def test_copy_flow(self):
a = set_as_top(Assembly())
a.add('comp1', DummyComp())
a.add('comp2', DummyComp())
a.connect('comp1.Fl_O', 'comp2.Fl_I')
a.driver.workflow.add(['comp1', 'comp2'])
fs = FlowStation()
fs.W = 100
fs.setDryAir()
fs.setTotalTP(518, 15)
a.comp1.Fl_I = fs
a.run()
def configure(self):
hx = self.add('hx', HeatExchanger())
driver = self.add('driver',BroydenSolver())
driver.add_parameter('hx.T_hot_out',low=0.,high=1000.)
driver.add_parameter('hx.T_cold_out',low=0.,high=1000.)
driver.add_constraint('hx.residual_qmax=0')
driver.add_constraint('hx.residual_e_balance=0')
#hx.Wh = 0.49
#hx.Cp_hot = 1.006
#hx.T_hot_in = 791
fs = FlowStation()
fs.setTotalTP(1423.8, 0.302712118187) #R, psi
fs.W = 1.0
hx.Fl_I = fs
hx.W_cold = .45
hx.T_hot_out = hx.Fl_I.Tt
hx.T_cold_out = hx.T_cold_in
driver.workflow.add(['hx'])
def execute(self):
Fl_I = self.Fl_I
Fl_O = self.Fl_O
Fl_ref = self.Fl_ref
fs_throat = FlowStation()
fs_exitIdeal = FlowStation()
fs_throat.W = Fl_I.W
Pt_out = (1-self.dPqP)*Fl_I.Pt
fs_throat.setTotalTP( Fl_I.Tt, Pt_out )
fs_throat.Mach = 1.0
self.Athroat_dmd = fs_throat.area
fs_exitIdeal.W = Fl_I.W
fs_exitIdeal.setTotalTP( Fl_I.Tt, Pt_out )
fs_exitIdeal.Ps = Fl_ref.Ps
Fl_O.W = Fl_I.W
Fl_O.setTotalTP( Fl_I.Tt, Pt_out )
Fl_O.Mach = fs_exitIdeal.Mach
if self.run_design:
# Design Calculations at throat
self.Athroat_des = fs_throat.area
# Design calculations at exit
self.Aexit_des = fs_exitIdeal.area
self.switchRegime = "PERFECTLY_EXPANDED"
else:
# Find subsonic solution, curve 4
Fl_O.sub_or_super = "sub"
Fl_O.area = self.Aexit_des
MachSubsonic = Fl_O.Mach
if MachSubsonic > 1:
print "invalid nozzle subsonic solution"
PsSubsonic = Fl_O.Ps
# Find supersonic solution, curve 5
Fl_O.sub_or_super = "super"
Fl_O.area = self.Aexit_des
MachSupersonic = Fl_O.Mach
PsSupersonic = Fl_O.Ps
# normal shock at nozzle exit, curve c
Fl_O.sub_or_super = "sub"
Msuper = MachSupersonic
PtExit = self.shockPR( Msuper, fs_throat.gams ) * fs_throat.Pt
Fl_O.setTotalTP( fs_throat.Tt, PtExit )
Fl_O.area = self.Aexit_des
PsShock = Fl_O.Ps
# find correct operating regime
# curves 1 to 4
if Fl_ref.Ps >= PsSubsonic:
self.switchRegime = "UNCHOKED"
fs_throat.sub_or_super = "sub"
Fl_O.sub_or_super = "sub"
fs_throat.area = self.Athroat_des
Fl_O.setTotalTP( fs_throat.Tt, fs_throat.Pt )
Fl_O.area = self.Aexit_des
# between curves 4 and c
elif Fl_ref.Ps < PsSubsonic and Fl_ref.Ps >= PsShock:
self.switchRegime = "NORMAL_SHOCK"
Fl_O.sub_or_super = "sub"
Fl_O.Ps = Fl_ref.Ps
# between curves c and 5
elif Fl_ref.Ps < PsShock and Fl_ref.Ps > PsSupersonic:
self.switchRegime = "OVEREXPANDED"
Fl_O.sub_or_super = "super"
Fl_O.setTotalTP( fs_throat.Tt, fs_throat.Pt )
Fl_O.area = self.Aexit_des
# between curves 5 and e
elif Fl_ref.Ps <= PsSupersonic:
self.switchRegime = "UNDEREXPANDED"
Fl_O.sub_or_super = "super"
Fl_O.setTotalTP( fs_throat.Tt, fs_throat.Pt )
Fl_O.area = self.Aexit_des
if abs(Fl_ref.Ps - PsSupersonic)/Fl_ref.Ps < .001:
self.switchRegime = "PERFECTLY_EXPANDED"
self.Fg = Fl_O.W*Fl_O.Vflow/32.174 + Fl_O.area*(Fl_O.Ps-Fl_ref.Ps)
self.PR = fs_throat.Pt/Fl_O.Ps
self.AR = Fl_O.area/fs_throat.area
self.WqAexit = Fl_I.W/self.Athroat_des
self.WqAexit_dmd = Fl_I.W/self.Athroat_dmd
if self.switchRegime == "UNCHOKED":
self.WqAexit = Fl_I.W/Fl_ref.Ps
self.WqAexit_dmd = Fl_I.W/Fl_O.Ps
def execute(self):
Fl_I = self.Fl_I
Fl_O = self.Fl_O
Fl_ref = self.Fl_ref
fs_throat = FlowStation()
fs_exitIdeal = FlowStation()
fs_throat.W = Fl_I.W
Pt_out = (1 - self.dPqP) * Fl_I.Pt
fs_throat.setTotalTP(Fl_I.Tt, Pt_out)
fs_throat.Mach = 1.0
self.Athroat_dmd = fs_throat.area
fs_exitIdeal.W = Fl_I.W
fs_exitIdeal.setTotalTP(Fl_I.Tt, Pt_out)
fs_exitIdeal.Ps = Fl_ref.Ps
Fl_O.W = Fl_I.W
Fl_O.setTotalTP(Fl_I.Tt, Pt_out)
Fl_O.Mach = fs_exitIdeal.Mach
if self.run_design:
# Design Calculations at throat
self.Athroat_des = fs_throat.area
# Design calculations at exit
self.Aexit_des = fs_exitIdeal.area
self.switchRegime = "PERFECTLY_EXPANDED"
else:
# Find subsonic solution, curve 4
Fl_O.sub_or_super = "sub"
Fl_O.area = self.Aexit_des
MachSubsonic = Fl_O.Mach
if MachSubsonic > 1:
print "invalid nozzle subsonic solution"
PsSubsonic = Fl_O.Ps
# Find supersonic solution, curve 5
Fl_O.sub_or_super = "super"
Fl_O.area = self.Aexit_des
MachSupersonic = Fl_O.Mach
PsSupersonic = Fl_O.Ps
# normal shock at nozzle exit, curve c
Fl_O.sub_or_super = "sub"
Msuper = MachSupersonic
PtExit = self.shockPR(Msuper, fs_throat.gams) * fs_throat.Pt
Fl_O.setTotalTP(fs_throat.Tt, PtExit)
Fl_O.area = self.Aexit_des
PsShock = Fl_O.Ps
# find correct operating regime
# curves 1 to 4
if Fl_ref.Ps >= PsSubsonic:
self.switchRegime = "UNCHOKED"
fs_throat.sub_or_super = "sub"
Fl_O.sub_or_super = "sub"
fs_throat.area = self.Athroat_des
Fl_O.setTotalTP(fs_throat.Tt, fs_throat.Pt)
Fl_O.area = self.Aexit_des
# between curves 4 and c
elif Fl_ref.Ps < PsSubsonic and Fl_ref.Ps >= PsShock:
self.switchRegime = "NORMAL_SHOCK"
Fl_O.sub_or_super = "sub"
Fl_O.Ps = Fl_ref.Ps
# between curves c and 5
elif Fl_ref.Ps < PsShock and Fl_ref.Ps > PsSupersonic:
self.switchRegime = "OVEREXPANDED"
Fl_O.sub_or_super = "super"
Fl_O.setTotalTP(fs_throat.Tt, fs_throat.Pt)
Fl_O.area = self.Aexit_des
# between curves 5 and e
elif Fl_ref.Ps <= PsSupersonic:
self.switchRegime = "UNDEREXPANDED"
Fl_O.sub_or_super = "super"
Fl_O.setTotalTP(fs_throat.Tt, fs_throat.Pt)
Fl_O.area = self.Aexit_des
if abs(Fl_ref.Ps - PsSupersonic) / Fl_ref.Ps < .001:
self.switchRegime = "PERFECTLY_EXPANDED"
self.Fg = Fl_O.W * Fl_O.Vflow / 32.174 + Fl_O.area * (Fl_O.Ps -
Fl_ref.Ps)
self.PR = fs_throat.Pt / Fl_O.Ps
self.AR = Fl_O.area / fs_throat.area
self.WqAexit = Fl_I.W / self.Athroat_des
self.WqAexit_dmd = Fl_I.W / self.Athroat_dmd
if self.switchRegime == "UNCHOKED":
self.WqAexit = Fl_I.W / Fl_ref.Ps
self.WqAexit_dmd = Fl_I.W / Fl_O.Ps
