def setup(self):
thermo_spec = pyc.species_data.janaf
design = self.options['design']
cooling = self.options['cooling']
self.pyc_add_element(
'fc',
pyc.FlightConditions(thermo_data=thermo_spec,
elements=pyc.AIR_MIX))
self.pyc_add_element(
'inlet',
pyc.Inlet(design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_MIX))
self.pyc_add_element('fan',
pyc.Compressor(map_data=FanMap,
design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_MIX,
map_extrap=True,
bleed_names=[]),
promotes_inputs=[('Nmech', 'Fan_Nmech')])
self.pyc_add_element(
'splitter',
pyc.Splitter(design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_MIX))
self.pyc_add_element(
'duct2',
pyc.Duct(design=design,
expMN=2.0,
thermo_data=thermo_spec,
elements=pyc.AIR_MIX))
self.pyc_add_element('lpc',
pyc.Compressor(map_data=LPCMap,
design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_MIX,
map_extrap=True),
promotes_inputs=[('Nmech', 'LP_Nmech')])
self.pyc_add_element('bld25',
pyc.BleedOut(design=design, bleed_names=['sbv']))
self.pyc_add_element(
'duct25',
pyc.Duct(design=design,
expMN=2.0,
thermo_data=thermo_spec,
elements=pyc.AIR_MIX))
self.pyc_add_element(
'hpc',
pyc.Compressor(map_data=HPCMap,
design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_MIX,
map_extrap=True,
bleed_names=['bld_inlet', 'bld_exit', 'cust']),
promotes_inputs=[('Nmech', 'HP_Nmech')])
self.pyc_add_element(
'bld3',
pyc.BleedOut(design=design, bleed_names=['bld_inlet', 'bld_exit']))
self.pyc_add_element(
'burner',
pyc.Combustor(design=design,
thermo_data=thermo_spec,
inflow_elements=pyc.AIR_MIX,
air_fuel_elements=pyc.AIR_FUEL_MIX,
fuel_type='Jet-A(g)'))
self.pyc_add_element('hpt',
pyc.Turbine(map_data=HPTMap,
design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_FUEL_MIX,
map_extrap=True,
bleed_names=['bld_inlet',
'bld_exit']),
promotes_inputs=[('Nmech', 'HP_Nmech')])
self.pyc_add_element(
'duct45',
pyc.Duct(design=design,
expMN=2.0,
thermo_data=thermo_spec,
elements=pyc.AIR_FUEL_MIX))
self.pyc_add_element('lpt',
pyc.Turbine(map_data=LPTMap,
design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_FUEL_MIX,
map_extrap=True,
bleed_names=['bld_inlet',
'bld_exit']),
promotes_inputs=[('Nmech', 'LP_Nmech')])
self.pyc_add_element(
'duct5',
pyc.Duct(design=design,
expMN=2.0,
thermo_data=thermo_spec,
elements=pyc.AIR_FUEL_MIX))
self.pyc_add_element(
'core_nozz',
pyc.Nozzle(nozzType='CV',
lossCoef='Cv',
thermo_data=thermo_spec,
elements=pyc.AIR_FUEL_MIX))
self.pyc_add_element(
'byp_bld', pyc.BleedOut(design=design, bleed_names=['bypBld']))
self.pyc_add_element(
'duct17',
pyc.Duct(design=design,
expMN=2.0,
thermo_data=thermo_spec,
elements=pyc.AIR_MIX))
self.pyc_add_element(
'byp_nozz',
pyc.Nozzle(nozzType='CV',
lossCoef='Cv',
thermo_data=thermo_spec,
elements=pyc.AIR_MIX))
self.pyc_add_element('fan_shaft',
pyc.Shaft(num_ports=2),
promotes_inputs=[('Nmech', 'Fan_Nmech')])
self.pyc_add_element('gearbox',
pyc.Gearbox(design=design),
promotes_inputs=[('N_in', 'LP_Nmech'),
('N_out', 'Fan_Nmech')])
self.pyc_add_element('lp_shaft',
pyc.Shaft(num_ports=3),
promotes_inputs=[('Nmech', 'LP_Nmech')])
self.pyc_add_element('hp_shaft',
pyc.Shaft(num_ports=2),
promotes_inputs=[('Nmech', 'HP_Nmech')])
self.pyc_add_element('perf',
pyc.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', 'fan_shaft.trq_0')
self.connect('gearbox.trq_out', 'fan_shaft.trq_1')
self.connect('gearbox.trq_in', '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')
self.add_subsystem(
'ext_ratio',
om.ExecComp(
'ER = core_V_ideal * core_Cv / ( byp_V_ideal * byp_Cv )',
core_V_ideal={
'value': 1000.0,
'units': 'ft/s'
},
core_Cv={
'value': 0.98,
'units': None
},
byp_V_ideal={
'value': 1000.0,
'units': 'ft/s'
},
byp_Cv={
'value': 0.98,
'units': None
},
ER={
'value': 1.4,
'units': None
}))
self.connect('core_nozz.ideal_flow.V', 'ext_ratio.core_V_ideal')
self.connect('byp_nozz.ideal_flow.V', 'ext_ratio.byp_V_ideal')
main_order = [
'fc', 'inlet', 'fan', 'splitter', 'duct2', 'lpc', 'bld25',
'duct25', 'hpc', 'bld3', 'burner', 'hpt', 'duct45', 'lpt', 'duct5',
'core_nozz', 'byp_bld', 'duct17', 'byp_nozz', 'gearbox',
'fan_shaft', 'lp_shaft', 'hp_shaft', 'perf', 'ext_ratio'
]
balance = self.add_subsystem('balance', om.BalanceComp())
if design:
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=10.937,
lower=1.001,
upper=20,
eq_units='hp',
rhs_val=0.,
res_ref=1e4)
self.connect('balance.lpt_PR', 'lpt.PR')
self.connect('lp_shaft.pwr_net', 'balance.lhs:lpt_PR')
balance.add_balance('hpt_PR',
val=4.185,
lower=1.001,
upper=8,
eq_units='hp',
rhs_val=0.,
res_ref=1e4)
self.connect('balance.hpt_PR', 'hpt.PR')
self.connect('hp_shaft.pwr_net', 'balance.lhs:hpt_PR')
balance.add_balance('gb_trq',
val=23928.0,
units='ft*lbf',
eq_units='hp',
rhs_val=0.0)
self.connect('balance.gb_trq', 'gearbox.trq_base')
self.connect('fan_shaft.pwr_net', 'balance.lhs:gb_trq')
balance.add_balance('hpc_PR', val=14.0, units=None, eq_units=None)
self.connect('balance.hpc_PR', ['hpc.PR', 'opr_calc.HPCPR'])
# self.connect('perf.OPR', 'balance.lhs:hpc_PR')
self.connect('opr_calc.OPR_simple', 'balance.lhs:hpc_PR')
balance.add_balance('fan_eff',
val=0.9689,
units=None,
eq_units=None)
self.connect('balance.fan_eff', 'fan.eff')
self.connect('fan.eff_poly', 'balance.lhs:fan_eff')
balance.add_balance('lpc_eff',
val=0.8895,
units=None,
eq_units=None)
self.connect('balance.lpc_eff', 'lpc.eff')
self.connect('lpc.eff_poly', 'balance.lhs:lpc_eff')
# balance.add_balance('hpc_eff', val=0.8470, units=None, eq_units=None)
# self.connect('balance.hpc_eff', 'hpc.eff')
# self.connect('hpc.eff_poly', 'balance.lhs:hpc_eff')
balance.add_balance('hpt_eff',
val=0.9226,
units=None,
eq_units=None)
self.connect('balance.hpt_eff', 'hpt.eff')
self.connect('hpt.eff_poly', 'balance.lhs:hpt_eff')
balance.add_balance('lpt_eff',
val=0.9401,
units=None,
eq_units=None)
self.connect('balance.lpt_eff', 'lpt.eff')
self.connect('lpt.eff_poly', 'balance.lhs:lpt_eff')
self.add_subsystem(
'hpc_CS',
om.ExecComp('CS = Win *(pow(Tout/518.67,0.5)/(Pout/14.696))',
Win={
'value': 10.0,
'units': 'lbm/s'
},
Tout={
'value': 14.696,
'units': 'degR'
},
Pout={
'value': 518.67,
'units': 'psi'
},
CS={
'value': 10.0,
'units': 'lbm/s'
}))
self.connect('duct25.Fl_O:stat:W', 'hpc_CS.Win')
self.connect('hpc.Fl_O:tot:T', 'hpc_CS.Tout')
self.connect('hpc.Fl_O:tot:P', 'hpc_CS.Pout')
self.add_subsystem(
'hpc_EtaBalance',
SmallCoreEffBalance(eng_type='large', tech_level=0))
self.connect('hpc_CS.CS', 'hpc_EtaBalance.CS')
self.connect('hpc.eff_poly', 'hpc_EtaBalance.eta_p')
self.connect('hpc_EtaBalance.eta_a', 'hpc.eff')
self.add_subsystem(
'fan_dia',
om.ExecComp('FanDia = 2.0*(area/(pi*(1.0-hub_tip**2.0)))**0.5',
area={
'value': 7000.0,
'units': 'inch**2'
},
hub_tip={
'value': 0.3125,
'units': None
},
FanDia={
'value': 100.0,
'units': 'inch'
}))
self.connect('inlet.Fl_O:stat:area', 'fan_dia.area')
self.add_subsystem(
'opr_calc',
om.ExecComp('OPR_simple = FPR*LPCPR*HPCPR',
FPR={
'value': 1.3,
'units': None
},
LPCPR={
'value': 3.0,
'units': None
},
HPCPR={
'value': 14.0,
'units': None
},
OPR_simple={
'value': 55.0,
'units': None
}))
# order_add = ['hpc_CS', 'fan_dia', 'opr_calc']
order_add = ['hpc_CS', 'hpc_EtaBalance', 'fan_dia', 'opr_calc']
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')
# self.connect('burner.Fl_O:tot:T', 'balance.lhs:FAR')
balance.add_balance('W',
units='lbm/s',
lower=10.,
upper=2500.,
eq_units='inch**2')
self.connect('balance.W', 'fc.W')
self.connect('core_nozz.Throat:stat:area', 'balance.lhs:W')
balance.add_balance('BPR', lower=15., upper=40.)
self.connect('balance.BPR', 'splitter.BPR')
self.connect('fan.map.RlineMap', 'balance.lhs:BPR')
balance.add_balance('fan_Nmech',
val=2000.0,
units='rpm',
lower=500.,
eq_units='hp',
rhs_val=0.,
res_ref=1e2)
self.connect('balance.fan_Nmech', 'Fan_Nmech')
self.connect('fan_shaft.pwr_net', 'balance.lhs:fan_Nmech')
balance.add_balance('lp_Nmech',
val=6000.0,
units='rpm',
lower=500.,
eq_units='hp',
rhs_val=0.,
res_ref=1e2)
self.connect('balance.lp_Nmech', 'LP_Nmech')
self.connect('lp_shaft.pwr_net', 'balance.lhs:lp_Nmech')
balance.add_balance('hp_Nmech',
val=20000.0,
units='rpm',
lower=500.,
eq_units='hp',
rhs_val=0.,
res_ref=1e2)
self.connect('balance.hp_Nmech', 'HP_Nmech')
self.connect('hp_shaft.pwr_net', 'balance.lhs:hp_Nmech')
order_add = []
if cooling:
self.add_subsystem(
'hpt_cooling',
pyc.TurbineCooling(n_stages=2,
thermo_data=pyc.species_data.janaf,
T_metal=2460.))
self.add_subsystem('hpt_chargable', pyc.CombineCooling(n_ins=3))
self.pyc_connect_flow('bld3.bld_inlet',
'hpt_cooling.Fl_cool',
connect_stat=False)
self.pyc_connect_flow('burner.Fl_O', 'hpt_cooling.Fl_turb_I')
self.pyc_connect_flow('hpt.Fl_O', 'hpt_cooling.Fl_turb_O')
self.connect('hpt_cooling.row_1.W_cool', 'hpt_chargable.W_1')
self.connect('hpt_cooling.row_2.W_cool', 'hpt_chargable.W_2')
self.connect('hpt_cooling.row_3.W_cool', 'hpt_chargable.W_3')
self.connect('hpt.power', 'hpt_cooling.turb_pwr')
balance.add_balance('hpt_nochrg_cool_frac',
val=0.063660111,
lower=0.02,
upper=.15,
eq_units='lbm/s')
self.connect('balance.hpt_nochrg_cool_frac',
'bld3.bld_inlet:frac_W')
self.connect('bld3.bld_inlet:stat:W',
'balance.lhs:hpt_nochrg_cool_frac')
self.connect('hpt_cooling.row_0.W_cool',
'balance.rhs:hpt_nochrg_cool_frac')
balance.add_balance('hpt_chrg_cool_frac',
val=0.07037185,
lower=0.02,
upper=.15,
eq_units='lbm/s')
self.connect('balance.hpt_chrg_cool_frac', 'bld3.bld_exit:frac_W')
self.connect('bld3.bld_exit:stat:W',
'balance.lhs:hpt_chrg_cool_frac')
self.connect('hpt_chargable.W_cool',
'balance.rhs:hpt_chrg_cool_frac')
order_add = ['hpt_cooling', 'hpt_chargable']
self.set_order(main_order + order_add + ['balance'])
self.pyc_connect_flow('fc.Fl_O', 'inlet.Fl_I')
self.pyc_connect_flow('inlet.Fl_O', 'fan.Fl_I')
self.pyc_connect_flow('fan.Fl_O', 'splitter.Fl_I')
self.pyc_connect_flow('splitter.Fl_O1', 'duct2.Fl_I')
self.pyc_connect_flow('duct2.Fl_O', 'lpc.Fl_I')
self.pyc_connect_flow('lpc.Fl_O', 'bld25.Fl_I')
self.pyc_connect_flow('bld25.Fl_O', 'duct25.Fl_I')
self.pyc_connect_flow('duct25.Fl_O', 'hpc.Fl_I')
self.pyc_connect_flow('hpc.Fl_O', 'bld3.Fl_I')
self.pyc_connect_flow('bld3.Fl_O', 'burner.Fl_I')
self.pyc_connect_flow('burner.Fl_O', 'hpt.Fl_I')
self.pyc_connect_flow('hpt.Fl_O', 'duct45.Fl_I')
self.pyc_connect_flow('duct45.Fl_O', 'lpt.Fl_I')
self.pyc_connect_flow('lpt.Fl_O', 'duct5.Fl_I')
self.pyc_connect_flow('duct5.Fl_O', 'core_nozz.Fl_I')
self.pyc_connect_flow('splitter.Fl_O2', 'byp_bld.Fl_I')
self.pyc_connect_flow('byp_bld.Fl_O', 'duct17.Fl_I')
self.pyc_connect_flow('duct17.Fl_O', 'byp_nozz.Fl_I')
self.pyc_connect_flow('hpc.bld_inlet',
'lpt.bld_inlet',
connect_stat=False)
self.pyc_connect_flow('hpc.bld_exit',
'lpt.bld_exit',
connect_stat=False)
self.pyc_connect_flow('bld3.bld_inlet',
'hpt.bld_inlet',
connect_stat=False)
self.pyc_connect_flow('bld3.bld_exit',
'hpt.bld_exit',
connect_stat=False)
newton = self.nonlinear_solver = om.NewtonSolver()
newton.options['atol'] = 1e-4
newton.options['rtol'] = 1e-4
newton.options['iprint'] = 2
newton.options['maxiter'] = 10
newton.options['solve_subsystems'] = True
newton.options['max_sub_solves'] = 10
newton.options['reraise_child_analysiserror'] = False
# newton.linesearch = om.BoundsEnforceLS()
newton.linesearch = om.ArmijoGoldsteinLS()
# newton.linesearch.options['maxiter'] = 2
newton.linesearch.options['bound_enforcement'] = 'scalar'
newton.linesearch.options['iprint'] = -1
# if design:
# newton.linesearch.options['print_bound_enforce'] = True
# newton.options['debug_print'] = True
self.linear_solver = om.DirectSolver(assemble_jac=True)
def setup(self):
thermo_spec = pyc.species_data.janaf
design = self.options['design']
# Add engine elements
self.add_subsystem(
'fc',
pyc.FlightConditions(thermo_data=thermo_spec,
elements=pyc.AIR_MIX))
self.add_subsystem(
'inlet',
pyc.Inlet(design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_MIX))
self.add_subsystem('comp',
pyc.Compressor(
map_data=pyc.AXI5,
design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_MIX,
),
promotes_inputs=['Nmech'])
self.add_subsystem(
'burner',
pyc.Combustor(design=design,
thermo_data=thermo_spec,
inflow_elements=pyc.AIR_MIX,
air_fuel_elements=pyc.AIR_FUEL_MIX,
fuel_type='JP-7'))
self.add_subsystem('turb',
pyc.Turbine(
map_data=pyc.LPT2269,
design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_FUEL_MIX,
),
promotes_inputs=['Nmech'])
self.add_subsystem(
'nozz',
pyc.Nozzle(nozzType='CD',
lossCoef='Cv',
thermo_data=thermo_spec,
elements=pyc.AIR_FUEL_MIX))
self.add_subsystem('shaft',
pyc.Shaft(num_ports=2),
promotes_inputs=['Nmech'])
self.add_subsystem('perf', pyc.Performance(num_nozzles=1,
num_burners=1))
# Connect flow stations
pyc.connect_flow(self, 'fc.Fl_O', 'inlet.Fl_I', connect_w=False)
pyc.connect_flow(self, 'inlet.Fl_O', 'comp.Fl_I')
pyc.connect_flow(self, 'comp.Fl_O', 'burner.Fl_I')
pyc.connect_flow(self, 'burner.Fl_O', 'turb.Fl_I')
pyc.connect_flow(self, 'turb.Fl_O', 'nozz.Fl_I')
# Connect turbomachinery elements to shaft
self.connect('comp.trq', 'shaft.trq_0')
self.connect('turb.trq', 'shaft.trq_1')
# Connnect nozzle exhaust to freestream static conditions
self.connect('fc.Fl_O:stat:P', 'nozz.Ps_exhaust')
# Connect outputs to 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')
# Add balances for design and off-design
balance = self.add_subsystem('balance', om.BalanceComp())
if design:
balance.add_balance('W', units='lbm/s', eq_units='lbf')
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')
else:
balance.add_balance('FAR', eq_units='lbf', lower=1e-4, val=.3)
self.connect('balance.FAR', 'burner.Fl_I:FAR')
self.connect('perf.Fn', 'balance.lhs:FAR')
balance.add_balance('Nmech',
val=1.5,
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=168.0,
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', 'nozz',
'shaft', 'perf'
])
newton = self.nonlinear_solver = om.NewtonSolver()
newton.options['atol'] = 1e-6
newton.options['rtol'] = 1e-6
newton.options['iprint'] = 2
newton.options['maxiter'] = 15
newton.options['solve_subsystems'] = True
newton.options['max_sub_solves'] = 100
newton.linesearch = om.BoundsEnforceLS()
# newton.linesearch = ArmijoGoldsteinLS()
# newton.linesearch.options['c'] = .0001
newton.linesearch.options['bound_enforcement'] = 'scalar'
newton.linesearch.options['iprint'] = -1
self.linear_solver = om.DirectSolver(assemble_jac=True)
def setup(self):
design = self.options['design']
maxiter = self.options['maxiter']
self.options['thermo_method'] = 'CEA'
self.options['thermo_data'] = pyc.species_data.janaf
self.add_subsystem('fc', pyc.FlightConditions())
self.add_subsystem('inlet', pyc.Inlet())
self.add_subsystem('duct1', pyc.Duct())
self.add_subsystem('lpc', pyc.Compressor(map_data=pyc.LPCMap),
promotes_inputs=[('Nmech','IP_Nmech')])
self.add_subsystem('icduct', pyc.Duct())
self.add_subsystem('hpc_axi', pyc.Compressor(map_data=pyc.HPCMap),
promotes_inputs=[('Nmech','HP_Nmech')])
self.add_subsystem('bld25', pyc.BleedOut(bleed_names=['cool1','cool2']))
self.add_subsystem('hpc_centri', pyc.Compressor(map_data=pyc.HPCMap),
promotes_inputs=[('Nmech','HP_Nmech')])
self.add_subsystem('bld3', pyc.BleedOut(bleed_names=['cool3','cool4']))
self.add_subsystem('duct6', pyc.Duct())
self.add_subsystem('burner', pyc.Combustor(fuel_type='Jet-A(g)'))
self.add_subsystem('hpt', pyc.Turbine(map_data=pyc.HPTMap, bleed_names=['cool3','cool4']),
promotes_inputs=[('Nmech','HP_Nmech')])
self.add_subsystem('duct43', pyc.Duct())
self.add_subsystem('lpt', pyc.Turbine(map_data=pyc.LPTMap, bleed_names=['cool1','cool2']),
promotes_inputs=[('Nmech','IP_Nmech')])
self.add_subsystem('itduct', pyc.Duct())
self.add_subsystem('pt', pyc.Turbine(map_data=pyc.LPTMap),
promotes_inputs=[('Nmech','LP_Nmech')])
self.add_subsystem('duct12', pyc.Duct())
self.add_subsystem('nozzle', pyc.Nozzle(nozzType='CV', lossCoef='Cv'))
self.add_subsystem('lp_shaft', pyc.Shaft(num_ports=1),promotes_inputs=[('Nmech','LP_Nmech')])
self.add_subsystem('ip_shaft', pyc.Shaft(num_ports=2),promotes_inputs=[('Nmech','IP_Nmech')])
self.add_subsystem('hp_shaft', pyc.Shaft(num_ports=3),promotes_inputs=[('Nmech','HP_Nmech')])
self.add_subsystem('perf', pyc.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', om.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')
else:
balance.add_balance('FAR', eq_units='hp', lower=1e-4, val=.017)
self.connect('balance.FAR', 'burner.Fl_I:FAR')
self.connect('lp_shaft.pwr_net', 'balance.lhs:FAR')
balance.add_balance('W', units='lbm/s', eq_units='inch**2')
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')
self.pyc_connect_flow('fc.Fl_O', 'inlet.Fl_I', connect_w=False)
self.pyc_connect_flow('inlet.Fl_O', 'duct1.Fl_I')
self.pyc_connect_flow('duct1.Fl_O', 'lpc.Fl_I')
self.pyc_connect_flow('lpc.Fl_O', 'icduct.Fl_I')
self.pyc_connect_flow('icduct.Fl_O', 'hpc_axi.Fl_I')
self.pyc_connect_flow('hpc_axi.Fl_O', 'bld25.Fl_I')
self.pyc_connect_flow('bld25.Fl_O', 'hpc_centri.Fl_I')
self.pyc_connect_flow('hpc_centri.Fl_O', 'bld3.Fl_I')
self.pyc_connect_flow('bld3.Fl_O', 'duct6.Fl_I')
self.pyc_connect_flow('duct6.Fl_O', 'burner.Fl_I')
self.pyc_connect_flow('burner.Fl_O', 'hpt.Fl_I')
self.pyc_connect_flow('hpt.Fl_O', 'duct43.Fl_I')
self.pyc_connect_flow('duct43.Fl_O', 'lpt.Fl_I')
self.pyc_connect_flow('lpt.Fl_O', 'itduct.Fl_I')
self.pyc_connect_flow('itduct.Fl_O', 'pt.Fl_I')
self.pyc_connect_flow('pt.Fl_O', 'duct12.Fl_I')
self.pyc_connect_flow('duct12.Fl_O', 'nozzle.Fl_I')
self.pyc_connect_flow('bld25.cool1', 'lpt.cool1', connect_stat=False)
self.pyc_connect_flow('bld25.cool2', 'lpt.cool2', connect_stat=False)
self.pyc_connect_flow('bld3.cool3', 'hpt.cool3', connect_stat=False)
self.pyc_connect_flow('bld3.cool4', 'hpt.cool4', connect_stat=False)
newton = self.nonlinear_solver = om.NewtonSolver()
newton.options['atol'] = 1e-6
newton.options['rtol'] = 1e-6
newton.options['iprint'] = 2
newton.options['maxiter'] = maxiter
newton.options['solve_subsystems'] = True
newton.options['max_sub_solves'] = 100
newton.options['reraise_child_analysiserror'] = False
newton.linesearch = om.BoundsEnforceLS()
newton.linesearch.options['bound_enforcement'] = 'scalar'
newton.linesearch.options['iprint'] = -1
self.linear_solver = om.DirectSolver()
super().setup()
def setup(self):
thermo_spec = pyc.species_data.janaf
design = self.options['design']
self.add_subsystem(
'fc',
pyc.FlightConditions(thermo_data=thermo_spec,
elements=pyc.AIR_MIX))
self.add_subsystem(
'inlet',
pyc.Inlet(design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_MIX))
self.add_subsystem(
'fan',
pyc.Compressor(thermo_data=thermo_spec,
elements=pyc.AIR_MIX,
design=design,
map_data=pyc.FanMap,
map_extrap=True))
self.add_subsystem(
'nozz', pyc.Nozzle(thermo_data=thermo_spec, elements=pyc.AIR_MIX))
self.add_subsystem('perf', pyc.Performance(num_nozzles=1,
num_burners=0))
balance = om.BalanceComp()
if design:
self.add_subsystem('shaft',
om.IndepVarComp('Nmech', 1., units='rpm'))
self.connect('shaft.Nmech', 'fan.Nmech')
balance.add_balance('W',
units='lbm/s',
eq_units='hp',
val=50.,
lower=1.,
upper=500.)
self.add_subsystem('balance',
balance,
promotes_inputs=[('rhs:W', 'pwr_target')])
self.connect('fan.power', 'balance.lhs:W')
else:
# vary mass flow till the nozzle area matches the design values
balance.add_balance('W',
units='lbm/s',
eq_units='inch**2',
val=50,
lower=1.,
upper=500.)
self.connect('nozz.Throat:stat:area', 'balance.lhs:W')
balance.add_balance('Nmech',
val=1.,
units='rpm',
lower=0.1,
upper=2.0,
eq_units='hp')
self.connect('balance.Nmech', 'fan.Nmech')
self.connect('fan.power', 'balance.lhs:Nmech')
# self.add_subsystem('shaft', om.IndepVarComp('Nmech', 1., units='rpm'))
# self.connect('shaft.Nmech', 'fan.Nmech')
self.add_subsystem('balance',
balance,
promotes_inputs=[('rhs:Nmech', 'pwr_target')])
pyc.connect_flow(self, 'fc.Fl_O', 'inlet.Fl_I')
pyc.connect_flow(self, 'inlet.Fl_O', 'fan.Fl_I')
pyc.connect_flow(self, 'fan.Fl_O', 'nozz.Fl_I')
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('balance.W', 'fc.W')
newton = self.nonlinear_solver = om.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 = om.ArmijoGoldsteinLS()
# newton.linesearch.options['maxiter'] = 3
newton.linesearch = om.BoundsEnforceLS()
newton.linesearch.options['bound_enforcement'] = 'scalar'
# newton.linesearch.options['print_bound_enforce'] = True
# newton.linesearch.options['iprint'] = -1
#
self.linear_solver = om.DirectSolver(assemble_jac=True)
def setup(self):
#Setup the problem by including all the relavant components here - comp, burner, turbine etc
#Create any relavent short hands here:
design = self.options['design']
USE_TABULAR = False
if USE_TABULAR:
self.options['thermo_method'] = 'TABULAR'
self.options['thermo_data'] = pyc.AIR_JETA_TAB_SPEC
FUEL_TYPE = 'FAR'
else:
self.options['thermo_method'] = 'CEA'
self.options['thermo_data'] = pyc.species_data.janaf
FUEL_TYPE = 'Jet-A(g)'
#Add subsystems to build the engine deck:
self.add_subsystem('fc', pyc.FlightConditions())
self.add_subsystem('inlet', pyc.Inlet())
# Note variable promotion for the fan --
# the LP spool speed and the fan speed are INPUTS that are promoted:
# Note here that promotion aliases are used. Here Nmech is being aliased to LP_Nmech
# check out: http://openmdao.org/twodocs/versions/latest/features/core_features/grouping_components/add_subsystem.html?highlight=alias
self.add_subsystem('fan',
pyc.Compressor(map_data=pyc.FanMap,
bleed_names=[],
map_extrap=True),
promotes_inputs=[('Nmech', 'LP_Nmech')])
self.add_subsystem('splitter', pyc.Splitter())
self.add_subsystem('duct4', pyc.Duct())
self.add_subsystem('lpc',
pyc.Compressor(map_data=pyc.LPCMap,
map_extrap=True),
promotes_inputs=[('Nmech', 'LP_Nmech')])
self.add_subsystem('duct6', pyc.Duct())
self.add_subsystem('hpc',
pyc.Compressor(
map_data=pyc.HPCMap,
bleed_names=['cool1', 'cool2', 'cust'],
map_extrap=True),
promotes_inputs=[('Nmech', 'HP_Nmech')])
self.add_subsystem('bld3',
pyc.BleedOut(bleed_names=['cool3', 'cool4']))
self.add_subsystem('burner', pyc.Combustor(fuel_type=FUEL_TYPE))
self.add_subsystem('hpt',
pyc.Turbine(map_data=pyc.HPTMap,
bleed_names=['cool3', 'cool4'],
map_extrap=True),
promotes_inputs=[('Nmech', 'HP_Nmech')])
self.add_subsystem('duct11', pyc.Duct())
self.add_subsystem('lpt',
pyc.Turbine(map_data=pyc.LPTMap,
bleed_names=['cool1', 'cool2'],
map_extrap=True),
promotes_inputs=[('Nmech', 'LP_Nmech')])
self.add_subsystem('duct13', pyc.Duct())
self.add_subsystem('core_nozz', pyc.Nozzle(nozzType='CV',
lossCoef='Cv'))
self.add_subsystem('byp_bld', pyc.BleedOut(bleed_names=['bypBld']))
self.add_subsystem('duct15', pyc.Duct())
self.add_subsystem('byp_nozz', pyc.Nozzle(nozzType='CV',
lossCoef='Cv'))
#Create shaft instances. Note that LP shaft has 3 ports! => no gearbox
self.add_subsystem('lp_shaft',
pyc.Shaft(num_ports=3),
promotes_inputs=[('Nmech', 'LP_Nmech')])
self.add_subsystem('hp_shaft',
pyc.Shaft(num_ports=2),
promotes_inputs=[('Nmech', 'HP_Nmech')])
self.add_subsystem('perf', pyc.Performance(num_nozzles=2,
num_burners=1))
# Now use the explicit connect method to make connections -- connect(<from>, <to>)
#Connect the inputs to perf group
self.connect('inlet.Fl_O:tot:P', 'perf.Pt2')
self.connect('hpc.Fl_O:tot:P', 'perf.Pt3')
self.connect('burner.Wfuel', 'perf.Wfuel_0')
self.connect('inlet.F_ram', 'perf.ram_drag')
self.connect('core_nozz.Fg', 'perf.Fg_0')
self.connect('byp_nozz.Fg', 'perf.Fg_1')
#LP-shaft connections
self.connect('fan.trq', 'lp_shaft.trq_0')
self.connect('lpc.trq', 'lp_shaft.trq_1')
self.connect('lpt.trq', 'lp_shaft.trq_2')
#HP-shaft connections
self.connect('hpc.trq', 'hp_shaft.trq_0')
self.connect('hpt.trq', 'hp_shaft.trq_1')
#Ideally expanding flow by conneting flight condition static pressure to nozzle exhaust pressure
self.connect('fc.Fl_O:stat:P', 'core_nozz.Ps_exhaust')
self.connect('fc.Fl_O:stat:P', 'byp_nozz.Ps_exhaust')
#Create a balance component
# Balances can be a bit confusing, here's some explanation -
# State Variables:
# (W) Inlet mass flow rate to implictly balance thrust
# LHS: perf.Fn == RHS: Thrust requirement (set when TF is instantiated)
#
# (FAR) Fuel-air ratio to balance Tt4
# LHS: burner.Fl_O:tot:T == RHS: Tt4 target (set when TF is instantiated)
#
# (lpt_PR) LPT press ratio to balance shaft power on the low spool
# (hpt_PR) HPT press ratio to balance shaft power on the high spool
# Ref: look at the XDSM diagrams in the pyCycle paper and this:
# http://openmdao.org/twodocs/versions/latest/features/building_blocks/components/balance_comp.html
balance = self.add_subsystem('balance', om.BalanceComp())
if design:
balance.add_balance('W', units='lbm/s', eq_units='lbf')
#Here balance.W is implicit state variable that is the OUTPUT of balance object
self.connect(
'balance.W',
'fc.W') #Connect the output of balance to the relevant input
self.connect(
'perf.Fn', 'balance.lhs:W'
) #This statement makes perf.Fn the LHS of the balance eqn.
self.promotes('balance', inputs=[('rhs:W', 'Fn_DES')])
balance.add_balance('FAR', eq_units='degR', lower=1e-4, val=.017)
self.connect('balance.FAR', 'burner.Fl_I:FAR')
self.connect('burner.Fl_O:tot:T', 'balance.lhs:FAR')
self.promotes('balance', inputs=[('rhs:FAR', 'T4_MAX')])
# Note that for the following two balances the mult val is set to -1 so that the NET torque is zero
balance.add_balance('lpt_PR',
val=1.5,
lower=1.001,
upper=8,
eq_units='hp',
use_mult=True,
mult_val=-1)
self.connect('balance.lpt_PR', 'lpt.PR')
self.connect('lp_shaft.pwr_in_real', 'balance.lhs:lpt_PR')
self.connect('lp_shaft.pwr_out_real', 'balance.rhs:lpt_PR')
balance.add_balance('hpt_PR',
val=1.5,
lower=1.001,
upper=8,
eq_units='hp',
use_mult=True,
mult_val=-1)
self.connect('balance.hpt_PR', 'hpt.PR')
self.connect('hp_shaft.pwr_in_real', 'balance.lhs:hpt_PR')
self.connect('hp_shaft.pwr_out_real', 'balance.rhs:hpt_PR')
else:
#In OFF-DESIGN mode we need to redefine the balances:
# State Variables:
# (W) Inlet mass flow rate to balance core flow area
# LHS: core_nozz.Throat:stat:area == Area from DESIGN calculation
#
# (FAR) Fuel-air ratio to balance Thrust req.
# LHS: perf.Fn == RHS: Thrust requirement (set when TF is instantiated)
#
# (BPR) Bypass ratio to balance byp. noz. area
# LHS: byp_nozz.Throat:stat:area == Area from DESIGN calculation
#
# (lp_Nmech) LP spool speed to balance shaft power on the low spool
# (hp_Nmech) HP spool speed to balance shaft power on the high spool
if self.options['throttle_mode'] == 'T4':
balance.add_balance('FAR',
val=0.017,
lower=1e-4,
eq_units='degR')
self.connect('balance.FAR', 'burner.Fl_I:FAR')
self.connect('burner.Fl_O:tot:T', 'balance.lhs:FAR')
self.promotes('balance', inputs=[('rhs:FAR', 'T4_MAX')])
elif self.options['throttle_mode'] == 'percent_thrust':
balance.add_balance('FAR',
val=0.017,
lower=1e-4,
eq_units='lbf',
use_mult=True)
self.connect('balance.FAR', 'burner.Fl_I:FAR')
self.connect('perf.Fn', 'balance.rhs:FAR')
self.promotes('balance',
inputs=[('mult:FAR', 'PC'),
('lhs:FAR', 'Fn_max')])
balance.add_balance('W',
units='lbm/s',
lower=10.,
upper=1000.,
eq_units='inch**2')
self.connect('balance.W', 'fc.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')
# Again for the following two balances the mult val is set to -1 so that the NET torque is zero
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')
# Specify the order in which the subsystems are executed:
# 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'])
# Set up all the flow connections:
self.pyc_connect_flow('fc.Fl_O', 'inlet.Fl_I')
self.pyc_connect_flow('inlet.Fl_O', 'fan.Fl_I')
self.pyc_connect_flow('fan.Fl_O', 'splitter.Fl_I')
self.pyc_connect_flow('splitter.Fl_O1', 'duct4.Fl_I')
self.pyc_connect_flow('duct4.Fl_O', 'lpc.Fl_I')
self.pyc_connect_flow('lpc.Fl_O', 'duct6.Fl_I')
self.pyc_connect_flow('duct6.Fl_O', 'hpc.Fl_I')
self.pyc_connect_flow('hpc.Fl_O', 'bld3.Fl_I')
self.pyc_connect_flow('bld3.Fl_O', 'burner.Fl_I')
self.pyc_connect_flow('burner.Fl_O', 'hpt.Fl_I')
self.pyc_connect_flow('hpt.Fl_O', 'duct11.Fl_I')
self.pyc_connect_flow('duct11.Fl_O', 'lpt.Fl_I')
self.pyc_connect_flow('lpt.Fl_O', 'duct13.Fl_I')
self.pyc_connect_flow('duct13.Fl_O', 'core_nozz.Fl_I')
self.pyc_connect_flow('splitter.Fl_O2', 'byp_bld.Fl_I')
self.pyc_connect_flow('byp_bld.Fl_O', 'duct15.Fl_I')
self.pyc_connect_flow('duct15.Fl_O', 'byp_nozz.Fl_I')
#Bleed flows:
self.pyc_connect_flow('hpc.cool1', 'lpt.cool1', connect_stat=False)
self.pyc_connect_flow('hpc.cool2', 'lpt.cool2', connect_stat=False)
self.pyc_connect_flow('bld3.cool3', 'hpt.cool3', connect_stat=False)
self.pyc_connect_flow('bld3.cool4', 'hpt.cool4', connect_stat=False)
#Specify solver settings:
newton = self.nonlinear_solver = om.NewtonSolver()
newton.options['atol'] = 1e-8
# set this very small, so it never activates and we rely on atol
newton.options['rtol'] = 1e-99
newton.options['iprint'] = 2
newton.options['maxiter'] = 50
newton.options['solve_subsystems'] = True
newton.options['max_sub_solves'] = 1000
newton.options['reraise_child_analysiserror'] = False
# ls = newton.linesearch = BoundsEnforceLS()
ls = newton.linesearch = om.ArmijoGoldsteinLS()
ls.options['maxiter'] = 3
ls.options['rho'] = 0.75
# ls.options['print_bound_enforce'] = True
self.linear_solver = om.DirectSolver()
super().setup()
def setup(self):
USE_TABULAR = True
if USE_TABULAR:
self.options['thermo_method'] = 'TABULAR'
self.options['thermo_data'] = pyc.AIR_JETA_TAB_SPEC
FUEL_TYPE = "FAR"
else:
self.options['thermo_method'] = 'CEA'
self.options['thermo_data'] = pyc.species_data.janaf
FUEL_TYPE = "Jet-A(g)"
design = self.options['design']
# Add engine elements
self.add_subsystem('fc', pyc.FlightConditions())
self.add_subsystem('inlet', pyc.Inlet())
self.add_subsystem('comp', pyc.Compressor(map_data=pyc.AXI5, map_extrap=True),
promotes_inputs=['Nmech'])
self.add_subsystem('burner', pyc.Combustor(fuel_type=FUEL_TYPE))
self.add_subsystem('turb', pyc.Turbine(map_data=pyc.LPT2269),
promotes_inputs=['Nmech'])
self.add_subsystem('nozz', pyc.Nozzle(nozzType='CD', lossCoef='Cv'))
self.add_subsystem('shaft', pyc.Shaft(num_ports=2),promotes_inputs=['Nmech'])
self.add_subsystem('perf', pyc.Performance(num_nozzles=1, num_burners=1))
# Connect flow stations
self.pyc_connect_flow('fc.Fl_O', 'inlet.Fl_I', connect_w=False)
self.pyc_connect_flow('inlet.Fl_O', 'comp.Fl_I')
self.pyc_connect_flow('comp.Fl_O', 'burner.Fl_I')
self.pyc_connect_flow('burner.Fl_O', 'turb.Fl_I')
self.pyc_connect_flow('turb.Fl_O', 'nozz.Fl_I')
# Make other non-flow connections
# Connect turbomachinery elements to shaft
self.connect('comp.trq', 'shaft.trq_0')
self.connect('turb.trq', 'shaft.trq_1')
# Connnect nozzle exhaust to freestream static conditions
self.connect('fc.Fl_O:stat:P', 'nozz.Ps_exhaust')
# Connect outputs to perfomance element
self.connect('inlet.Fl_O:tot:P', 'perf.Pt2')
self.connect('comp.Fl_O:tot:P', 'perf.Pt3')
self.connect('burner.Wfuel', 'perf.Wfuel_0')
self.connect('inlet.F_ram', 'perf.ram_drag')
self.connect('nozz.Fg', 'perf.Fg_0')
# Add balances for design and off-design
balance = self.add_subsystem('balance', om.BalanceComp())
if design:
balance.add_balance('W', units='lbm/s', eq_units='lbf', rhs_name='Fn_target')
self.connect('balance.W', 'inlet.Fl_I:stat:W')
self.connect('perf.Fn', 'balance.lhs:W')
balance.add_balance('FAR', eq_units='degR', lower=1e-4, val=.017, rhs_name='T4_target')
self.connect('balance.FAR', 'burner.Fl_I:FAR')
self.connect('burner.Fl_O:tot:T', 'balance.lhs:FAR')
balance.add_balance('turb_PR', val=1.5, lower=1.001, upper=8, eq_units='hp', rhs_val=0.)
self.connect('balance.turb_PR', 'turb.PR')
self.connect('shaft.pwr_net', 'balance.lhs:turb_PR')
else:
balance.add_balance('FAR', eq_units='lbf', lower=1e-4, val=.3, rhs_name='Fn_target')
self.connect('balance.FAR', 'burner.Fl_I:FAR')
self.connect('perf.Fn', 'balance.lhs:FAR')
balance.add_balance('Nmech', val=1.5, 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=168.0, 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')
newton = self.nonlinear_solver = om.NewtonSolver()
newton.options['atol'] = 1e-6
newton.options['rtol'] = 1e-6
newton.options['iprint'] = 2
newton.options['maxiter'] = 15
newton.options['solve_subsystems'] = True
newton.options['max_sub_solves'] = 100
newton.options['reraise_child_analysiserror'] = False
self.linear_solver = om.DirectSolver()
super().setup()
def setup(self):
wet_thermo_spec = pyc.species_data.wet_air #special species library is called that allows for using initial compositions that include both H and C
janaf_thermo_spec = pyc.species_data.janaf #standard species library is called for use in and after burner
design = self.options['design']
# Add engine elements
self.pyc_add_element('fc', pyc.FlightConditions(thermo_data=wet_thermo_spec, use_WAR=True,
elements=pyc.WET_AIR_ELEMENTS))#WET_AIR_ELEMENTS contains standard dry air compounds as well as H2O
self.pyc_add_element('inlet', pyc.Inlet(design=design, thermo_data=wet_thermo_spec,
elements=pyc.WET_AIR_ELEMENTS))
self.pyc_add_element('comp', pyc.Compressor(map_data=pyc.AXI5, design=design,
thermo_data=wet_thermo_spec, elements=pyc.WET_AIR_ELEMENTS,),
promotes_inputs=['Nmech'])
###Note###
#The Combustor element automatically assumes that the thermo data to use for both the inflowing air
#and the outflowing mixed air and fuel is the data specified by the thermo_data option
#unless the inflow_thermo_data option is set. If the inflow_thermo_data option is set,
#the Combustor element will use the thermo data specified by inflow_thermo_data for the inflowing air
#to the burner, and it will use the thermo data specified by thermo_data for the outflowing mixed
#air and fuel. This is necessary to do if the airflow upstream of the burner contains both C and H
#within its compounds, because without the addition of the hydrocarbons from fuel, the solver has
#a difficult time converging the trace amount of hydrocarbons "present" in the original flow.
self.pyc_add_element('burner', pyc.Combustor(design=design,inflow_thermo_data=wet_thermo_spec,
thermo_data=janaf_thermo_spec, inflow_elements=pyc.WET_AIR_ELEMENTS,
air_fuel_elements=pyc.AIR_FUEL_ELEMENTS,
fuel_type='JP-7'))
self.pyc_add_element('turb', pyc.Turbine(map_data=pyc.LPT2269, design=design,
thermo_data=janaf_thermo_spec, elements=pyc.AIR_FUEL_ELEMENTS,),
promotes_inputs=['Nmech'])
self.pyc_add_element('nozz', pyc.Nozzle(nozzType='CD', lossCoef='Cv',
thermo_data=janaf_thermo_spec, elements=pyc.AIR_FUEL_ELEMENTS))
self.pyc_add_element('shaft', pyc.Shaft(num_ports=2),promotes_inputs=['Nmech'])
self.pyc_add_element('perf', pyc.Performance(num_nozzles=1, num_burners=1))
# Connect flow stations
self.pyc_connect_flow('fc.Fl_O', 'inlet.Fl_I', connect_w=False)
self.pyc_connect_flow('inlet.Fl_O', 'comp.Fl_I')
self.pyc_connect_flow('comp.Fl_O', 'burner.Fl_I')
self.pyc_connect_flow('burner.Fl_O', 'turb.Fl_I')
self.pyc_connect_flow('turb.Fl_O', 'nozz.Fl_I')
# Connect turbomachinery elements to shaft
self.connect('comp.trq', 'shaft.trq_0')
self.connect('turb.trq', 'shaft.trq_1')
# Connnect nozzle exhaust to freestream static conditions
self.connect('fc.Fl_O:stat:P', 'nozz.Ps_exhaust')
# Connect outputs to 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')
# Add balances for design and off-design
balance = self.add_subsystem('balance', om.BalanceComp())
if design:
balance.add_balance('W', units='lbm/s', eq_units='lbf')
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')
else:
balance.add_balance('FAR', eq_units='lbf', lower=1e-4, val=.3)
self.connect('balance.FAR', 'burner.Fl_I:FAR')
self.connect('perf.Fn', 'balance.lhs:FAR')
balance.add_balance('Nmech', val=1.5, 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=168.0, 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', 'nozz', 'shaft', 'perf'])
newton = self.nonlinear_solver = om.NewtonSolver()
newton.options['atol'] = 1e-6
newton.options['rtol'] = 1e-6
newton.options['iprint'] = 2
newton.options['maxiter'] = 15
newton.options['solve_subsystems'] = True
newton.options['max_sub_solves'] = 100
newton.options['reraise_child_analysiserror'] = False
newton.linesearch = om.BoundsEnforceLS()
# newton.linesearch = ArmijoGoldsteinLS()
# newton.linesearch.options['c'] = .0001
newton.linesearch.options['bound_enforcement'] = 'scalar'
newton.linesearch.options['iprint'] = -1
self.linear_solver = om.DirectSolver(assemble_jac=True)
def setup(self):
thermo_spec = pyc.species_data.janaf
design = self.options['design']
self.pyc_add_element('fc', pyc.FlightConditions(thermo_data=thermo_spec, elements=pyc.AIR_ELEMENTS))
self.pyc_add_element('inlet', pyc.Inlet(design=design, thermo_data=thermo_spec, elements=pyc.AIR_ELEMENTS))
self.pyc_add_element('duct1', pyc.Duct(design=design, thermo_data=thermo_spec, elements=pyc.AIR_ELEMENTS))
self.pyc_add_element('comp', pyc.Compressor(map_data=pyc.AXI5, design=design, thermo_data=thermo_spec, elements=pyc.AIR_ELEMENTS,
bleed_names=['cool1','cool2'], map_extrap=True),promotes_inputs=['Nmech'])
self.pyc_add_element('burner', pyc.Combustor(design=design,thermo_data=thermo_spec,
inflow_elements=pyc.AIR_ELEMENTS,
air_fuel_elements=pyc.AIR_FUEL_ELEMENTS,
fuel_type='JP-7'))
self.pyc_add_element('turb', pyc.Turbine(map_data=pyc.LPT2269, design=design, thermo_data=thermo_spec, elements=pyc.AIR_FUEL_ELEMENTS,
bleed_names=['cool1','cool2'], map_extrap=True),promotes_inputs=['Nmech'])
self.pyc_add_element('ab', pyc.Combustor(design=design,thermo_data=thermo_spec,
inflow_elements=pyc.AIR_FUEL_ELEMENTS,
air_fuel_elements=pyc.AIR_FUEL_ELEMENTS,
fuel_type='JP-7'))
self.pyc_add_element('nozz', pyc.Nozzle(nozzType='CD', lossCoef='Cv', thermo_data=thermo_spec, elements=pyc.AIR_FUEL_ELEMENTS, internal_solver=True))
self.pyc_add_element('shaft', pyc.Shaft(num_ports=2),promotes_inputs=['Nmech'])
self.pyc_add_element('perf', pyc.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', om.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'])
self.pyc_connect_flow('fc.Fl_O', 'inlet.Fl_I', connect_w=False)
self.pyc_connect_flow('inlet.Fl_O', 'duct1.Fl_I', connect_stat=False)
self.pyc_connect_flow('duct1.Fl_O', 'comp.Fl_I', connect_stat=False)
self.pyc_connect_flow('comp.Fl_O', 'burner.Fl_I', connect_stat=False)
self.pyc_connect_flow('burner.Fl_O', 'turb.Fl_I', connect_stat=False)
self.pyc_connect_flow('turb.Fl_O', 'ab.Fl_I', connect_stat=False)
self.pyc_connect_flow('ab.Fl_O', 'nozz.Fl_I', connect_stat=False)
self.pyc_connect_flow('comp.cool1', 'turb.cool1', connect_stat=False)
self.pyc_connect_flow('comp.cool2', 'turb.cool2', connect_stat=False)
newton = self.nonlinear_solver = om.NewtonSolver()
newton.options['atol'] = 1e-6
newton.options['rtol'] = 1e-6
newton.options['iprint'] = 2
newton.options['maxiter'] = 50
newton.options['solve_subsystems'] = True
newton.options['max_sub_solves'] = 100
newton.options['reraise_child_analysiserror'] = False
# newton.linesearch = om.BoundsEnforceLS()
newton.linesearch = om.ArmijoGoldsteinLS()
# newton.linesearch.options['c'] = .0001
newton.linesearch.options['bound_enforcement'] = 'scalar'
newton.linesearch.options['iprint'] = -1
self.linear_solver = om.DirectSolver(assemble_jac=True)
def setup(self):
thermo_spec = pyc.species_data.janaf
design = self.options['design']
self.pyc_add_element(
'fc',
pyc.FlightConditions(thermo_data=thermo_spec,
elements=pyc.AIR_ELEMENTS))
# Inlet Components
self.pyc_add_element(
'inlet',
pyc.Inlet(design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_ELEMENTS))
self.pyc_add_element(
'inlet_duct',
pyc.Duct(design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_ELEMENTS))
# Fan Components - Split here for CFD integration Add a CFDStart Compomponent
self.pyc_add_element('fan',
pyc.Compressor(map_data=pyc.AXI5,
design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_ELEMENTS,
map_extrap=True),
promotes_inputs=[('Nmech', 'LP_Nmech')])
self.pyc_add_element(
'splitter',
pyc.Splitter(design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_ELEMENTS))
# Core Stream components
self.pyc_add_element(
'splitter_core_duct',
pyc.Duct(design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_ELEMENTS))
self.pyc_add_element('lpc',
pyc.Compressor(map_data=pyc.LPCMap,
design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_ELEMENTS,
map_extrap=True),
promotes_inputs=[('Nmech', 'LP_Nmech')])
self.pyc_add_element(
'lpc_duct',
pyc.Duct(design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_ELEMENTS))
self.pyc_add_element('hpc',
pyc.Compressor(map_data=pyc.HPCMap,
design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_ELEMENTS,
bleed_names=['cool1'],
map_extrap=True),
promotes_inputs=[('Nmech', 'HP_Nmech')])
self.pyc_add_element(
'bld3', pyc.BleedOut(design=design, bleed_names=['cool3']))
self.pyc_add_element(
'burner',
pyc.Combustor(design=design,
thermo_data=thermo_spec,
inflow_elements=pyc.AIR_ELEMENTS,
air_fuel_elements=pyc.AIR_FUEL_ELEMENTS,
fuel_type='Jet-A(g)'))
self.pyc_add_element('hpt',
pyc.Turbine(map_data=pyc.HPTMap,
design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_FUEL_ELEMENTS,
bleed_names=['cool3'],
map_extrap=True),
promotes_inputs=[('Nmech', 'HP_Nmech')])
self.pyc_add_element(
'hpt_duct',
pyc.Duct(design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_FUEL_ELEMENTS))
self.pyc_add_element('lpt',
pyc.Turbine(map_data=pyc.LPTMap,
design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_FUEL_ELEMENTS,
bleed_names=['cool1'],
map_extrap=True),
promotes_inputs=[('Nmech', 'LP_Nmech')])
self.pyc_add_element(
'lpt_duct',
pyc.Duct(design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_FUEL_ELEMENTS))
# Bypass Components
self.pyc_add_element(
'bypass_duct',
pyc.Duct(design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_ELEMENTS))
# Mixer component
self.pyc_add_element(
'mixer',
pyc.Mixer(design=design,
designed_stream=1,
Fl_I1_elements=pyc.AIR_FUEL_ELEMENTS,
Fl_I2_elements=pyc.AIR_ELEMENTS))
self.pyc_add_element(
'mixer_duct',
pyc.Duct(design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_FUEL_ELEMENTS))
# Afterburner Components
self.pyc_add_element(
'afterburner',
pyc.Combustor(design=design,
thermo_data=thermo_spec,
inflow_elements=pyc.AIR_FUEL_ELEMENTS,
air_fuel_elements=pyc.AIR_FUEL_ELEMENTS,
fuel_type='Jet-A(g)'))
# End CFD HERE
# Nozzle
self.pyc_add_element(
'mixed_nozz',
pyc.Nozzle(nozzType='CD',
lossCoef='Cfg',
thermo_data=thermo_spec,
elements=pyc.AIR_FUEL_ELEMENTS))
# Mechanical components
self.pyc_add_element('lp_shaft',
pyc.Shaft(num_ports=3),
promotes_inputs=[('Nmech', 'LP_Nmech')])
self.pyc_add_element('hp_shaft',
pyc.Shaft(num_ports=2),
promotes_inputs=[('Nmech', 'HP_Nmech')])
# Aggregating component
self.pyc_add_element('perf',
pyc.Performance(num_nozzles=1, num_burners=2))
# Connnect flow path
self.pyc_connect_flow('fc.Fl_O', 'inlet.Fl_I')
self.pyc_connect_flow('inlet.Fl_O', 'inlet_duct.Fl_I')
self.pyc_connect_flow('inlet_duct.Fl_O', 'fan.Fl_I')
self.pyc_connect_flow('fan.Fl_O', 'splitter.Fl_I')
# Core connections
self.pyc_connect_flow('splitter.Fl_O1', 'splitter_core_duct.Fl_I')
self.pyc_connect_flow('splitter_core_duct.Fl_O', 'lpc.Fl_I')
self.pyc_connect_flow('lpc.Fl_O', 'lpc_duct.Fl_I')
self.pyc_connect_flow('lpc_duct.Fl_O', 'hpc.Fl_I')
self.pyc_connect_flow('hpc.Fl_O', 'bld3.Fl_I')
self.pyc_connect_flow('bld3.Fl_O', 'burner.Fl_I')
self.pyc_connect_flow('burner.Fl_O', 'hpt.Fl_I')
self.pyc_connect_flow('hpt.Fl_O', 'hpt_duct.Fl_I')
self.pyc_connect_flow('hpt_duct.Fl_O', 'lpt.Fl_I')
self.pyc_connect_flow('lpt.Fl_O', 'lpt_duct.Fl_I')
self.pyc_connect_flow('lpt_duct.Fl_O', 'mixer.Fl_I1')
# Bypass Connections
self.pyc_connect_flow('splitter.Fl_O2', 'bypass_duct.Fl_I')
self.pyc_connect_flow('bypass_duct.Fl_O', 'mixer.Fl_I2')
#Mixer Connections
self.pyc_connect_flow('mixer.Fl_O', 'mixer_duct.Fl_I')
# After Burner
self.pyc_connect_flow('mixer_duct.Fl_O', 'afterburner.Fl_I')
# Nozzle
self.pyc_connect_flow('afterburner.Fl_O', 'mixed_nozz.Fl_I')
# Connect cooling flows
self.pyc_connect_flow('hpc.cool1', 'lpt.cool1', connect_stat=False)
self.pyc_connect_flow('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', om.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 = om.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.options['reraise_child_analysiserror'] = False
newton.linesearch = om.BoundsEnforceLS()
newton.linesearch.options['bound_enforcement'] = 'scalar'
newton.linesearch.options['iprint'] = -1
self.linear_solver = om.DirectSolver(assemble_jac=True)
def setup(self):
thermo_spec = pyc.species_data.janaf
design = self.options['design']
self.add_subsystem(
'fc',
pyc.FlightConditions(thermo_data=thermo_spec,
elements=pyc.AIR_MIX))
self.add_subsystem(
'inlet',
pyc.Inlet(design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_MIX))
self.add_subsystem('fan',
pyc.Compressor(map_data=pyc.FanMap,
design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_MIX,
bleed_names=[],
map_extrap=True),
promotes_inputs=[('Nmech', 'LP_Nmech')])
self.add_subsystem(
'splitter',
pyc.Splitter(design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_MIX))
self.add_subsystem(
'duct4',
pyc.Duct(design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_MIX))
self.add_subsystem('lpc',
pyc.Compressor(map_data=pyc.LPCMap,
design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_MIX,
map_extrap=True),
promotes_inputs=[('Nmech', 'LP_Nmech')])
self.add_subsystem(
'duct6',
pyc.Duct(design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_MIX))
self.add_subsystem('hpc',
pyc.Compressor(
map_data=pyc.HPCMap,
design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_MIX,
bleed_names=['cool1', 'cool2', 'cust'],
map_extrap=True),
promotes_inputs=[('Nmech', 'HP_Nmech')])
self.add_subsystem(
'bld3', pyc.BleedOut(design=design, bleed_names=['cool3',
'cool4']))
self.add_subsystem(
'burner',
pyc.Combustor(design=design,
thermo_data=thermo_spec,
inflow_elements=pyc.AIR_MIX,
air_fuel_elements=pyc.AIR_FUEL_MIX,
fuel_type='Jet-A(g)'))
self.add_subsystem('hpt',
pyc.Turbine(map_data=pyc.HPTMap,
design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_FUEL_MIX,
bleed_names=['cool3', 'cool4'],
map_extrap=True),
promotes_inputs=[('Nmech', 'HP_Nmech')])
self.add_subsystem(
'duct11',
pyc.Duct(design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_FUEL_MIX))
self.add_subsystem('lpt',
pyc.Turbine(map_data=pyc.LPTMap,
design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_FUEL_MIX,
bleed_names=['cool1', 'cool2'],
map_extrap=True),
promotes_inputs=[('Nmech', 'LP_Nmech')])
self.add_subsystem(
'duct13',
pyc.Duct(design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_FUEL_MIX))
self.add_subsystem(
'core_nozz',
pyc.Nozzle(nozzType='CV',
lossCoef='Cv',
thermo_data=thermo_spec,
elements=pyc.AIR_FUEL_MIX))
self.add_subsystem('byp_bld',
pyc.BleedOut(design=design, bleed_names=['bypBld']))
self.add_subsystem(
'duct15',
pyc.Duct(design=design,
thermo_data=thermo_spec,
elements=pyc.AIR_MIX))
self.add_subsystem(
'byp_nozz',
pyc.Nozzle(nozzType='CV',
lossCoef='Cv',
thermo_data=thermo_spec,
elements=pyc.AIR_MIX))
self.add_subsystem('lp_shaft',
pyc.Shaft(num_ports=3),
promotes_inputs=[('Nmech', 'LP_Nmech')])
self.add_subsystem('hp_shaft',
pyc.Shaft(num_ports=2),
promotes_inputs=[('Nmech', 'HP_Nmech')])
self.add_subsystem('perf', pyc.Performance(num_nozzles=2,
num_burners=1))
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', om.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'
])
pyc.connect_flow(self, 'fc.Fl_O', 'inlet.Fl_I', connect_w=False)
pyc.connect_flow(self, 'inlet.Fl_O', 'fan.Fl_I')
pyc.connect_flow(self, 'fan.Fl_O', 'splitter.Fl_I')
pyc.connect_flow(self, 'splitter.Fl_O1', 'duct4.Fl_I')
pyc.connect_flow(self, 'duct4.Fl_O', 'lpc.Fl_I')
pyc.connect_flow(self, 'lpc.Fl_O', 'duct6.Fl_I')
pyc.connect_flow(self, 'duct6.Fl_O', 'hpc.Fl_I')
pyc.connect_flow(self, 'hpc.Fl_O', 'bld3.Fl_I')
pyc.connect_flow(self, 'bld3.Fl_O', 'burner.Fl_I')
pyc.connect_flow(self, 'burner.Fl_O', 'hpt.Fl_I')
pyc.connect_flow(self, 'hpt.Fl_O', 'duct11.Fl_I')
pyc.connect_flow(self, 'duct11.Fl_O', 'lpt.Fl_I')
pyc.connect_flow(self, 'lpt.Fl_O', 'duct13.Fl_I')
pyc.connect_flow(self, 'duct13.Fl_O', 'core_nozz.Fl_I')
pyc.connect_flow(self, 'splitter.Fl_O2', 'byp_bld.Fl_I')
pyc.connect_flow(self, 'byp_bld.Fl_O', 'duct15.Fl_I')
pyc.connect_flow(self, 'duct15.Fl_O', 'byp_nozz.Fl_I')
pyc.connect_flow(self, 'hpc.cool1', 'lpt.cool1', connect_stat=False)
pyc.connect_flow(self, 'hpc.cool2', 'lpt.cool2', connect_stat=False)
pyc.connect_flow(self, 'bld3.cool3', 'hpt.cool3', connect_stat=False)
pyc.connect_flow(self, 'bld3.cool4', 'hpt.cool4', connect_stat=False)
newton = self.nonlinear_solver = om.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
newton.options['reraise_child_analysiserror'] = False
# ls = newton.linesearch = BoundsEnforceLS()
ls = newton.linesearch = om.ArmijoGoldsteinLS()
ls.options['maxiter'] = 3
ls.options['bound_enforcement'] = 'scalar'
# ls.options['print_bound_enforce'] = True
self.linear_solver = om.DirectSolver(assemble_jac=True)
def setup(self):
design = self.options['design']
# NOTE: DEFAULT TABULAR thermo doesn't include WAR, so must use CEA here
# (or build your own thermo tables)
self.options['thermo_method'] = 'CEA'
self.options['thermo_data'] = pyc.species_data.wet_air
self.add_subsystem(
'fc',
pyc.FlightConditions(composition=pyc.CEA_AIR_COMPOSITION,
reactant='Water',
mix_ratio_name='WAR'))
self.add_subsystem('inlet', pyc.Inlet())
self.add_subsystem(
'fan', pyc.Compressor(map_data=pyc.FanMap, map_extrap=True))
self.add_subsystem('nozz', pyc.Nozzle())
self.add_subsystem('perf', pyc.Performance(num_nozzles=1,
num_burners=0))
balance = om.BalanceComp()
if design:
self.add_subsystem('shaft',
om.IndepVarComp('Nmech', 1., units='rpm'))
self.connect('shaft.Nmech', 'fan.Nmech')
balance.add_balance('W',
units='lbm/s',
eq_units='hp',
val=50.,
lower=1.,
upper=500.)
self.add_subsystem('balance',
balance,
promotes_inputs=[('rhs:W', 'pwr_target')])
self.connect('fan.power', 'balance.lhs:W')
else:
# vary mass flow till the nozzle area matches the design values
balance.add_balance('W',
units='lbm/s',
eq_units='inch**2',
val=50,
lower=1.,
upper=500.)
self.connect('nozz.Throat:stat:area', 'balance.lhs:W')
balance.add_balance('Nmech',
val=1.,
units='rpm',
lower=0.1,
upper=2.0,
eq_units='hp')
self.connect('balance.Nmech', 'fan.Nmech')
self.connect('fan.power', 'balance.lhs:Nmech')
# self.add_subsystem('shaft', om.IndepVarComp('Nmech', 1., units='rpm'))
# self.connect('shaft.Nmech', 'fan.Nmech')
self.add_subsystem('balance',
balance,
promotes_inputs=[('rhs:Nmech', 'pwr_target')])
self.pyc_connect_flow('fc.Fl_O', 'inlet.Fl_I')
self.pyc_connect_flow('inlet.Fl_O', 'fan.Fl_I')
self.pyc_connect_flow('fan.Fl_O', 'nozz.Fl_I')
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('balance.W', 'fc.W')
newton = self.nonlinear_solver = om.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.options['reraise_child_analysiserror'] = False
#
# newton.linesearch = om.ArmijoGoldsteinLS()
# newton.linesearch.options['maxiter'] = 3
newton.linesearch = om.BoundsEnforceLS()
newton.linesearch.options['bound_enforcement'] = 'scalar'
# newton.linesearch.options['print_bound_enforce'] = True
# newton.linesearch.options['iprint'] = -1
#
self.linear_solver = om.DirectSolver(assemble_jac=True)
# base_class setup should be called as the last thing in your setup
super().setup()
def setup(self):
design = self.options['design']
# NOTE: DEFAULT TABULAR thermo doesn't include WAR, so must use CEA here
# (or build your own thermo tables)
self.options['thermo_method'] = 'CEA'
self.options['thermo_data'] = pyc.species_data.wet_air
# Add engine elements
self.add_subsystem('fc', pyc.FlightConditions(composition=pyc.CEA_AIR_COMPOSITION,
reactant='Water',
mix_ratio_name='WAR'))
self.add_subsystem('inlet', pyc.Inlet())
self.add_subsystem('comp', pyc.Compressor(map_data=pyc.AXI5),
promotes_inputs=['Nmech'])
self.add_subsystem('burner', pyc.Combustor(fuel_type='JP-7'))
self.add_subsystem('turb', pyc.Turbine(map_data=pyc.LPT2269),
promotes_inputs=['Nmech'])
self.add_subsystem('nozz', pyc.Nozzle(nozzType='CD', lossCoef='Cv'))
self.add_subsystem('shaft', pyc.Shaft(num_ports=2), promotes_inputs=['Nmech'])
self.add_subsystem('perf', pyc.Performance(num_nozzles=1, num_burners=1))
# Connect flow stations
self.pyc_connect_flow('fc.Fl_O', 'inlet.Fl_I', connect_w=False)
self.pyc_connect_flow('inlet.Fl_O', 'comp.Fl_I')
self.pyc_connect_flow('comp.Fl_O', 'burner.Fl_I')
self.pyc_connect_flow('burner.Fl_O', 'turb.Fl_I')
self.pyc_connect_flow('turb.Fl_O', 'nozz.Fl_I')
# Connect turbomachinery elements to shaft
self.connect('comp.trq', 'shaft.trq_0')
self.connect('turb.trq', 'shaft.trq_1')
# Connnect nozzle exhaust to freestream static conditions
self.connect('fc.Fl_O:stat:P', 'nozz.Ps_exhaust')
# Connect outputs to 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')
# Add balances for design and off-design
balance = self.add_subsystem('balance', om.BalanceComp())
if design:
balance.add_balance('W', units='lbm/s', eq_units='lbf')
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')
else:
balance.add_balance('FAR', eq_units='lbf', lower=1e-4, val=.3)
self.connect('balance.FAR', 'burner.Fl_I:FAR')
self.connect('perf.Fn', 'balance.lhs:FAR')
balance.add_balance('Nmech', val=1.5, 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=168.0, 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', 'nozz', 'shaft', 'perf'])
newton = self.nonlinear_solver = om.NewtonSolver()
newton.options['atol'] = 1e-6
newton.options['rtol'] = 1e-6
newton.options['iprint'] = 2
newton.options['maxiter'] = 15
newton.options['solve_subsystems'] = True
newton.options['max_sub_solves'] = 100
newton.options['reraise_child_analysiserror'] = False
newton.linesearch = om.BoundsEnforceLS()
# newton.linesearch = ArmijoGoldsteinLS()
# newton.linesearch.options['c'] = .0001
newton.linesearch.options['bound_enforcement'] = 'scalar'
newton.linesearch.options['iprint'] = -1
self.linear_solver = om.DirectSolver(assemble_jac=True)
super().setup()
def setup(self):
thermo_spec = pyc.species_data.wet_air #special species library is called that allows for using initial compositions that include both H and C
design = self.options['design']
self.pyc_add_element(
'fc',
pyc.FlightConditions(thermo_data=thermo_spec,
use_WAR=True,
elements=pyc.WET_AIR_ELEMENTS)
) #WET_AIR_ELEMENTS contains standard dry air compounds as well as H2O
self.pyc_add_element(
'inlet',
pyc.Inlet(design=design,
thermo_data=thermo_spec,
elements=pyc.WET_AIR_ELEMENTS))
self.pyc_add_element(
'fan',
pyc.Compressor(thermo_data=thermo_spec,
elements=pyc.WET_AIR_ELEMENTS,
design=design,
map_data=pyc.FanMap,
map_extrap=True))
self.pyc_add_element(
'nozz',
pyc.Nozzle(thermo_data=thermo_spec, elements=pyc.WET_AIR_ELEMENTS))
self.pyc_add_element('perf',
pyc.Performance(num_nozzles=1, num_burners=0))
balance = om.BalanceComp()
if design:
self.add_subsystem('shaft',
om.IndepVarComp('Nmech', 1., units='rpm'))
self.connect('shaft.Nmech', 'fan.Nmech')
balance.add_balance('W',
units='lbm/s',
eq_units='hp',
val=50.,
lower=1.,
upper=500.)
self.add_subsystem('balance',
balance,
promotes_inputs=[('rhs:W', 'pwr_target')])
self.connect('fan.power', 'balance.lhs:W')
else:
# vary mass flow till the nozzle area matches the design values
balance.add_balance('W',
units='lbm/s',
eq_units='inch**2',
val=50,
lower=1.,
upper=500.)
self.connect('nozz.Throat:stat:area', 'balance.lhs:W')
balance.add_balance('Nmech',
val=1.,
units='rpm',
lower=0.1,
upper=2.0,
eq_units='hp')
self.connect('balance.Nmech', 'fan.Nmech')
self.connect('fan.power', 'balance.lhs:Nmech')
# self.add_subsystem('shaft', om.IndepVarComp('Nmech', 1., units='rpm'))
# self.connect('shaft.Nmech', 'fan.Nmech')
self.add_subsystem('balance',
balance,
promotes_inputs=[('rhs:Nmech', 'pwr_target')])
self.pyc_connect_flow('fc.Fl_O', 'inlet.Fl_I')
self.pyc_connect_flow('inlet.Fl_O', 'fan.Fl_I')
self.pyc_connect_flow('fan.Fl_O', 'nozz.Fl_I')
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('balance.W', 'fc.W')
newton = self.nonlinear_solver = om.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.options['reraise_child_analysiserror'] = False
#
# newton.linesearch = om.ArmijoGoldsteinLS()
# newton.linesearch.options['maxiter'] = 3
newton.linesearch = om.BoundsEnforceLS()
newton.linesearch.options['bound_enforcement'] = 'scalar'
# newton.linesearch.options['print_bound_enforce'] = True
# newton.linesearch.options['iprint'] = -1
#
self.linear_solver = om.DirectSolver(assemble_jac=True)
