def __init__(self):
super(TubeTemp, self).__init__()
self.add('tm', TubeWallTemp(), promotes=['radius_outer_tube'])
self.add('tmp_balance', TempBalance())
self.add('nozzle_air', FlowStart(thermo_data=janaf, elements=AIR_MIX))
self.add('bearing_air', FlowStart(thermo_data=janaf, elements=AIR_MIX))
self.connect("nozzle_air.Fl_O:tot:T", "tm.nozzle_air_Tt")
self.connect("nozzle_air.Fl_O:tot:Cp", "tm.nozzle_air_Cp")
self.connect("nozzle_air.Fl_O:stat:W", "tm.nozzle_air_W")
self.connect("bearing_air.Fl_O:tot:T", "tm.bearing_air_Tt")
self.connect("bearing_air.Fl_O:tot:Cp", "tm.bearing_air_Cp")
self.connect("bearing_air.Fl_O:stat:W", "tm.bearing_air_W")
self.connect('tm.ss_temp_residual', 'tmp_balance.ss_temp_residual')
self.connect('tmp_balance.temp_boundary', 'tm.temp_boundary')
self.nl_solver = Newton()
self.nl_solver.options['atol'] = 1e-5
self.nl_solver.options['iprint'] = 1
self.nl_solver.options['rtol'] = 1e-5
self.nl_solver.options['maxiter'] = 50
self.ln_solver = ScipyGMRES()
self.ln_solver.options['atol'] = 1e-6
self.ln_solver.options['maxiter'] = 100
self.ln_solver.options['restart'] = 100
def __init__(self):
super(SteadyStateVacuum, self).__init__()
des_vars = (('ram_recovery', 0.99), ('effDes', 0.8), ('duct_MN', 0.0),
('duct_dPqP', 0.), ('nozzle_Cfg', 1.0),
('nozzle_dPqP', 0.), ('shaft_Nmech', 10000.), ('inlet_MN',
0.0),
('comp_MN', 0.5), ('vehicle_mach', 0.8), ('Pa', 101.3e3, {
'units': 'Pa'
}))
self.add('input_vars', IndepVarComp(des_vars))
self.add('fl_start', FlowStart(thermo_data=janaf, elements=AIR_MIX))
# internal flow
self.add('comp', Compressor(thermo_data=janaf, elements=AIR_MIX))
self.add('q', ExecComp('Prc = Pa/Ps'), promotes=['Prc', 'Pa'])
self.add('q1',
ExecComp('m_dot = 3*(A_tube*L_pod)*(1/pod_period)'),
promotes=['m_dot', 'pod_period', 'A_tube', 'L_pod'])
# connect components
connect_flow(self, 'fl_start.Fl_O', 'comp.Fl_I')
self.connect('input_vars.effDes', 'comp.map.effDes')
self.connect('input_vars.comp_MN', 'comp.MN_target')
self.connect('input_vars.shaft_Nmech', 'comp.Nmech')
self.connect('input_vars.vehicle_mach', 'fl_start.MN_target')
self.connect('input_vars.Pa', 'Pa')
self.connect('Prc', 'comp.map.PRdes')
self.connect('m_dot', 'fl_start.W')
self.connect('fl_start.P', 'q.Ps')
def __init__(self):
super(CompressionCycle, self).__init__()
# initiate components
#self.add('fc', FlightConditions())
self.add('fl_start', FlowStart(thermo_data=janaf, elements=AIR_MIX))
self.add('tube', Duct(thermo_data=janaf, elements=AIR_MIX))
self.add('splitter', Splitter(thermo_data=janaf, elements=AIR_MIX))
# internal flow
self.add('inlet', Inlet(thermo_data=janaf, elements=AIR_MIX))
self.add('comp', Compressor(thermo_data=janaf, elements=AIR_MIX))
self.add('duct', Duct(thermo_data=janaf, elements=AIR_MIX))
self.add('nozzle', Nozzle(thermo_data=janaf, elements=AIR_MIX))
self.add('shaft', Shaft(1))
#external flow
self.add('bypass', Duct(thermo_data=janaf, elements=AIR_MIX))
self.add('bypass_exit', Duct(thermo_data=janaf, elements=AIR_MIX))
# connect components
connect_flow(self, 'fl_start.Fl_O', 'tube.Fl_I')
connect_flow(self, 'tube.Fl_O', 'splitter.Fl_I')
connect_flow(self, 'splitter.Fl_O1', 'inlet.Fl_I')
connect_flow(self, 'inlet.Fl_O', 'comp.Fl_I')
connect_flow(self, 'comp.Fl_O', 'duct.Fl_I')
connect_flow(self, 'duct.Fl_O', 'nozzle.Fl_I')
# bypass stream
connect_flow(self, 'splitter.Fl_O2', 'bypass.Fl_I')
connect_flow(self, 'bypass.Fl_O', 'bypass_exit.Fl_I')
self.connect('comp.trq', 'shaft.trq_0')
self.connect('shaft.Nmech', 'comp.Nmech')
def __init__(self):
super(FlowPath, self).__init__()
des_vars = (('ram_recovery', 0.99), ('effDes', 0.9), ('duct_MN', 0.65),
('duct_dPqP', 0.), ('nozzle_Cfg', 1.0),
('nozzle_dPqP', 0.), ('shaft_Nmech', 10000.),
('inlet_MN', 0.6), ('comp_MN', 0.65))
self.add('input_vars', IndepVarComp(des_vars))
self.add('fl_start', FlowStart(thermo_data=janaf, elements=AIR_MIX))
# internal flow
self.add('inlet', Inlet(thermo_data=janaf, elements=AIR_MIX))
self.add('comp', Compressor(thermo_data=janaf, elements=AIR_MIX))
self.add('duct', Duct(thermo_data=janaf, elements=AIR_MIX))
self.add('nozzle', Nozzle(thermo_data=janaf, elements=AIR_MIX))
self.add('shaft', Shaft(1))
# connect components
connect_flow(self, 'fl_start.Fl_O', 'inlet.Fl_I')
connect_flow(self, 'inlet.Fl_O', 'comp.Fl_I')
connect_flow(self, 'comp.Fl_O', 'duct.Fl_I')
connect_flow(self, 'duct.Fl_O', 'nozzle.Fl_I')
self.connect('input_vars.ram_recovery', 'inlet.ram_recovery')
self.connect('input_vars.effDes', 'comp.map.effDes')
self.connect('input_vars.duct_MN', 'duct.MN_target')
self.connect('input_vars.duct_dPqP', 'duct.dPqP')
self.connect('input_vars.nozzle_Cfg', 'nozzle.Cfg')
self.connect('input_vars.nozzle_dPqP', 'nozzle.dPqP')
self.connect('input_vars.shaft_Nmech', 'shaft.Nmech')
self.connect('input_vars.inlet_MN', 'inlet.MN_target')
self.connect('input_vars.comp_MN', 'comp.MN_target')
self.connect('comp.trq', 'shaft.trq_0')
self.connect('shaft.Nmech', 'comp.Nmech')
from openmdao.core.problem import Problem
from openmdao.core.group import Group
from openmdao.core.component import Component
from pycycle.components import FlowStart
from pycycle import species_data
from pycycle.constants import AIR_MIX
from openmdao.components.indep_var_comp import IndepVarComp
if __name__ == "__main__":
# -------------------------
# --- Default Test Case ---
# -------------------------
p1 = Problem()
p1.root = Group()
#p1.root.add("freestream",Freestream())
p1.root.add("fs", FlowStart())
params = (
('P', 0.5, {
"units": "psi"
}),
('T', 291.0, {
"units": "K"
}),
('MN', 0.8),
)
p1.root.add('des_vars', IndepVarComp(params))
p1.root.connect('des_vars.P', 'fs.P')
#p1.root.connect('des_vars.MN', 'fs.MN')
p1.root.connect('des_vars.T', 'fs.T')