s') p.model.add_subsystem('start1', FlowStart(), promotes=['MN', 'T', 'W']) p.model.add_subsystem('start2', FlowStart(), promotes=['MN', 'T', 'W']) p.model.add_subsystem( 'mixer', Mixer(design=True, Fl_I1_elements=AIR_MIX, Fl_I2_elements=AIR_MIX)) connect_flow(p.model, 'start1.Fl_O', 'mixer.Fl_I1') connect_flow(p.model, 'start2.Fl_O', 'mixer.Fl_I2') p.set_solver_print(level=-1) p.setup() p.run_model() tol = 2e-7 assert_near_equal(p['mixer.Fl_O:stat:area'], 653.2652635, tolerance=tol) assert_near_equal(p['mixer.Fl_O:tot:P'], 15.94216641, tolerance=tol) assert_near_equal(p['mixer.ER'], 1.1333333333, tolerance=tol)
def test_case1(self): thermo = Thermo(janaf, constants.AIR_MIX) self.prob = Problem() self.prob.model = Group() self.prob.model.add_subsystem('flow_start', FlowStart(thermo_data=janaf, elements=AIR_MIX), promotes=['MN', 'P', 'T']) self.prob.model.add_subsystem('duct', Duct(elements=AIR_MIX), promotes=['MN']) connect_flow(self.prob.model, 'flow_start.Fl_O', 'duct.Fl_I') self.prob.model.set_input_defaults('MN', 0.5) self.prob.model.set_input_defaults('duct.dPqP', 0.0) self.prob.model.set_input_defaults('P', 17., units='psi') self.prob.model.set_input_defaults('T', 500., units='degR') self.prob.model.set_input_defaults('flow_start.W', 500., units='lbm/s') self.prob.setup(check=False) self.prob.set_solver_print(level=-1) # 6 cases to check against for i, data in enumerate(ref_data): self.prob['duct.dPqP'] = data[h_map['dPqP']] # input flowstation self.prob['P'] = data[h_map['Fl_I.Pt']] self.prob['T'] = data[h_map['Fl_I.Tt']] self.prob['MN'] = data[h_map['Fl_O.MN']] self.prob['flow_start.W'] = data[h_map['Fl_I.W']] self.prob['duct.Fl_I:stat:V'] = data[h_map['Fl_I.V']] # give a decent initial guess for Ps print(i, self.prob['P'], self.prob['T'], self.prob['MN']) self.prob.run_model() # check outputs pt, ht, ps, ts = data[h_map['Fl_O.Pt']], data[h_map[ 'Fl_O.ht']], data[h_map['Fl_O.Ps']], data[h_map['Fl_O.Ts']] pt_computed = self.prob['duct.Fl_O:tot:P'] ht_computed = self.prob['duct.Fl_O:tot:h'] ps_computed = self.prob['duct.Fl_O:stat:P'] ts_computed = self.prob['duct.Fl_O:stat:T'] tol = 2.0e-2 assert_near_equal(pt_computed, pt, tol) assert_near_equal(ht_computed, ht, tol) assert_near_equal(ps_computed, ps, tol) assert_near_equal(ts_computed, ts, tol) check_element_partials(self, self.prob)
def setUp(self): self.prob = Problem() des_vars = self.prob.model.add_subsystem('des_vars', IndepVarComp(), promotes=['*']) des_vars.add_output('P', 17., units='psi') des_vars.add_output('T', 500., units='degR') des_vars.add_output('W', 0., units='lbm/s') des_vars.add_output('Nmech', 0., units='rpm') des_vars.add_output('area_targ', 50., units='inch**2') des_vars.add_output('s_PR', val=1.) des_vars.add_output('s_eff', val=1.) des_vars.add_output('s_Wc', val=1.) des_vars.add_output('s_Nc', val=1.) des_vars.add_output('alphaMap', val=0.) self.prob.model.connect("P", "flow_start.P") self.prob.model.connect("T", "flow_start.T") self.prob.model.connect("W", "flow_start.W") self.prob.model.connect("Nmech", "compressor.Nmech") self.prob.model.connect("area_targ", "compressor.area") self.prob.model.connect("s_PR", "compressor.s_PR") self.prob.model.connect("s_eff", "compressor.s_eff") self.prob.model.connect("s_Wc", "compressor.s_Wc") self.prob.model.connect("s_Nc", "compressor.s_Nc") self.prob.model.connect('alphaMap', 'compressor.map.alphaMap') self.prob.model.add_subsystem( 'flow_start', FlowStart(thermo_data=janaf, elements=AIR_MIX)) self.prob.model.add_subsystem( 'compressor', Compressor(map_data=AXI5, design=False, elements=AIR_MIX, map_extrap=False)) connect_flow(self.prob.model, "flow_start.Fl_O", "compressor.Fl_I") newton = self.prob.model.nonlinear_solver = NewtonSolver() newton.options['atol'] = 1e-8 newton.options['rtol'] = 1e-8 newton.options['iprint'] = 2 newton.options['maxiter'] = 10 newton.options['solve_subsystems'] = True newton.options['max_sub_solves'] = 10 newton.linesearch = BoundsEnforceLS() newton.linesearch.options['bound_enforcement'] = 'scalar' newton.linesearch.options['iprint'] = -1 self.prob.model.linear_solver = DirectSolver(assemble_jac=True) self.prob.set_solver_print(level=-1) self.prob.setup(check=False)
def setup_helper(self, NozzType, LossType): self.prob = Problem() self.prob.model = Group() des_vars = self.prob.model.add_subsystem('des_vars', IndepVarComp(), promotes=['*']) des_vars.add_output('Pt', 17.0, units='psi') des_vars.add_output('Tt', 500.0, units='degR') des_vars.add_output('W', 0.0, units='lbm/s') des_vars.add_output('MN', 0.2) des_vars.add_output('Ps_exhaust', 17.0, units='psi') des_vars.add_output('Cv', 0.99) des_vars.add_output('Cfg', 0.99) self.prob.model.add_subsystem( 'flow_start', FlowStart(thermo_data=janaf, elements=AIR_MIX)) self.prob.model.add_subsystem( 'nozzle', Nozzle(nozzType=NozzType, lossCoef=LossType, thermo_data=janaf, elements=AIR_MIX, internal_solver=True)) connect_flow(self.prob.model, "flow_start.Fl_O", "nozzle.Fl_I") self.prob.model.connect("Pt", "flow_start.P") self.prob.model.connect("Tt", "flow_start.T") self.prob.model.connect("W", "flow_start.W") self.prob.model.connect("MN", "flow_start.MN") self.prob.model.connect("Ps_exhaust", "nozzle.Ps_exhaust") if LossType == 'Cv': self.prob.model.connect("Cv", "nozzle.Cv") elif LossType == 'Cfg': self.prob.model.connect("Cfg", "nozzle.Cfg") # self.prob.model.connect("area_targ", "compressor.area") self.prob.set_solver_print(level=2) self.prob.setup(check=False) header = [ 'Cfg', 'Cv', 'PsExh', 'Fl_I.W', 'Fl_I.MN', 'Fl_I.s', 'Fl_I.Pt', 'Fl_I.Tt', 'Fl_I.ht', 'Fl_I.rhot', 'Fl_I.gamt', 'Fl_O.MN', 'Fl_O.s', 'Fl_O.Pt', 'Fl_O.Tt', 'Fl_O.ht', 'Fl_O.rhot', 'Fl_O.gamt', 'Fl_O.Ps', 'Fl_Th.MN', 'Fl_Th.s', 'Fl_Th.Pt', 'Fl_Th.Tt', 'Fl_Th.ht', 'Fl_Th.rhot', 'Fl_Th.gamt', 'Fl_Th.Ps', 'Fl_Th.Aphy', 'Fg', 'FgIdeal', 'Vactual', 'AthCold', 'AR', 'PR' ] self.h_map = dict(((v_name, i) for i, v_name in enumerate(header))) self.fpath = os.path.dirname(os.path.realpath(__file__))
def setup_helper(self, NozzType, LossType): thermo = Thermo(janaf, AIR_MIX) self.prob = Problem() self.prob.model = Group() self.prob.model.add_subsystem( 'flow_start', FlowStart(thermo_data=janaf, elements=AIR_MIX)) self.prob.model.add_subsystem( 'nozzle', Nozzle(nozzType=NozzType, lossCoef=LossType, thermo_data=janaf, elements=AIR_MIX, internal_solver=True)) self.prob.model.set_input_defaults('flow_start.P', 17.0, units='psi') self.prob.model.set_input_defaults('flow_start.T', 500.0, units='degR') self.prob.model.set_input_defaults('flow_start.MN', 0.2) self.prob.model.set_input_defaults('nozzle.Ps_exhaust', 17.0, units='psi') self.prob.model.set_input_defaults('flow_start.W', 0.0, units='lbm/s') connect_flow(self.prob.model, "flow_start.Fl_O", "nozzle.Fl_I") if LossType == 'Cv': self.prob.model.set_input_defaults('nozzle.Cv', 0.99) elif LossType == 'Cfg': self.prob.model.set_input_defaults('nozzle.Cfg', 0.99) self.prob.set_solver_print(level=2) self.prob.setup(check=False) header = [ 'Cfg', 'Cv', 'PsExh', 'Fl_I.W', 'Fl_I.MN', 'Fl_I.s', 'Fl_I.Pt', 'Fl_I.Tt', 'Fl_I.ht', 'Fl_I.rhot', 'Fl_I.gamt', 'Fl_O.MN', 'Fl_O.s', 'Fl_O.Pt', 'Fl_O.Tt', 'Fl_O.ht', 'Fl_O.rhot', 'Fl_O.gamt', 'Fl_O.Ps', 'Fl_Th.MN', 'Fl_Th.s', 'Fl_Th.Pt', 'Fl_Th.Tt', 'Fl_Th.ht', 'Fl_Th.rhot', 'Fl_Th.gamt', 'Fl_Th.Ps', 'Fl_Th.Aphy', 'Fg', 'FgIdeal', 'Vactual', 'AthCold', 'AR', 'PR' ] self.h_map = dict(((v_name, i) for i, v_name in enumerate(header))) self.fpath = os.path.dirname(os.path.realpath(__file__))
def setUp(self): thermo = Thermo(janaf, constants.AIR_MIX) self.prob = Problem() self.prob.model.add_subsystem( 'flow_start', FlowStart(thermo_data=janaf, elements=AIR_MIX)) self.prob.model.add_subsystem( 'compressor', Compressor(map_data=AXI5, design=False, elements=AIR_MIX, map_extrap=False)) self.prob.model.set_input_defaults('compressor.s_PR', val=1.) self.prob.model.set_input_defaults('compressor.s_eff', val=1.) self.prob.model.set_input_defaults('compressor.s_Wc', val=1.) self.prob.model.set_input_defaults('compressor.s_Nc', val=1.) self.prob.model.set_input_defaults('compressor.map.alphaMap', val=0.) self.prob.model.set_input_defaults('compressor.Nmech', 0., units='rpm') self.prob.model.set_input_defaults('flow_start.P', 17., units='psi') self.prob.model.set_input_defaults('flow_start.T', 500., units='degR') self.prob.model.set_input_defaults('flow_start.W', 0., units='lbm/s') self.prob.model.set_input_defaults('compressor.area', 50., units='inch**2') connect_flow(self.prob.model, "flow_start.Fl_O", "compressor.Fl_I") newton = self.prob.model.nonlinear_solver = NewtonSolver() newton.options['atol'] = 1e-8 newton.options['rtol'] = 1e-8 newton.options['iprint'] = 2 newton.options['maxiter'] = 10 newton.options['solve_subsystems'] = True newton.options['max_sub_solves'] = 10 newton.linesearch = BoundsEnforceLS() newton.linesearch.options['bound_enforcement'] = 'scalar' newton.linesearch.options['iprint'] = -1 self.prob.model.linear_solver = DirectSolver(assemble_jac=True) self.prob.set_solver_print(level=-1) self.prob.setup(check=False)
def _build_problem(self, designed_stream=1, complex=False): p = Problem() des_vars = p.model.add_subsystem('des_vars', IndepVarComp()) des_vars.add_output('P1', 9.218, units='psi') des_vars.add_output('T1', 1524.32, units='degR') des_vars.add_output('W1', 161.49, units='lbm/s') des_vars.add_output('MN1', 0.4463) des_vars.add_output('P2', 8.68, units='psi') des_vars.add_output('T2', 524., units='degR') des_vars.add_output('W2', 158., units='lbm/s') des_vars.add_output('MN2', 0.4463) p.model.add_subsystem('start1', FlowStart(elements=AIR_FUEL_MIX)) p.model.add_subsystem('start2', FlowStart(elements=AIR_MIX)) p.model.connect('des_vars.P1', 'start1.P') p.model.connect('des_vars.T1', 'start1.T') p.model.connect('des_vars.W1', 'start1.W') p.model.connect('des_vars.MN1', 'start1.MN') p.model.connect('des_vars.P2', 'start2.P') p.model.connect('des_vars.T2', 'start2.T') p.model.connect('des_vars.W2', 'start2.W') p.model.connect('des_vars.MN2', 'start2.MN') p.model.add_subsystem( 'mixer', Mixer(design=True, designed_stream=designed_stream, Fl_I1_elements=AIR_FUEL_MIX, Fl_I2_elements=AIR_MIX)) connect_flow(p.model, 'start1.Fl_O', 'mixer.Fl_I1') connect_flow(p.model, 'start2.Fl_O', 'mixer.Fl_I2') p.setup(force_alloc_complex=complex) p.set_solver_print(level=-1) return p
def test_mix_diff(self): # mix two identical streams and make sure you get twice the area and the same total pressure p = Problem() des_vars = p.model.add_subsystem('des_vars', IndepVarComp()) des_vars.add_output('P1', 17., units='psi') des_vars.add_output('P2', 15., units='psi') des_vars.add_output('T', 500., units='degR') des_vars.add_output('W', 100., units='lbm/s') des_vars.add_output('MN', 0.5) p.model.add_subsystem('start1', FlowStart()) p.model.add_subsystem('start2', FlowStart()) p.model.connect('des_vars.P1', 'start1.P') p.model.connect('des_vars.P2', 'start2.P') p.model.connect('des_vars.T', ['start1.T', 'start2.T']) p.model.connect('des_vars.W', ['start1.W', 'start2.W']) p.model.connect('des_vars.MN', ['start1.MN', 'start2.MN']) p.model.add_subsystem( 'mixer', Mixer(design=True, Fl_I1_elements=AIR_MIX, Fl_I2_elements=AIR_MIX)) connect_flow(p.model, 'start1.Fl_O', 'mixer.Fl_I1') connect_flow(p.model, 'start2.Fl_O', 'mixer.Fl_I2') p.set_solver_print(level=-1) p.setup() p.run_model() tol = 2e-7 assert_rel_error(self, p['mixer.Fl_O:stat:area'], 653.2652635, tolerance=tol) assert_rel_error(self, p['mixer.Fl_O:tot:P'], 15.94216641, tolerance=tol) assert_rel_error(self, p['mixer.ER'], 1.1333333333, tolerance=tol)
def setup(self): thermo_spec = species_data.janaf self.add_subsystem( 'fc', FlightConditions(thermo_data=thermo_spec, elements=AIR_MIX)) self.add_subsystem( 'inlet', Inlet(design=True, thermo_data=thermo_spec, elements=AIR_MIX)) self.add_subsystem( 'fan', Compressor(thermo_data=thermo_spec, elements=AIR_MIX, design=True)) self.add_subsystem('nozz', Nozzle(thermo_data=thermo_spec, elements=AIR_MIX)) self.add_subsystem('perf', Performance(num_nozzles=1, num_burners=0)) self.add_subsystem('shaft', IndepVarComp('Nmech', 1., units='rpm')) self.add_subsystem('pwr_balance', BalanceComp('W', units='lbm/s', eq_units='hp', val=50., lower=1., upper=500.), promotes_inputs=[('rhs:W', 'pwr_target')]) # self.set_order(['pwr_balance', 'pwr_target', 'fc', 'inlet', 'shaft', 'fan', 'nozz', 'perf']) connect_flow(self, 'fc.Fl_O', 'inlet.Fl_I') connect_flow(self, 'inlet.Fl_O', 'fan.Fl_I') connect_flow(self, 'fan.Fl_O', 'nozz.Fl_I') self.connect('shaft.Nmech', 'fan.Nmech') self.connect('fc.Fl_O:stat:P', 'nozz.Ps_exhaust') self.connect('inlet.Fl_O:tot:P', 'perf.Pt2') self.connect('fan.Fl_O:tot:P', 'perf.Pt3') self.connect('inlet.F_ram', 'perf.ram_drag') self.connect('nozz.Fg', 'perf.Fg_0') self.connect('pwr_balance.W', 'fc.W') self.connect('fan.power', 'pwr_balance.lhs:W') newton = self.nonlinear_solver = NewtonSolver() newton.options['atol'] = 1e-12 newton.options['rtol'] = 1e-12 newton.options['iprint'] = 2 newton.options['maxiter'] = 10 newton.options['solve_subsystems'] = True newton.options['max_sub_solves'] = 10 # newton.linesearch = BoundsEnforceLS() newton.linesearch.options['bound_enforcement'] = 'scalar' # newton.linesearch.options['print_bound_enforce'] = True # newton.linesearch.options['iprint'] = -1 # self.linear_solver = DirectSolver(assemble_jac=True)
def setUp(self): self.prob = Problem() des_vars = self.prob.model.add_subsystem('des_vars', IndepVarComp(), promotes=['*']) des_vars.add_output('P', 17., units='psi'), des_vars.add_output('T', 500.0, units='degR'), des_vars.add_output('W', 0., units='lbm/s'), des_vars.add_output('Nmech', 1000., units='rpm'), des_vars.add_output('area_targ', 150., units='inch**2') des_vars.add_output('burner_MN', .01, units=None) des_vars.add_output('burner_FAR', .01, units=None) self.prob.model.add_subsystem( 'flow_start', FlowStart(thermo_data=janaf, elements=AIR_MIX)) self.prob.model.add_subsystem( 'burner', Combustor(thermo_data=janaf, inflow_elements=AIR_MIX, air_fuel_elements=AIR_FUEL_MIX, fuel_type="JP-7")) self.prob.model.add_subsystem( 'turbine', Turbine(map_data=LPT2269, design=False, elements=AIR_FUEL_MIX)) connect_flow(self.prob.model, "flow_start.Fl_O", "burner.Fl_I") connect_flow(self.prob.model, "burner.Fl_O", "turbine.Fl_I") self.prob.model.connect("P", "flow_start.P") self.prob.model.connect("T", "flow_start.T") self.prob.model.connect("W", "flow_start.W") self.prob.model.connect("Nmech", "turbine.Nmech") self.prob.model.connect("area_targ", "turbine.area") self.prob.model.connect("burner_MN", "burner.MN") self.prob.model.connect("burner_FAR", "burner.Fl_I:FAR") self.prob.set_solver_print(level=-1) self.prob.setup(check=False)
def setUp(self): thermo = Thermo(janaf, constants.AIR_MIX) self.prob = Problem() self.prob.model.add_subsystem( 'flow_start', FlowStart(thermo_data=janaf, elements=AIR_MIX)) self.prob.model.add_subsystem( 'compressor', Compressor(design=True, elements=AIR_MIX)) self.prob.model.set_input_defaults('flow_start.P', 17., units='psi') self.prob.model.set_input_defaults('flow_start.T', 500., units='degR') self.prob.model.set_input_defaults('compressor.MN', 0.5) self.prob.model.set_input_defaults('flow_start.W', 10., units='lbm/s') self.prob.model.set_input_defaults('compressor.PR', 6.) self.prob.model.set_input_defaults('compressor.eff', 0.9) connect_flow(self.prob.model, "flow_start.Fl_O", "compressor.Fl_I") self.prob.set_solver_print(level=-1) self.prob.setup(check=False)
def setUp(self): self.prob = Problem() self.prob.model = Group() des_vars = self.prob.model.add_subsystem('des_vars', IndepVarComp(), promotes=['*']) des_vars.add_output('P', 17.0, units='psi') des_vars.add_output('T', 500.0, units='degR') des_vars.add_output('W', 100.0, units='lbm/s') des_vars.add_output('PR', 4.0) des_vars.add_output('MN', 0.0) des_vars.add_output('Nmech', 1000.0, units='rpm') des_vars.add_output('flow_start_MN', 0.0) des_vars.add_output('eff', 0.9) self.prob.model.add_subsystem( 'flow_start', FlowStart(thermo_data=janaf, elements=AIR_MIX)) self.prob.model.add_subsystem( 'turbine', Turbine(map_data=LPT2269, design=True, elements=AIR_MIX)) connect_flow(self.prob.model, 'flow_start.Fl_O', 'turbine.Fl_I') self.prob.model.connect("P", "flow_start.P") self.prob.model.connect("T", "flow_start.T") self.prob.model.connect("W", "flow_start.W") self.prob.model.connect("flow_start_MN", "flow_start.MN") self.prob.model.connect("PR", "turbine.PR") self.prob.model.connect("MN", "turbine.MN") self.prob.model.connect("Nmech", "turbine.Nmech") self.prob.model.connect('eff', 'turbine.eff') self.prob.setup(check=False) self.prob.set_solver_print(level=-1)
def __init__(self): super(CompressionCycle, self).__init__() # initiate components #self.add('fc', FlightConditions()) self.add('fl_start', FlowStart(thermo_data=janaf, elements=AIR_MIX)) # internal flow self.add('inlet', Inlet(thermo_data=janaf, elements=AIR_MIX)) self.add('comp', Compressor(thermo_data=janaf, elements=AIR_MIX)) self.add('duct', Duct(thermo_data=janaf, elements=AIR_MIX)) self.add('nozzle', Nozzle(thermo_data=janaf, elements=AIR_MIX)) self.add('shaft', Shaft(1)) # connect components connect_flow(self, 'fl_start.Fl_O', 'inlet.Fl_I') connect_flow(self, 'inlet.Fl_O', 'comp.Fl_I') connect_flow(self, 'comp.Fl_O', 'duct.Fl_I') connect_flow(self, 'duct.Fl_O', 'nozzle.Fl_I') self.connect('comp.trq', 'shaft.trq_0') self.connect('shaft.Nmech', 'comp.Nmech')
def __init__(self): super(CompressionCycle, self).__init__() # initiate components #self.add('fc', FlightConditions()) self.add('fl_start', FlowStart(thermo_data=janaf, elements=AIR_MIX)) # internal flow self.add('inlet', Inlet(thermo_data=janaf, elements=AIR_MIX)) self.add('comp', Compressor(thermo_data=janaf, elements=AIR_MIX)) self.add('duct', Duct(thermo_data=janaf, elements=AIR_MIX)) self.add('nozzle', Nozzle(thermo_data=janaf, elements=AIR_MIX)) self.add('shaft', Shaft(1)) # connect components connect_flow(self,'fl_start.Fl_O', 'inlet.Fl_I') connect_flow(self, 'inlet.Fl_O','comp.Fl_I') connect_flow(self,'comp.Fl_O', 'duct.Fl_I') connect_flow(self,'duct.Fl_O', 'nozzle.Fl_I') self.connect('comp.trq', 'shaft.trq_0') self.connect('shaft.Nmech', 'comp.Nmech')
def __init__(self): super(FlowPath, self).__init__() des_vars = (('ram_recovery', 0.99), ('effDes', 0.9), ('duct_MN', 0.65), ('duct_dPqP', 0.), ('nozzle_Cfg', 1.0), ('nozzle_dPqP', 0.), ('shaft_Nmech', 10000.), ('inlet_MN', 0.6), ('comp_MN', 0.65)) self.add('input_vars', IndepVarComp(des_vars)) self.add('fl_start', FlowStart(thermo_data=janaf, elements=AIR_MIX)) # internal flow self.add('inlet', Inlet(thermo_data=janaf, elements=AIR_MIX)) self.add('comp', Compressor(thermo_data=janaf, elements=AIR_MIX)) self.add('duct', Duct(thermo_data=janaf, elements=AIR_MIX)) self.add('nozzle', Nozzle(thermo_data=janaf, elements=AIR_MIX)) self.add('shaft', Shaft(1)) # connect components connect_flow(self, 'fl_start.Fl_O', 'inlet.Fl_I') connect_flow(self, 'inlet.Fl_O', 'comp.Fl_I') connect_flow(self, 'comp.Fl_O', 'duct.Fl_I') connect_flow(self, 'duct.Fl_O', 'nozzle.Fl_I') self.connect('input_vars.ram_recovery', 'inlet.ram_recovery') self.connect('input_vars.effDes', 'comp.map.effDes') self.connect('input_vars.duct_MN', 'duct.MN_target') self.connect('input_vars.duct_dPqP', 'duct.dPqP') self.connect('input_vars.nozzle_Cfg', 'nozzle.Cfg') self.connect('input_vars.nozzle_dPqP', 'nozzle.dPqP') self.connect('input_vars.shaft_Nmech', 'shaft.Nmech') self.connect('input_vars.inlet_MN', 'inlet.MN_target') self.connect('input_vars.comp_MN', 'comp.MN_target') self.connect('comp.trq', 'shaft.trq_0') self.connect('shaft.Nmech', 'comp.Nmech')
p.model.add_subsystem('des_var2', IndepVarComp('Pt', 14.0, units='lbf/inch**2')) p.model.add_subsystem('des_var3', IndepVarComp('Tt', 1662.44, units='degR')) p.model.add_subsystem('des_var4', IndepVarComp('dPqP', 0.0)) p.model.add_subsystem( 'des_var5', IndepVarComp('Ps_exhaust', 14.696, units='lbf/inch**2')) p.model.add_subsystem('des_var6', IndepVarComp('Cv', 0.99, units=None)) p.model.add_subsystem( 'flow_start', FlowStart(thermo_data=species_data.janaf, elements=AIR_MIX)) p.model.add_subsystem( 'nozz', Nozzle(nozzType="CD", lossCoef='Cv', elements=AIR_MIX)) connect_flow(p.model, "flow_start.Fl_O", "nozz.Fl_I", connect_stat=False) p.model.connect('des_var1.W', 'flow_start.W') p.model.connect('des_var2.Pt', 'flow_start.P') p.model.connect('des_var3.Tt', 'flow_start.T') p.model.connect('des_var4.dPqP', 'nozz.dPqP') p.model.connect('des_var5.Ps_exhaust', 'nozz.Ps_exhaust') p.model.connect('des_var6.Cv', 'nozz.Cv') # p.model.add('pressure', IndepVarComp('Ps_exhaust', 3.457820249, units='lbf/inch**2'), promotes=["*"]) p.setup(check=True) # p.model.Fl_I.W = 51.45 # p.model.Fl_I.Pt = 9.262 # p.model.Fl_I.Tt = 1443.35
def setup(self): thermo_spec = species_data.janaf design = self.options['design'] ########################################## # Elements ########################################## self.add_subsystem( 'fc', FlightConditions(thermo_data=thermo_spec, elements=AIR_MIX)) # Inlet Components self.add_subsystem('mil_spec', MilSpecRecovery()) self.add_subsystem( 'inlet', Inlet(design=design, thermo_data=thermo_spec, elements=AIR_MIX)) # Fan Components - Split here for CFD integration Add a CFDStart Compomponent self.add_subsystem('fan', Compressor(map_data=AXI5, design=design, thermo_data=thermo_spec, elements=AIR_MIX, map_extrap=True), promotes_inputs=[('Nmech', 'LP_Nmech')]) self.add_subsystem( 'splitter', Splitter(design=design, thermo_data=thermo_spec, elements=AIR_MIX)) # Bypass Stream ################### self.add_subsystem( 'bypass_duct', Duct(design=design, thermo_data=thermo_spec, elements=AIR_MIX)) # Core Stream ############## self.add_subsystem( 'ic_duct', Duct(design=design, thermo_data=thermo_spec, elements=AIR_MIX)) self.add_subsystem('hpc', Compressor(map_data=HPCmap, design=design, thermo_data=thermo_spec, elements=AIR_MIX, bleed_names=['cool1', 'cool2'], map_extrap=True), promotes_inputs=[('Nmech', 'HP_Nmech')]) self.add_subsystem( 'duct_3', Duct(design=design, thermo_data=thermo_spec, elements=AIR_MIX)) self.add_subsystem('bleed_3', BleedOut(design=design, bleed_names=['cust_bleed'])) self.add_subsystem( 'burner', Combustor(design=design, thermo_data=thermo_spec, inflow_elements=AIR_MIX, air_fuel_elements=AIR_FUEL_MIX, fuel_type='Jet-A(g)')) self.add_subsystem('hpt', Turbine(map_data=HPTmap, design=design, thermo_data=thermo_spec, elements=AIR_FUEL_MIX, bleed_names=['chargable', 'non_chargable'], map_extrap=True), promotes_inputs=[('Nmech', 'HP_Nmech')]) self.add_subsystem( 'it_duct', Duct(design=design, thermo_data=thermo_spec, elements=AIR_FUEL_MIX)) # uncooled lpt self.add_subsystem('lpt', Turbine(map_data=LPTmap, design=design, thermo_data=thermo_spec, elements=AIR_FUEL_MIX, map_extrap=True), promotes_inputs=[('Nmech', 'LP_Nmech')]) if not design: self.add_subsystem( 'vabi', ExecComp('Fl1_area = Fl1_area_des*fact', Fl1_area_des={'units': 'inch**2'}, Fl1_area={ 'units': 'inch**2', 'value': 164. })) self.add_subsystem( 'mixer', Mixer(design=design, designed_stream=1, Fl_I1_elements=AIR_FUEL_MIX, Fl_I2_elements=AIR_MIX)) # augmentor Components self.add_subsystem( 'augmentor', Combustor(design=design, thermo_data=thermo_spec, inflow_elements=AIR_FUEL_MIX, air_fuel_elements=AIR_FUEL_MIX, fuel_type='Jet-A(g)')) # End CFD HERE # Nozzle self.add_subsystem( 'nozzle', Nozzle(nozzType='CD', lossCoef='Cfg', thermo_data=thermo_spec, elements=AIR_FUEL_MIX)) # Mechanical components self.add_subsystem('lp_shaft', Shaft(num_ports=2), promotes_inputs=[('Nmech', 'LP_Nmech')]) self.add_subsystem('hp_shaft', Shaft(num_ports=2), promotes_inputs=[('Nmech', 'HP_Nmech')]) # Aggregating component self.add_subsystem('perf', Performance(num_nozzles=1, num_burners=2)) ########################################## # Connecting the Flow Path ########################################## connect_flow(self, 'fc.Fl_O', 'inlet.Fl_I') connect_flow(self, 'inlet.Fl_O', 'fan.Fl_I') connect_flow(self, 'fan.Fl_O', 'splitter.Fl_I') # Bypass Connections connect_flow(self, 'splitter.Fl_O2', 'bypass_duct.Fl_I') connect_flow(self, 'bypass_duct.Fl_O', 'mixer.Fl_I2') # Core connections connect_flow(self, 'splitter.Fl_O1', 'ic_duct.Fl_I') connect_flow(self, 'ic_duct.Fl_O', 'hpc.Fl_I') connect_flow(self, 'hpc.Fl_O', 'duct_3.Fl_I') connect_flow(self, 'duct_3.Fl_O', 'bleed_3.Fl_I') connect_flow(self, 'bleed_3.Fl_O', 'burner.Fl_I') connect_flow(self, 'burner.Fl_O', 'hpt.Fl_I') connect_flow(self, 'hpt.Fl_O', 'it_duct.Fl_I') connect_flow(self, 'it_duct.Fl_O', 'lpt.Fl_I') connect_flow(self, 'lpt.Fl_O', 'mixer.Fl_I1') connect_flow(self, 'mixer.Fl_O', 'augmentor.Fl_I') connect_flow(self, 'augmentor.Fl_O', 'nozzle.Fl_I') # Connect cooling flows connect_flow(self, 'hpc.cool1', 'hpt.non_chargable', connect_stat=False) connect_flow(self, 'hpc.cool2', 'hpt.chargable', connect_stat=False) ########################################## # Additional Connections ########################################## # Make additional model connections self.connect('fc.Fl_O:stat:MN', 'mil_spec.MN') self.connect('mil_spec.ram_recovery', 'inlet.ram_recovery') 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('augmentor.Wfuel', 'perf.Wfuel_1') self.connect('inlet.F_ram', 'perf.ram_drag') self.connect('nozzle.Fg', 'perf.Fg_0') self.connect('fan.trq', 'lp_shaft.trq_0') self.connect('lpt.trq', 'lp_shaft.trq_1') self.connect('hpc.trq', 'hp_shaft.trq_0') self.connect('hpt.trq', 'hp_shaft.trq_1') self.connect('fc.Fl_O:stat:P', 'nozzle.Ps_exhaust') if not design: self.connect('vabi.Fl1_area', 'mixer.Fl_I1_stat_calc.area') ########################################## # Balances to define cycle convergence ########################################## balance = self.add_subsystem('balance', BalanceComp()) if design: balance.add_balance('W', lower=1e-3, upper=200., units='lbm/s', eq_units='lbf') self.connect('balance.W', 'fc.fs.W') self.connect('perf.Fn', 'balance.lhs:W') # self.add_subsystem('wDV',IndepVarComp('wDes',100,units='lbm/s')) # self.connect('wDV.wDes','fc.fs.W') balance.add_balance('BPR', eq_units=None, lower=0.25, val=5.0) self.connect('balance.BPR', 'splitter.BPR') self.connect('mixer.ER', 'balance.lhs:BPR') balance.add_balance('FAR_core', eq_units='degR', lower=1e-4, val=.017) self.connect('balance.FAR_core', 'burner.Fl_I:FAR') self.connect('burner.Fl_O:tot:T', 'balance.lhs:FAR_core') balance.add_balance('FAR_ab', eq_units='degR', lower=1e-4, val=.017) self.connect('balance.FAR_ab', 'augmentor.Fl_I:FAR') self.connect('augmentor.Fl_O:tot:T', 'balance.lhs:FAR_ab') 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', 'balance.lhs:lpt_PR') self.connect('lp_shaft.pwr_out', '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', 'balance.lhs:hpt_PR') self.connect('hp_shaft.pwr_out', 'balance.rhs:hpt_PR') else: # off design balance.add_balance('W', lower=1e-3, upper=400., units='lbm/s', eq_units='inch**2') self.connect('balance.W', 'fc.fs.W') self.connect('nozzle.Throat:stat:area', 'balance.lhs:W') balance.add_balance('BPR', lower=0.25, upper=3.0, eq_units='psi') self.connect('balance.BPR', 'splitter.BPR') self.connect('mixer.Fl_I1_calc:stat:P', 'balance.lhs:BPR') self.connect('bypass_duct.Fl_O:stat:P', 'balance.rhs:BPR') # balance.add_balance('FAR_core', eq_units='degR', lower=1e-4, upper=.045, val=.017) # self.connect('balance.FAR_core', 'burner.Fl_I:FAR') # self.connect('burner.Fl_O:tot:T', 'balance.lhs:FAR_core') balance.add_balance('FAR_ab', eq_units='degR', lower=1e-4, upper=.045, val=.017) self.connect('balance.FAR_ab', 'augmentor.Fl_I:FAR') self.connect('augmentor.Fl_O:tot:T', 'balance.lhs:FAR_ab') far_core_bal = ConstrainedTempBalance() self.add_subsystem('far_core_bal', far_core_bal) self.connect('far_core_bal.FAR', 'burner.Fl_I:FAR') self.connect('burner.Fl_O:tot:T', 'far_core_bal.T_computed') self.connect('fan.map.shaftNc.NcMap', 'far_core_bal.Nc_computed') balance.add_balance('LP_Nmech', val=1., units='rpm', lower=0.5, upper=2., eq_units='hp', use_mult=True, mult_val=-1) self.connect('balance.LP_Nmech', 'LP_Nmech') self.connect('lp_shaft.pwr_in', 'balance.lhs:LP_Nmech') self.connect('lp_shaft.pwr_out', 'balance.rhs:LP_Nmech') balance.add_balance('HP_Nmech', val=1., units='rpm', lower=0.5, upper=2., eq_units='hp', use_mult=True, mult_val=-1) self.connect('balance.HP_Nmech', 'HP_Nmech') self.connect('hp_shaft.pwr_in', 'balance.lhs:HP_Nmech') self.connect('hp_shaft.pwr_out', 'balance.rhs:HP_Nmech') newton = self.nonlinear_solver = NewtonSolver() newton.options['atol'] = 1e-6 newton.options['rtol'] = 1e-10 newton.options['iprint'] = 2 newton.options['maxiter'] = 30 newton.options['solve_subsystems'] = True newton.options['max_sub_solves'] = 10 newton.linesearch = BoundsEnforceLS() newton.linesearch.options['bound_enforcement'] = 'scalar' # newton.linesearch.options['print_bound_enforce'] = True newton.linesearch.options['iprint'] = -1 # newton.linesearch = ArmijoGoldsteinLS() # newton.linesearch.options['c'] = -.1 self.linear_solver = DirectSolver(assemble_jac=True) # TODO: re-factor pycycle so this block isn't needed in default use case!!! if design: ########################################## # Model Parameters ########################################## element_params = self.add_subsystem('element_params', IndepVarComp(), promotes=["*"]) # element_params.add_output('inlet:ram_recovery', 0.9990) element_params.add_output('inlet:MN_out', 0.65) # self.connect('inlet:ram_recovery', 'inlet.ram_recovery') self.connect('inlet:MN_out', 'inlet.MN') element_params.add_output('fan:effDes', 0.8700) element_params.add_output('fan:MN_out', 0.4578) self.connect('fan:effDes', 'fan.map.effDes') self.connect('fan:MN_out', 'fan.MN') element_params.add_output('splitter:MN_out1', 0.3104) element_params.add_output('splitter:MN_out2', 0.4518) self.connect('splitter:MN_out1', 'splitter.MN1') self.connect('splitter:MN_out2', 'splitter.MN2') element_params.add_output('ic_duct:dPqP', 0.0048) element_params.add_output('ic_duct:MN_out', 0.3121) self.connect('ic_duct:dPqP', 'ic_duct.dPqP') self.connect('ic_duct:MN_out', 'ic_duct.MN') element_params.add_output('hpc:effDes', 0.8707) element_params.add_output('hpc:MN_out', 0.2442) self.connect('hpc:effDes', 'hpc.map.effDes') self.connect('hpc:MN_out', 'hpc.MN') element_params.add_output('hpc:cool1:frac_W', 0.09) element_params.add_output('hpc:cool1:frac_P', 1.0) element_params.add_output('hpc:cool1:frac_work', 1.0) self.connect('hpc:cool1:frac_W', 'hpc.cool1:frac_W') self.connect('hpc:cool1:frac_P', 'hpc.cool1:frac_P') self.connect('hpc:cool1:frac_work', 'hpc.cool1:frac_work') element_params.add_output('hpc:cool2:frac_W', 0.07) element_params.add_output('hpc:cool2:frac_P', 0.5) element_params.add_output('hpc:cool2:frac_work', 0.5) self.connect('hpc:cool2:frac_W', 'hpc.cool2:frac_W') self.connect('hpc:cool2:frac_P', 'hpc.cool2:frac_P') self.connect('hpc:cool2:frac_work', 'hpc.cool2:frac_work') element_params.add_output('duct_3:dPqP', 0.0048) element_params.add_output('duct_3:MN_out', 0.2) self.connect('duct_3:dPqP', 'duct_3.dPqP') self.connect('duct_3:MN_out', 'duct_3.MN') element_params.add_output('bleed_3:MN_out', 0.3000) element_params.add_output('bleed_3:cust_bleed:frac_W', 0.07) self.connect('bleed_3:MN_out', 'bleed_3.MN') self.connect('bleed_3:cust_bleed:frac_W', 'bleed_3.cust_bleed:frac_W') element_params.add_output('burner:dPqP', 0.0540) element_params.add_output('burner:MN_out', 0.1025) self.connect('burner:dPqP', 'burner.dPqP') self.connect('burner:MN_out', 'burner.MN') element_params.add_output('hpt:effDes', 0.8888) element_params.add_output('hpt:MN_out', 0.3650) element_params.add_output('hpt:chargable:frac_P', 0.0) element_params.add_output('hpt:non_chargable:frac_P', 1.0) self.connect('hpt:effDes', 'hpt.map.effDes') self.connect('hpt:MN_out', 'hpt.MN') self.connect('hpt:chargable:frac_P', 'hpt.chargable:frac_P') self.connect('hpt:non_chargable:frac_P', 'hpt.non_chargable:frac_P') element_params.add_output('it_duct:dPqP', 0.0051) element_params.add_output('it_duct:MN_out', 0.3063) self.connect('it_duct:dPqP', 'it_duct.dPqP') self.connect('it_duct:MN_out', 'it_duct.MN') element_params.add_output('lpt:effDes', 0.8996) element_params.add_output('lpt:MN_out', 0.4127) self.connect('lpt:effDes', 'lpt.map.effDes') self.connect('lpt:MN_out', 'lpt.MN') element_params.add_output('bypass_duct:dPqP', 0.0107) element_params.add_output('bypass_duct:MN_out', 0.4463) self.connect('bypass_duct:dPqP', 'bypass_duct.dPqP') self.connect('bypass_duct:MN_out', 'bypass_duct.MN') # No params for mixer element_params.add_output('augmentor:dPqP', 0.0540) element_params.add_output('augmentor:MN_out', 0.1025) self.connect('augmentor:dPqP', 'augmentor.dPqP') self.connect('augmentor:MN_out', 'augmentor.MN') element_params.add_output('nozzle:Cfg', 0.9933) self.connect('nozzle:Cfg', 'nozzle.Cfg') element_params.add_output('lp_shaft:Nmech', 1, units='rpm') element_params.add_output('hp_shaft:Nmech', 1, units='rpm') element_params.add_output('hp_shaft:HPX', 250.0, units='hp') self.connect('lp_shaft:Nmech', 'LP_Nmech') self.connect('hp_shaft:Nmech', 'HP_Nmech') self.connect('hp_shaft:HPX', 'hp_shaft.HPX')
def test_case_with_dPqP_MN(self): self.prob = Problem() self.prob.model = Group() self.prob.model.add_subsystem( 'flow_start', FlowStart(thermo_data=janaf, elements=AIR_MIX)) self.prob.model.add_subsystem( 'flow_start_OD', FlowStart(thermo_data=janaf, elements=AIR_MIX)) expMN = 1.0 self.prob.model.add_subsystem('duct_des', Duct(elements=AIR_MIX, expMN=expMN)) self.prob.model.add_subsystem( 'duct_OD', Duct(elements=AIR_MIX, expMN=expMN, design=False)) connect_flow(self.prob.model, 'flow_start.Fl_O', 'duct_des.Fl_I') connect_flow(self.prob.model, 'flow_start_OD.Fl_O', 'duct_OD.Fl_I') des_vars = self.prob.model.add_subsystem('des_vars', IndepVarComp(), promotes=['*']) des_vars.add_output('P', 17., units='psi') des_vars.add_output('T', 500., units='degR') des_vars.add_output('W', 500., units='lbm/s') des_vars.add_output('MN', 0.5) des_vars.add_output('MN_OD', 0.25) des_vars.add_output('dPqP_des', 0.0) self.prob.model.connect("P", ["flow_start.P", 'flow_start_OD.P']) self.prob.model.connect("T", ["flow_start.T", 'flow_start_OD.T']) self.prob.model.connect("W", ["flow_start.W", 'flow_start_OD.W']) self.prob.model.connect("MN", ["duct_des.MN", "flow_start.MN"]) self.prob.model.connect("MN_OD", "flow_start_OD.MN") self.prob.model.connect("duct_des.s_dPqP", "duct_OD.s_dPqP") self.prob.model.connect("duct_des.Fl_O:stat:area", "duct_OD.area") self.prob.model.connect("dPqP_des", "duct_des.dPqP") self.prob.setup(check=False) self.prob.set_solver_print(level=-1) data = ref_data[0] self.prob['dPqP_des'] = data[h_map['dPqP']] # input flowstation self.prob['P'] = data[h_map['Fl_I.Pt']] self.prob['T'] = data[h_map['Fl_I.Tt']] self.prob['MN'] = data[h_map['Fl_O.MN']] self.prob['W'] = data[h_map['Fl_I.W']] self.prob['duct_des.Fl_I:stat:V'] = data[h_map['Fl_I.V']] # give a decent initial guess for Ps print(self.prob['P'], self.prob['T'], self.prob['MN']) self.prob.run_model() # check outputs pt, ht, ps, ts = data[h_map['Fl_O.Pt']], data[h_map['Fl_O.ht']], data[ h_map['Fl_O.Ps']], data[h_map['Fl_O.Ts']] pt_computed = self.prob['duct_OD.Fl_O:tot:P'] ht_computed = self.prob['duct_OD.Fl_O:tot:h'] ps_computed = self.prob['duct_OD.Fl_O:stat:P'] ts_computed = self.prob['duct_OD.Fl_O:stat:T'] tol = 1.0e-4 assert_rel_error(self, pt_computed, 8.84073152, tol) assert_rel_error(self, ht_computed, ht, tol) assert_rel_error(self, ps_computed, 8.26348914, tol) assert_rel_error(self, ts_computed, ts, tol) check_element_partials(self, self.prob)
def test_case1(self): self.prob = Problem() self.prob.model = Group() self.prob.model.add_subsystem( 'flow_start', FlowStart(thermo_data=janaf, elements=AIR_MIX)) self.prob.model.add_subsystem('duct', Duct(elements=AIR_MIX)) connect_flow(self.prob.model, 'flow_start.Fl_O', 'duct.Fl_I') des_vars = self.prob.model.add_subsystem('des_vars', IndepVarComp(), promotes=['*']) des_vars.add_output('P', 17., units='psi') des_vars.add_output('T', 500., units='degR') des_vars.add_output('W', 500., units='lbm/s') des_vars.add_output('MN', 0.5) des_vars.add_output('dPqP_des', 0.0) self.prob.model.connect("P", "flow_start.P") self.prob.model.connect("T", "flow_start.T") self.prob.model.connect("W", "flow_start.W") self.prob.model.connect("MN", ["duct.MN", "flow_start.MN"]) self.prob.model.connect("dPqP_des", "duct.dPqP") self.prob.setup(check=False) self.prob.set_solver_print(level=-1) # 6 cases to check against for i, data in enumerate(ref_data): self.prob['dPqP_des'] = data[h_map['dPqP']] # input flowstation self.prob['P'] = data[h_map['Fl_I.Pt']] self.prob['T'] = data[h_map['Fl_I.Tt']] self.prob['MN'] = data[h_map['Fl_O.MN']] self.prob['W'] = data[h_map['Fl_I.W']] self.prob['duct.Fl_I:stat:V'] = data[h_map['Fl_I.V']] # give a decent initial guess for Ps print(i, self.prob['P'], self.prob['T'], self.prob['MN']) self.prob.run_model() # check outputs pt, ht, ps, ts = data[h_map['Fl_O.Pt']], data[h_map[ 'Fl_O.ht']], data[h_map['Fl_O.Ps']], data[h_map['Fl_O.Ts']] pt_computed = self.prob['duct.Fl_O:tot:P'] ht_computed = self.prob['duct.Fl_O:tot:h'] ps_computed = self.prob['duct.Fl_O:stat:P'] ts_computed = self.prob['duct.Fl_O:stat:T'] tol = 2.0e-2 assert_rel_error(self, pt_computed, pt, tol) assert_rel_error(self, ht_computed, ht, tol) assert_rel_error(self, ps_computed, ps, tol) assert_rel_error(self, ts_computed, ts, tol) check_element_partials(self, self.prob)
def setup(self): thermo_spec = species_data.janaf design = self.options['design'] statics = self.options['statics'] self.add_subsystem( 'fc', FlightConditions(thermo_data=thermo_spec, elements=AIR_MIX)) self.add_subsystem( 'inlet', Inlet(design=design, thermo_data=thermo_spec, elements=AIR_MIX)) self.add_subsystem( 'duct1', Duct(design=design, thermo_data=thermo_spec, elements=AIR_MIX, statics=statics)) self.add_subsystem('lpc', Compressor(map_data=LPCmap, design=design, thermo_data=thermo_spec, elements=AIR_MIX, statics=statics), promotes_inputs=[('Nmech', 'IP_Nmech')]) self.add_subsystem( 'icduct', Duct(design=design, thermo_data=thermo_spec, elements=AIR_MIX, statics=statics)) self.add_subsystem('hpc_axi', Compressor(map_data=HPCmap, design=design, thermo_data=thermo_spec, elements=AIR_MIX, statics=statics), promotes_inputs=[('Nmech', 'HP_Nmech')]) self.add_subsystem( 'bld25', BleedOut(design=design, statics=statics, bleed_names=['cool1', 'cool2'])) self.add_subsystem('hpc_centri', Compressor(map_data=HPCmap, design=design, thermo_data=thermo_spec, elements=AIR_MIX, statics=statics), promotes_inputs=[('Nmech', 'HP_Nmech')]) self.add_subsystem( 'bld3', BleedOut(design=design, statics=statics, bleed_names=['cool3', 'cool4'])) self.add_subsystem( 'duct6', Duct(design=design, thermo_data=thermo_spec, elements=AIR_MIX, statics=statics)) self.add_subsystem( 'burner', Combustor(design=design, thermo_data=thermo_spec, inflow_elements=AIR_MIX, air_fuel_elements=AIR_FUEL_MIX, fuel_type='Jet-A(g)', statics=statics)) self.add_subsystem('hpt', Turbine(map_data=HPTmap, design=design, thermo_data=thermo_spec, elements=AIR_FUEL_MIX, bleed_names=['cool3', 'cool4'], statics=statics), promotes_inputs=[('Nmech', 'HP_Nmech')]) self.add_subsystem( 'duct43', Duct(design=design, thermo_data=thermo_spec, elements=AIR_FUEL_MIX, statics=statics)) self.add_subsystem('lpt', Turbine(map_data=LPTmap, design=design, thermo_data=thermo_spec, elements=AIR_FUEL_MIX, bleed_names=['cool1', 'cool2'], statics=statics), promotes_inputs=[('Nmech', 'IP_Nmech')]) self.add_subsystem( 'itduct', Duct(design=design, thermo_data=thermo_spec, elements=AIR_FUEL_MIX, statics=statics)) self.add_subsystem('pt', Turbine(map_data=LPTmap, design=design, thermo_data=thermo_spec, elements=AIR_FUEL_MIX, statics=statics), promotes_inputs=[('Nmech', 'LP_Nmech')]) self.add_subsystem( 'duct12', Duct(design=design, thermo_data=thermo_spec, elements=AIR_FUEL_MIX, statics=statics)) self.add_subsystem( 'nozzle', Nozzle(nozzType='CV', lossCoef='Cv', thermo_data=thermo_spec, elements=AIR_FUEL_MIX)) self.add_subsystem('lp_shaft', Shaft(num_ports=1), promotes_inputs=[('Nmech', 'LP_Nmech')]) self.add_subsystem('ip_shaft', Shaft(num_ports=2), promotes_inputs=[('Nmech', 'IP_Nmech')]) self.add_subsystem('hp_shaft', Shaft(num_ports=3), promotes_inputs=[('Nmech', 'HP_Nmech')]) self.add_subsystem('perf', Performance(num_nozzles=1, num_burners=1)) self.connect('duct1.Fl_O:tot:P', 'perf.Pt2') self.connect('hpc_centri.Fl_O:tot:P', 'perf.Pt3') self.connect('burner.Wfuel', 'perf.Wfuel_0') self.connect('inlet.F_ram', 'perf.ram_drag') self.connect('nozzle.Fg', 'perf.Fg_0') self.connect('lp_shaft.pwr_in', 'perf.power') self.connect('pt.trq', 'lp_shaft.trq_0') self.connect('lpc.trq', 'ip_shaft.trq_0') self.connect('lpt.trq', 'ip_shaft.trq_1') self.connect('hpc_axi.trq', 'hp_shaft.trq_0') self.connect('hpc_centri.trq', 'hp_shaft.trq_1') self.connect('hpt.trq', 'hp_shaft.trq_2') self.connect('fc.Fl_O:stat:P', 'nozzle.Ps_exhaust') balance = self.add_subsystem('balance', BalanceComp()) if design: balance.add_balance('W', units='lbm/s', eq_units=None) self.connect('balance.W', 'inlet.Fl_I:stat:W') self.connect('nozzle.PR', 'balance.lhs:W') balance.add_balance('FAR', eq_units='degR', lower=1e-4, val=.017) self.connect('balance.FAR', 'burner.Fl_I:FAR') self.connect('burner.Fl_O:tot:T', 'balance.lhs:FAR') balance.add_balance('lpt_PR', val=1.5, lower=1.001, upper=8, eq_units='hp', rhs_val=0.) self.connect('balance.lpt_PR', 'lpt.PR') self.connect('ip_shaft.pwr_net', 'balance.lhs:lpt_PR') balance.add_balance('hpt_PR', val=1.5, lower=1.001, upper=8, eq_units='hp', rhs_val=0.) self.connect('balance.hpt_PR', 'hpt.PR') self.connect('hp_shaft.pwr_net', 'balance.lhs:hpt_PR') balance.add_balance('pt_PR', val=1.5, lower=1.001, upper=8, eq_units='hp', rhs_val=0.) self.connect('balance.pt_PR', 'pt.PR') self.connect('lp_shaft.pwr_net', 'balance.lhs:pt_PR') # self.set_order(['fc', 'inlet', 'duct1', 'comp', 'burner', 'turb', 'ab', 'nozz', 'shaft', 'perf', 'thrust_balance', 'temp_balance', 'shaft_balance']) # self.set_order(['balance', 'fc', 'inlet', 'duct1', 'comp', 'burner', 'turb', 'ab', 'nozz', 'shaft', 'perf']) else: # Need to check all these balances once power turbine map is updated balance.add_balance('FAR', eq_units='lbf', lower=1e-4, val=.017) self.connect('balance.FAR', 'burner.Fl_I:FAR') self.connect('perf.Fn', 'balance.lhs:FAR') balance.add_balance('W', units='lbm/s', eq_units=None) self.connect('balance.W', 'inlet.Fl_I:stat:W') self.connect('nozzle.Throat:stat:area', 'balance.lhs:W') balance.add_balance('IP_Nmech', val=12000.0, units='rpm', lower=1.001, eq_units='hp', rhs_val=0.) self.connect('balance.IP_Nmech', 'IP_Nmech') self.connect('ip_shaft.pwr_net', 'balance.lhs:IP_Nmech') balance.add_balance('HP_Nmech', val=14800.0, units='rpm', lower=1.001, eq_units='hp', rhs_val=0.) self.connect('balance.HP_Nmech', 'HP_Nmech') self.connect('hp_shaft.pwr_net', 'balance.lhs:HP_Nmech') balance.add_balance('LP_Nmech', val=1800.0, units='rpm', lower=1.001, eq_units='hp', rhs_val=0.) self.connect('balance.LP_Nmech', 'LP_Nmech') self.connect('lp_shaft.pwr_net', 'balance.lhs:LP_Nmech') # self.set_order(['balance', 'fc', 'inlet', 'fan', 'splitter', 'duct4', 'lpc', 'duct6', 'hpc', 'bld3', 'burner', 'hpt', 'duct11', # 'lpt', 'duct13', 'nozzle', 'byp_bld', 'duct15', 'lp_shaft', 'ip_shaft', 'hp_shaft', 'perf']) if statics: connect_flow(self, 'fc.Fl_O', 'inlet.Fl_I', connect_w=False) connect_flow(self, 'inlet.Fl_O', 'duct1.Fl_I') connect_flow(self, 'duct1.Fl_O', 'lpc.Fl_I') connect_flow(self, 'lpc.Fl_O', 'icduct.Fl_I') connect_flow(self, 'icduct.Fl_O', 'hpc_axi.Fl_I') connect_flow(self, 'hpc_axi.Fl_O', 'bld25.Fl_I') connect_flow(self, 'bld25.Fl_O', 'hpc_centri.Fl_I') connect_flow(self, 'hpc_centri.Fl_O', 'bld3.Fl_I') connect_flow(self, 'bld3.Fl_O', 'duct6.Fl_I') connect_flow(self, 'duct6.Fl_O', 'burner.Fl_I') connect_flow(self, 'burner.Fl_O', 'hpt.Fl_I') connect_flow(self, 'hpt.Fl_O', 'duct43.Fl_I') connect_flow(self, 'duct43.Fl_O', 'lpt.Fl_I') connect_flow(self, 'lpt.Fl_O', 'itduct.Fl_I') connect_flow(self, 'itduct.Fl_O', 'pt.Fl_I') connect_flow(self, 'pt.Fl_O', 'duct12.Fl_I') connect_flow(self, 'duct12.Fl_O', 'nozzle.Fl_I') else: connect_flow(self, 'fc.Fl_O', 'inlet.Fl_I', connect_w=False) connect_flow(self, 'inlet.Fl_O', 'duct1.Fl_I', connect_stat=False) connect_flow(self, 'duct1.Fl_O', 'lpc.Fl_I', connect_stat=False) connect_flow(self, 'lpc.Fl_O', 'icduct.Fl_I', connect_stat=False) connect_flow(self, 'icduct.Fl_O', 'hpc_axi.Fl_I', connect_stat=False) connect_flow(self, 'hpc_axi.Fl_O', 'bld25.Fl_I', connect_stat=False) connect_flow(self, 'bld25.Fl_O', 'hpc_centri.Fl_I', connect_stat=False) connect_flow(self, 'hpc_centri.Fl_O', 'bld3.Fl_I', connect_stat=False) connect_flow(self, 'bld3.Fl_O', 'duct6.Fl_I', connect_stat=False) connect_flow(self, 'duct6.Fl_O', 'burner.Fl_I', connect_stat=False) connect_flow(self, 'burner.Fl_O', 'hpt.Fl_I', connect_stat=False) connect_flow(self, 'hpt.Fl_O', 'duct43.Fl_I', connect_stat=False) connect_flow(self, 'duct43.Fl_O', 'lpt.Fl_I', connect_stat=False) connect_flow(self, 'lpt.Fl_O', 'itduct.Fl_I', connect_stat=False) connect_flow(self, 'itduct.Fl_O', 'pt.Fl_I', connect_stat=False) connect_flow(self, 'pt.Fl_O', 'duct12.Fl_I', connect_stat=False) connect_flow(self, 'duct12.Fl_O', 'nozzle.Fl_I', connect_stat=False) connect_flow(self, 'bld25.cool1', 'lpt.cool1', connect_stat=False) connect_flow(self, 'bld25.cool2', 'lpt.cool2', connect_stat=False) connect_flow(self, 'bld3.cool3', 'hpt.cool3', connect_stat=False) connect_flow(self, 'bld3.cool4', 'hpt.cool4', connect_stat=False) newton = self.nonlinear_solver = NewtonSolver() newton.options['atol'] = 1e-6 newton.options['rtol'] = 1e-6 newton.options['iprint'] = 2 newton.options['maxiter'] = 10 newton.options['solve_subsystems'] = True newton.options['max_sub_solves'] = 100 newton.linesearch = BoundsEnforceLS() # newton.linesearch = ArmijoGoldsteinLS() # newton.linesearch.options['c'] = .0001 newton.linesearch.options['bound_enforcement'] = 'scalar' newton.linesearch.options['iprint'] = -1 self.linear_solver = DirectSolver(assemble_jac=True)
def setup(self): thermo_spec = species_data.janaf design = self.options['design'] statics = self.options['statics'] self.add_subsystem('fc', FlightConditions(thermo_data=thermo_spec, elements=AIR_MIX)) self.add_subsystem('inlet', Inlet(design=design, thermo_data=thermo_spec, elements=AIR_MIX)) self.add_subsystem('fan', Compressor(map_data=FanMap, design=design, thermo_data=thermo_spec, elements=AIR_MIX, bleed_names=[], statics=statics, map_extrap=True), promotes_inputs=[('Nmech','LP_Nmech')]) self.add_subsystem('splitter', Splitter(design=design, thermo_data=thermo_spec, elements=AIR_MIX, statics=statics)) self.add_subsystem('duct4', Duct(design=design, thermo_data=thermo_spec, elements=AIR_MIX, statics=statics)) self.add_subsystem('lpc', Compressor(map_data=LPCmap, design=design, thermo_data=thermo_spec, elements=AIR_MIX, statics=statics, map_extrap=True),promotes_inputs=[('Nmech','LP_Nmech')]) self.add_subsystem('duct6', Duct(design=design, thermo_data=thermo_spec, elements=AIR_MIX, statics=statics)) self.add_subsystem('hpc', Compressor(map_data=HPCmap, design=design, thermo_data=thermo_spec, elements=AIR_MIX, bleed_names=['cool1','cool2','cust'], statics=statics, map_extrap=True),promotes_inputs=[('Nmech','HP_Nmech')]) self.add_subsystem('bld3', BleedOut(design=design, statics=statics, bleed_names=['cool3','cool4'])) self.add_subsystem('burner', Combustor(design=design,thermo_data=thermo_spec, inflow_elements=AIR_MIX, air_fuel_elements=AIR_FUEL_MIX, fuel_type='Jet-A(g)', statics=statics)) self.add_subsystem('hpt', Turbine(map_data=HPTmap, design=design, thermo_data=thermo_spec, elements=AIR_FUEL_MIX, bleed_names=['cool3','cool4'], statics=statics, map_extrap=True),promotes_inputs=[('Nmech','HP_Nmech')]) self.add_subsystem('duct11', Duct(design=design, thermo_data=thermo_spec, elements=AIR_FUEL_MIX, statics=statics)) self.add_subsystem('lpt', Turbine(map_data=LPTmap, design=design, thermo_data=thermo_spec, elements=AIR_FUEL_MIX, bleed_names=['cool1','cool2'], statics=statics, map_extrap=True),promotes_inputs=[('Nmech','LP_Nmech')]) self.add_subsystem('duct13', Duct(design=design, thermo_data=thermo_spec, elements=AIR_FUEL_MIX, statics=statics)) self.add_subsystem('core_nozz', Nozzle(nozzType='CV', lossCoef='Cv', thermo_data=thermo_spec, elements=AIR_FUEL_MIX)) self.add_subsystem('byp_bld', BleedOut(design=design, statics=statics, bleed_names=['bypBld'])) self.add_subsystem('duct15', Duct(design=design, thermo_data=thermo_spec, elements=AIR_MIX, statics=statics)) self.add_subsystem('byp_nozz', Nozzle(nozzType='CV', lossCoef='Cv', thermo_data=thermo_spec, elements=AIR_MIX)) self.add_subsystem('lp_shaft', Shaft(num_ports=3),promotes_inputs=[('Nmech','LP_Nmech')]) self.add_subsystem('hp_shaft', Shaft(num_ports=2),promotes_inputs=[('Nmech','HP_Nmech')]) self.add_subsystem('perf', Performance(num_nozzles=2, num_burners=1)) 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') self.connect('fan.trq', 'lp_shaft.trq_0') self.connect('lpc.trq', 'lp_shaft.trq_1') self.connect('lpt.trq', 'lp_shaft.trq_2') self.connect('hpc.trq', 'hp_shaft.trq_0') self.connect('hpt.trq', 'hp_shaft.trq_1') 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', BalanceComp()) if design: balance.add_balance('W', units='lbm/s', eq_units='lbf') 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=.017) self.connect('balance.FAR', 'burner.Fl_I:FAR') self.connect('burner.Fl_O:tot:T', 'balance.lhs:FAR') 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') else: balance.add_balance('FAR', val=0.017, lower=1e-4, eq_units='lbf') self.connect('balance.FAR', 'burner.Fl_I:FAR') self.connect('perf.Fn', 'balance.lhs:FAR') balance.add_balance('W', units='lbm/s', lower=10., upper=1000., eq_units='inch**2') self.connect('balance.W', 'inlet.Fl_I:stat:W') self.connect('core_nozz.Throat:stat:area', 'balance.lhs:W') balance.add_balance('BPR', lower=2., upper=10., eq_units='inch**2') self.connect('balance.BPR', 'splitter.BPR') self.connect('byp_nozz.Throat:stat:area', 'balance.lhs:BPR') balance.add_balance('lp_Nmech', val=1.5, units='rpm', lower=500., eq_units='hp', use_mult=True, mult_val=-1) self.connect('balance.lp_Nmech', 'LP_Nmech') self.connect('lp_shaft.pwr_in_real', 'balance.lhs:lp_Nmech') self.connect('lp_shaft.pwr_out_real', 'balance.rhs:lp_Nmech') balance.add_balance('hp_Nmech', val=1.5, units='rpm', lower=500., eq_units='hp', use_mult=True, mult_val=-1) self.connect('balance.hp_Nmech', 'HP_Nmech') self.connect('hp_shaft.pwr_in_real', 'balance.lhs:hp_Nmech') self.connect('hp_shaft.pwr_out_real', 'balance.rhs:hp_Nmech') self.set_order(['balance', 'fc', 'inlet', 'fan', 'splitter', 'duct4', 'lpc', 'duct6', 'hpc', 'bld3', 'burner', 'hpt', 'duct11', 'lpt', 'duct13', 'core_nozz', 'byp_bld', 'duct15', 'byp_nozz', 'lp_shaft', 'hp_shaft', 'perf']) connect_flow(self, 'fc.Fl_O', 'inlet.Fl_I', connect_w=False) connect_flow(self, 'inlet.Fl_O', 'fan.Fl_I') connect_flow(self, 'fan.Fl_O', 'splitter.Fl_I') connect_flow(self, 'splitter.Fl_O1', 'duct4.Fl_I') connect_flow(self, 'duct4.Fl_O', 'lpc.Fl_I') connect_flow(self, 'lpc.Fl_O', 'duct6.Fl_I') connect_flow(self, 'duct6.Fl_O', 'hpc.Fl_I') connect_flow(self, 'hpc.Fl_O', 'bld3.Fl_I') connect_flow(self, 'bld3.Fl_O', 'burner.Fl_I') connect_flow(self, 'burner.Fl_O', 'hpt.Fl_I') connect_flow(self, 'hpt.Fl_O', 'duct11.Fl_I') connect_flow(self, 'duct11.Fl_O', 'lpt.Fl_I') connect_flow(self, 'lpt.Fl_O', 'duct13.Fl_I') connect_flow(self, 'duct13.Fl_O','core_nozz.Fl_I') connect_flow(self, 'splitter.Fl_O2', 'byp_bld.Fl_I') connect_flow(self, 'byp_bld.Fl_O', 'duct15.Fl_I') connect_flow(self, 'duct15.Fl_O', 'byp_nozz.Fl_I') connect_flow(self, 'hpc.cool1', 'lpt.cool1', connect_stat=False) connect_flow(self, 'hpc.cool2', 'lpt.cool2', connect_stat=False) connect_flow(self, 'bld3.cool3', 'hpt.cool3', connect_stat=False) connect_flow(self, 'bld3.cool4', 'hpt.cool4', connect_stat=False) newton = self.nonlinear_solver = NewtonSolver() newton.options['atol'] = 1e-8 newton.options['rtol'] = 1e-8 newton.options['iprint'] = 2 newton.options['maxiter'] = 50 newton.options['solve_subsystems'] = True newton.options['max_sub_solves'] = 100 # ls = newton.linesearch = BoundsEnforceLS() ls = newton.linesearch = ArmijoGoldsteinLS() ls.options['maxiter'] = 3 ls.options['bound_enforcement'] = 'scalar' # ls.options['print_bound_enforce'] = True self.linear_solver = DirectSolver(assemble_jac=True)
def setup(self): thermo_spec = species_data.janaf design = self.options['design'] self.add_subsystem('fc', FlightConditions(thermo_data=thermo_spec, elements=AIR_MIX)) # Inlet Components self.add_subsystem('inlet', Inlet(design=design, thermo_data=thermo_spec, elements=AIR_MIX)) self.add_subsystem('inlet_duct', Duct(design=design, thermo_data=thermo_spec, elements=AIR_MIX)) # Fan Components - Split here for CFD integration Add a CFDStart Compomponent self.add_subsystem('fan', Compressor(map_data=AXI5, design=design, thermo_data=thermo_spec, elements=AIR_MIX, map_extrap=True),promotes_inputs=[('Nmech','LP_Nmech')]) self.add_subsystem('splitter', Splitter(design=design, thermo_data=thermo_spec, elements=AIR_MIX)) # Core Stream components self.add_subsystem('splitter_core_duct', Duct(design=design, thermo_data=thermo_spec, elements=AIR_MIX)) self.add_subsystem('lpc', Compressor(map_data=LPCmap, design=design, thermo_data=thermo_spec, elements=AIR_MIX,map_extrap=True), promotes_inputs=[('Nmech','LP_Nmech')]) self.add_subsystem('lpc_duct', Duct(design=design, thermo_data=thermo_spec, elements=AIR_MIX)) self.add_subsystem('hpc', Compressor(map_data=HPCmap, design=design, thermo_data=thermo_spec, elements=AIR_MIX, bleed_names=['cool1'],map_extrap=True),promotes_inputs=[('Nmech','HP_Nmech')]) self.add_subsystem('bld3', BleedOut(design=design, bleed_names=['cool3'])) self.add_subsystem('burner', Combustor(design=design,thermo_data=thermo_spec, inflow_elements=AIR_MIX, air_fuel_elements=AIR_FUEL_MIX, fuel_type='Jet-A(g)')) self.add_subsystem('hpt', Turbine(map_data=HPTmap, design=design, thermo_data=thermo_spec, elements=AIR_FUEL_MIX, bleed_names=['cool3'],map_extrap=True),promotes_inputs=[('Nmech','HP_Nmech')]) self.add_subsystem('hpt_duct', Duct(design=design, thermo_data=thermo_spec, elements=AIR_FUEL_MIX)) self.add_subsystem('lpt', Turbine(map_data=LPTmap, design=design, thermo_data=thermo_spec, elements=AIR_FUEL_MIX, bleed_names=['cool1'],map_extrap=True), promotes_inputs=[('Nmech','LP_Nmech')]) self.add_subsystem('lpt_duct', Duct(design=design, thermo_data=thermo_spec, elements=AIR_FUEL_MIX)) # Bypass Components self.add_subsystem('bypass_duct', Duct(design=design, thermo_data=thermo_spec, elements=AIR_MIX)) # Mixer component self.add_subsystem('mixer', Mixer(design=design, designed_stream=1, Fl_I1_elements=AIR_FUEL_MIX, Fl_I2_elements=AIR_MIX)) self.add_subsystem('mixer_duct', Duct(design=design, thermo_data=thermo_spec, elements=AIR_FUEL_MIX)) # Afterburner Components self.add_subsystem('afterburner', Combustor(design=design,thermo_data=thermo_spec, inflow_elements=AIR_FUEL_MIX, air_fuel_elements=AIR_FUEL_MIX, fuel_type='Jet-A(g)')) # End CFD HERE # Nozzle self.add_subsystem('mixed_nozz', Nozzle(nozzType='CD', lossCoef='Cfg', thermo_data=thermo_spec, elements=AIR_FUEL_MIX)) # Mechanical components self.add_subsystem('lp_shaft', Shaft(num_ports=3),promotes_inputs=[('Nmech','LP_Nmech')]) self.add_subsystem('hp_shaft', Shaft(num_ports=2),promotes_inputs=[('Nmech','HP_Nmech')]) # Aggregating component self.add_subsystem('perf', Performance(num_nozzles=1, num_burners=2)) # Connnect flow path connect_flow(self, 'fc.Fl_O', 'inlet.Fl_I') connect_flow(self, 'inlet.Fl_O', 'inlet_duct.Fl_I') connect_flow(self, 'inlet_duct.Fl_O', 'fan.Fl_I') connect_flow(self, 'fan.Fl_O', 'splitter.Fl_I') # Core connections connect_flow(self, 'splitter.Fl_O1', 'splitter_core_duct.Fl_I') connect_flow(self, 'splitter_core_duct.Fl_O', 'lpc.Fl_I') connect_flow(self, 'lpc.Fl_O', 'lpc_duct.Fl_I') connect_flow(self, 'lpc_duct.Fl_O', 'hpc.Fl_I') connect_flow(self, 'hpc.Fl_O', 'bld3.Fl_I') connect_flow(self, 'bld3.Fl_O', 'burner.Fl_I') connect_flow(self, 'burner.Fl_O', 'hpt.Fl_I') connect_flow(self, 'hpt.Fl_O', 'hpt_duct.Fl_I') connect_flow(self, 'hpt_duct.Fl_O', 'lpt.Fl_I') connect_flow(self, 'lpt.Fl_O', 'lpt_duct.Fl_I') connect_flow(self, 'lpt_duct.Fl_O','mixer.Fl_I1') # Bypass Connections connect_flow(self, 'splitter.Fl_O2', 'bypass_duct.Fl_I') connect_flow(self, 'bypass_duct.Fl_O', 'mixer.Fl_I2') #Mixer Connections connect_flow(self, 'mixer.Fl_O', 'mixer_duct.Fl_I') # After Burner connect_flow(self,'mixer_duct.Fl_O','afterburner.Fl_I') # Nozzle connect_flow(self,'afterburner.Fl_O','mixed_nozz.Fl_I') # Connect cooling flows connect_flow(self, 'hpc.cool1', 'lpt.cool1', connect_stat=False) connect_flow(self, 'bld3.cool3', 'hpt.cool3', connect_stat=False) # Make additional model connections 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('afterburner.Wfuel', 'perf.Wfuel_1') self.connect('inlet.F_ram', 'perf.ram_drag') self.connect('mixed_nozz.Fg', 'perf.Fg_0') self.connect('fan.trq', 'lp_shaft.trq_0') self.connect('lpc.trq', 'lp_shaft.trq_1') self.connect('lpt.trq', 'lp_shaft.trq_2') self.connect('hpc.trq', 'hp_shaft.trq_0') self.connect('hpt.trq', 'hp_shaft.trq_1') self.connect('fc.Fl_O:stat:P', 'mixed_nozz.Ps_exhaust') # Add balence components to close the implicit components balance = self.add_subsystem('balance', BalanceComp()) if design: balance.add_balance('W', lower=1e-3, upper=200., units='lbm/s', eq_units='lbf') self.connect('balance.W', 'fc.W') self.connect('perf.Fn', 'balance.lhs:W') # self.add_subsystem('wDV',IndepVarComp('wDes',100,units='lbm/s')) # self.connect('wDV.wDes','fc.W') balance.add_balance('BPR', eq_units=None, lower=0.25, val=5.0) self.connect('balance.BPR', 'splitter.BPR') self.connect('mixer.ER', 'balance.lhs:BPR') balance.add_balance('FAR_core', eq_units='degR', lower=1e-4, val=.017) self.connect('balance.FAR_core', 'burner.Fl_I:FAR') self.connect('burner.Fl_O:tot:T', 'balance.lhs:FAR_core') balance.add_balance('FAR_ab', eq_units='degR', lower=1e-4, val=.017) self.connect('balance.FAR_ab', 'afterburner.Fl_I:FAR') self.connect('afterburner.Fl_O:tot:T', 'balance.lhs:FAR_ab') 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', 'balance.lhs:lpt_PR') self.connect('lp_shaft.pwr_out', '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', 'balance.lhs:hpt_PR') self.connect('hp_shaft.pwr_out', 'balance.rhs:hpt_PR') else: balance.add_balance('W', lower=1e-3, upper=200., units='lbm/s', eq_units='inch**2') self.connect('balance.W', 'fc.W') self.connect('mixed_nozz.Throat:stat:area', 'balance.lhs:W') balance.add_balance('BPR', lower=0.25, upper=5.0, eq_units='psi') self.connect('balance.BPR', 'splitter.BPR') self.connect('mixer.Fl_I1_calc:stat:P', 'balance.lhs:BPR') self.connect('bypass_duct.Fl_O:stat:P', 'balance.rhs:BPR') balance.add_balance('FAR_core', eq_units='degR', lower=1e-4, upper=.06, val=.017) self.connect('balance.FAR_core', 'burner.Fl_I:FAR') self.connect('burner.Fl_O:tot:T', 'balance.lhs:FAR_core') balance.add_balance('FAR_ab', eq_units='degR', lower=1e-4, upper=.06, val=.017) self.connect('balance.FAR_ab', 'afterburner.Fl_I:FAR') self.connect('afterburner.Fl_O:tot:T', 'balance.lhs:FAR_ab') balance.add_balance('LP_Nmech', val=1., units='rpm', lower=500., eq_units='hp', use_mult=True, mult_val=-1) self.connect('balance.LP_Nmech', 'LP_Nmech') self.connect('lp_shaft.pwr_in', 'balance.lhs:LP_Nmech') self.connect('lp_shaft.pwr_out', 'balance.rhs:LP_Nmech') balance.add_balance('HP_Nmech', val=1., units='rpm', lower=500., eq_units='hp', use_mult=True, mult_val=-1) self.connect('balance.HP_Nmech', 'HP_Nmech') self.connect('hp_shaft.pwr_in', 'balance.lhs:HP_Nmech') self.connect('hp_shaft.pwr_out', 'balance.rhs:HP_Nmech') # Off design newton = self.nonlinear_solver = NewtonSolver() newton.options['atol'] = 1e-6 newton.options['rtol'] = 1e-10 newton.options['iprint'] = 2 newton.options['maxiter'] = 10 newton.options['solve_subsystems'] = True newton.options['max_sub_solves'] = 100 newton.linesearch = BoundsEnforceLS() newton.linesearch.options['bound_enforcement'] = 'scalar' newton.linesearch.options['iprint'] = -1 self.linear_solver = DirectSolver(assemble_jac=True)
def setup(self): thermo_spec = species_data.janaf design = self.options['design'] statics = self.options['statics'] self.add_subsystem('fc', FlightConditions(thermo_data=thermo_spec, elements=AIR_MIX)) self.add_subsystem('inlet', Inlet(design=design, thermo_data=thermo_spec, elements=AIR_MIX)) self.add_subsystem('duct1', Duct(design=design, thermo_data=thermo_spec, elements=AIR_MIX, statics=statics)) self.add_subsystem('comp', Compressor(map_data=AXI5, design=design, thermo_data=thermo_spec, elements=AIR_MIX, bleed_names=['cool1','cool2'], statics=statics, map_extrap=True),promotes_inputs=['Nmech']) self.add_subsystem('burner', Combustor(design=design,thermo_data=thermo_spec, inflow_elements=AIR_MIX, air_fuel_elements=AIR_FUEL_MIX, fuel_type='JP-7', statics=statics)) self.add_subsystem('turb', Turbine(map_data=LPT2269, design=design, thermo_data=thermo_spec, elements=AIR_FUEL_MIX, bleed_names=['cool1','cool2'], statics=statics, map_extrap=True),promotes_inputs=['Nmech']) self.add_subsystem('ab', Combustor(design=design,thermo_data=thermo_spec, inflow_elements=AIR_FUEL_MIX, air_fuel_elements=AIR_FUEL_MIX, fuel_type='JP-7', statics=statics)) self.add_subsystem('nozz', Nozzle(nozzType='CD', lossCoef='Cv', thermo_data=thermo_spec, elements=AIR_FUEL_MIX, internal_solver=True)) self.add_subsystem('shaft', Shaft(num_ports=2),promotes_inputs=['Nmech']) self.add_subsystem('perf', Performance(num_nozzles=1, num_burners=2)) self.connect('duct1.Fl_O:tot:P', 'perf.Pt2') self.connect('comp.Fl_O:tot:P', 'perf.Pt3') self.connect('burner.Wfuel', 'perf.Wfuel_0') self.connect('ab.Wfuel', 'perf.Wfuel_1') self.connect('inlet.F_ram', 'perf.ram_drag') self.connect('nozz.Fg', 'perf.Fg_0') self.connect('comp.trq', 'shaft.trq_0') self.connect('turb.trq', 'shaft.trq_1') # self.connect('shaft.Nmech', 'comp.Nmech') # self.connect('shaft.Nmech', 'turb.Nmech') self.connect('fc.Fl_O:stat:P', 'nozz.Ps_exhaust') balance = self.add_subsystem('balance', BalanceComp()) if design: balance.add_balance('W', units='lbm/s', eq_units='lbf') 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=.017) 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.) self.connect('balance.turb_PR', 'turb.PR') self.connect('shaft.pwr_net', 'balance.lhs:turb_PR') # self.set_order(['fc', 'inlet', 'duct1', 'comp', 'burner', 'turb', 'ab', 'nozz', 'shaft', 'perf', 'thrust_balance', 'temp_balance', 'shaft_balance']) self.set_order(['balance', 'fc', 'inlet', 'duct1', 'comp', 'burner', 'turb', 'ab', 'nozz', 'shaft', 'perf']) else: balance.add_balance('FAR', eq_units='degR', lower=1e-4, val=.017) self.connect('balance.FAR', 'burner.Fl_I:FAR') self.connect('burner.Fl_O:tot:T', 'balance.lhs:FAR') balance.add_balance('Nmech', val=8000., units='rpm', lower=500., eq_units='hp', rhs_val=0.) self.connect('balance.Nmech', 'Nmech') self.connect('shaft.pwr_net', 'balance.lhs:Nmech') balance.add_balance('W', val=100.0, units='lbm/s', eq_units=None, rhs_val=2.0) self.connect('balance.W', 'inlet.Fl_I:stat:W') self.connect('comp.map.RlineMap', 'balance.lhs:W') self.set_order(['balance', 'fc', 'inlet', 'duct1', 'comp', 'burner', 'turb', 'ab', 'nozz', 'shaft', 'perf']) if statics: connect_flow(self, 'fc.Fl_O', 'inlet.Fl_I', connect_w=False) connect_flow(self, 'inlet.Fl_O', 'duct1.Fl_I') connect_flow(self, 'duct1.Fl_O', 'comp.Fl_I') connect_flow(self, 'comp.Fl_O', 'burner.Fl_I') connect_flow(self, 'burner.Fl_O', 'turb.Fl_I') connect_flow(self, 'turb.Fl_O', 'ab.Fl_I') connect_flow(self, 'ab.Fl_O', 'nozz.Fl_I') else: connect_flow(self, 'fc.Fl_O', 'inlet.Fl_I', connect_w=False) connect_flow(self, 'inlet.Fl_O', 'duct1.Fl_I', connect_stat=False) connect_flow(self, 'duct1.Fl_O', 'comp.Fl_I', connect_stat=False) connect_flow(self, 'comp.Fl_O', 'burner.Fl_I', connect_stat=False) connect_flow(self, 'burner.Fl_O', 'turb.Fl_I', connect_stat=False) connect_flow(self, 'turb.Fl_O', 'ab.Fl_I', connect_stat=False) connect_flow(self, 'ab.Fl_O', 'nozz.Fl_I', connect_stat=False) connect_flow(self, 'comp.cool1', 'turb.cool1', connect_stat=False) connect_flow(self, 'comp.cool2', 'turb.cool2', connect_stat=False) newton = self.nonlinear_solver = 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.linesearch = BoundsEnforceLS() newton.linesearch = ArmijoGoldsteinLS() # newton.linesearch.options['c'] = .0001 newton.linesearch.options['bound_enforcement'] = 'scalar' newton.linesearch.options['iprint'] = -1 self.linear_solver = DirectSolver(assemble_jac=True)
def setup(self): thermo_spec = species_data.janaf design = self.options['design'] # Add engine elements self.add_subsystem( 'fc', FlightConditions(thermo_data=thermo_spec, elements=AIR_MIX)) self.add_subsystem( 'inlet', Inlet(design=design, thermo_data=thermo_spec, elements=AIR_MIX)) self.add_subsystem('comp', Compressor( map_data=AXI5, design=design, thermo_data=thermo_spec, elements=AIR_MIX, ), promotes_inputs=[('Nmech', 'HP_Nmech')]) self.add_subsystem( 'burner', Combustor(design=design, thermo_data=thermo_spec, inflow_elements=AIR_MIX, air_fuel_elements=AIR_FUEL_MIX, fuel_type='JP-7')) self.add_subsystem('turb', Turbine( map_data=LPT2269, design=design, thermo_data=thermo_spec, elements=AIR_FUEL_MIX, ), promotes_inputs=[('Nmech', 'HP_Nmech')]) self.add_subsystem('pt', Turbine( map_data=LPT2269, design=design, thermo_data=thermo_spec, elements=AIR_FUEL_MIX, ), promotes_inputs=[('Nmech', 'LP_Nmech')]) self.add_subsystem( 'nozz', Nozzle(nozzType='CV', lossCoef='Cv', thermo_data=thermo_spec, elements=AIR_FUEL_MIX)) self.add_subsystem('HP_shaft', Shaft(num_ports=2), promotes_inputs=[('Nmech', 'HP_Nmech')]) self.add_subsystem('LP_shaft', Shaft(num_ports=1), promotes_inputs=[('Nmech', 'LP_Nmech')]) self.add_subsystem('perf', Performance(num_nozzles=1, num_burners=1)) # Connect flow stations connect_flow(self, 'fc.Fl_O', 'inlet.Fl_I', connect_w=False) connect_flow(self, 'inlet.Fl_O', 'comp.Fl_I') connect_flow(self, 'comp.Fl_O', 'burner.Fl_I') connect_flow(self, 'burner.Fl_O', 'turb.Fl_I') connect_flow(self, 'turb.Fl_O', 'pt.Fl_I') connect_flow(self, 'pt.Fl_O', 'nozz.Fl_I') # Connect turbomachinery elements to shaft self.connect('comp.trq', 'HP_shaft.trq_0') self.connect('turb.trq', 'HP_shaft.trq_1') self.connect('pt.trq', 'LP_shaft.trq_0') # Connnect nozzle exhaust to freestream static conditions self.connect('fc.Fl_O:stat:P', 'nozz.Ps_exhaust') # Connect outputs to pefromance 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') self.connect('LP_shaft.pwr_net', 'perf.power') # Add balances for design and off-design balance = self.add_subsystem('balance', BalanceComp()) if design: balance.add_balance('W', val=27.0, units='lbm/s', eq_units=None) self.connect('balance.W', 'inlet.Fl_I:stat:W') self.connect('nozz.PR', 'balance.lhs:W') balance.add_balance('FAR', eq_units='degR', lower=1e-4, val=.017) self.connect('balance.FAR', 'burner.Fl_I:FAR') self.connect('burner.Fl_O:tot:T', 'balance.lhs:FAR') balance.add_balance('turb_PR', val=3.0, lower=1.001, upper=8, eq_units='hp', rhs_val=0.) self.connect('balance.turb_PR', 'turb.PR') self.connect('HP_shaft.pwr_net', 'balance.lhs:turb_PR') balance.add_balance('pt_PR', val=3.0, lower=1.001, upper=8, eq_units='hp') self.connect('balance.pt_PR', 'pt.PR') self.connect('LP_shaft.pwr_net', 'balance.lhs:pt_PR') else: balance.add_balance('FAR', eq_units='hp', lower=1e-4, val=.3) self.connect('balance.FAR', 'burner.Fl_I:FAR') self.connect('LP_shaft.pwr_net', 'balance.lhs:FAR') balance.add_balance('HP_Nmech', val=1.5, units='rpm', lower=500., eq_units='hp', rhs_val=0.) self.connect('balance.HP_Nmech', 'HP_Nmech') self.connect('HP_shaft.pwr_net', 'balance.lhs:HP_Nmech') balance.add_balance('W', val=27.0, units='lbm/s', eq_units='inch**2') self.connect('balance.W', 'inlet.Fl_I:stat:W') self.connect('nozz.Throat:stat:area', 'balance.lhs:W') # Setup solver to converge engine self.set_order([ 'balance', 'fc', 'inlet', 'comp', 'burner', 'turb', 'pt', 'nozz', 'HP_shaft', 'LP_shaft', 'perf' ]) newton = self.nonlinear_solver = 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.linesearch = BoundsEnforceLS() # newton.linesearch = ArmijoGoldsteinLS() # newton.linesearch.options['c'] = .0001 newton.linesearch.options['bound_enforcement'] = 'scalar' newton.linesearch.options['iprint'] = -1 self.linear_solver = DirectSolver(assemble_jac=True)
def test_case_with_dPqP_MN(self): thermo = Thermo(janaf, constants.AIR_MIX) self.prob = Problem() self.prob.model = Group() self.prob.model.add_subsystem('flow_start', FlowStart(thermo_data=janaf, elements=AIR_MIX), promotes=['P', 'T', 'MN', 'W']) self.prob.model.add_subsystem('flow_start_OD', FlowStart(thermo_data=janaf, elements=AIR_MIX), promotes=['P', 'T', 'W']) expMN = 1.0 self.prob.model.add_subsystem('duct_des', Duct(elements=AIR_MIX, expMN=expMN), promotes=['MN']) self.prob.model.add_subsystem( 'duct_OD', Duct(elements=AIR_MIX, expMN=expMN, design=False)) connect_flow(self.prob.model, 'flow_start.Fl_O', 'duct_des.Fl_I') connect_flow(self.prob.model, 'flow_start_OD.Fl_O', 'duct_OD.Fl_I') self.prob.model.set_input_defaults('P', 17., units='psi') self.prob.model.set_input_defaults('T', 500., units='degR') self.prob.model.set_input_defaults('MN', 0.5) self.prob.model.set_input_defaults('flow_start_OD.MN', 0.25) self.prob.model.set_input_defaults('duct_des.dPqP', 0.0) self.prob.model.set_input_defaults('W', 500., units='lbm/s') self.prob.model.connect("duct_des.s_dPqP", "duct_OD.s_dPqP") self.prob.model.connect("duct_des.Fl_O:stat:area", "duct_OD.area") self.prob.setup(check=False) self.prob.set_solver_print(level=-1) data = ref_data[0] self.prob['duct_des.dPqP'] = data[h_map['dPqP']] # input flowstation self.prob['P'] = data[h_map['Fl_I.Pt']] self.prob['T'] = data[h_map['Fl_I.Tt']] self.prob['MN'] = data[h_map['Fl_O.MN']] self.prob['W'] = data[h_map['Fl_I.W']] self.prob['duct_des.Fl_I:stat:V'] = data[h_map['Fl_I.V']] # give a decent initial guess for Ps print(self.prob['P'], self.prob['T'], self.prob['MN']) self.prob.run_model() # check outputs pt, ht, ps, ts = data[h_map['Fl_O.Pt']], data[h_map['Fl_O.ht']], data[ h_map['Fl_O.Ps']], data[h_map['Fl_O.Ts']] pt_computed = self.prob['duct_OD.Fl_O:tot:P'] ht_computed = self.prob['duct_OD.Fl_O:tot:h'] ps_computed = self.prob['duct_OD.Fl_O:stat:P'] ts_computed = self.prob['duct_OD.Fl_O:stat:T'] tol = 1.0e-4 assert_near_equal(pt_computed, 8.84073152, tol) assert_near_equal(ht_computed, ht, tol) assert_near_equal(ps_computed, 8.26348914, tol) assert_near_equal(ts_computed, ts, tol) check_element_partials(self, self.prob)
dv.add_output('frac_P', 0.5), prob.model.add_subsystem( 'flow_start', FlowStart(thermo_data=species_data.janaf, elements=AIR_MIX)) prob.model.add_subsystem( 'bld_start', FlowStart(thermo_data=species_data.janaf, elements=AIR_MIX)) prob.model.add_subsystem( 'turbine', Turbine(map_data=LPT2269, design=True, elements=AIR_MIX, bleed_names=['bld1'])) connect_flow(prob.model, 'flow_start.Fl_O', 'turbine.Fl_I') connect_flow(prob.model, 'bld_start.Fl_O', 'turbine.bld1', connect_stat=False) prob.model.connect("P", "flow_start.P") prob.model.connect("T", "flow_start.T") prob.model.connect("W", "flow_start.W") prob.model.connect("P_bld", "bld_start.P") prob.model.connect("T_bld", "bld_start.T") prob.model.connect("W_bld", "bld_start.W") prob.model.connect("PR", "turbine.PR") prob.model.connect('eff', 'turbine.eff') prob.model.connect("frac_P", "turbine.bld1:frac_P")