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):
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 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']
# 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 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']
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)