def setUp(self):
"""Initialization function called before every test function"""
self.fs = FlowStation()
self.fs.W = 100
self.fs.setDryAir()
self.fs.setTotalTP(518, 15)
def execute(self):
Fl_I = self.Fl_I
Fl_O = self.Fl_O
fs_ideal = FlowStation()
Fl_O.W = Fl_I.W
if self.run_design:
#Design Calculations
Pt_out = self.Fl_I.Pt * self.PR_des
self.PR = self.PR_des
fs_ideal.setTotalSP(Fl_I.s, Pt_out)
ht_out = (fs_ideal.ht - Fl_I.ht) / self.eff_des + Fl_I.ht
Fl_O.setTotal_hP(ht_out, Pt_out)
Fl_O.Mach = self.MNexit_des
self._exit_area_des = Fl_O.area
self._Wc_des = Fl_I.Wc
else:
#Assumed Op Line Calculation
self.PR = self._op_line(Fl_I.Wc)
self.eff = self.eff_des #TODO: add in eff variation with W
#Operational Conditions
Pt_out = Fl_I.Pt * self.PR
fs_ideal.setTotalSP(Fl_I.s, Pt_out)
ht_out = (fs_ideal.ht - Fl_I.ht) / self.eff + Fl_I.ht
Fl_O.setTotal_hP(ht_out, Pt_out)
Fl_O.area = self._exit_area_des #causes Mach to be calculated based on fixed area
C = GAS_CONSTANT * math.log(self.PR)
delta_s = Fl_O.s - Fl_I.s
self.eff_poly = C / (C + delta_s)
self.pwr = Fl_I.W * (Fl_O.ht - Fl_I.ht) * 1.4148532 #btu/s to hp
self.tip_radius = (Fl_O.area / math.pi / (1 - self.hub_to_tip**2))**.5
self.hub_radius = self.hub_to_tip * self.tip_radius
def test_copyFS(self):
#print "TESTING"
self.new_fs = FlowStation()
self.new_fs.copy_from(self.fs)
assert_rel_error(self, self.new_fs.Tt, 518, .0001)
assert_rel_error(self, self.new_fs.Pt, 15, .0001)
def testMN(self):
self.fs = FlowStation()
self.fs.setReactant(6)
self.fs.W = 100
self.fs.setTotalTP(5000, 540)
self.fs.Mach = 3.
assert_rel_error(self, self.fs.Mach, 3., .0001)
assert_rel_error(self, self.fs.Ts, 2052.78, .0001)
assert_rel_error(self, self.fs.Ps, 13.032, .0001)
assert_rel_error(self, self.fs.Vflow, 24991.2, .0001)
assert_rel_error(self, self.fs.rhos, .001192, .0001)
assert_rel_error(self, self.fs.gams, 1.370663, .0001)
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 test_add(self):
self.fs1 = FlowStation()
self.fs1.setDryAir()
self.fs1.setTotalTP(1100, 15)
self.fs1.W = 100.
self.fs1.setWAR(.02)
self.fs1.setTotalTP(1100, 400)
self.fs.add(self.fs1)
assert_rel_error(self, self.fs.Tt, 1932.471, .0001)
assert_rel_error(self, self.fs.W, 202.5, .0001)
assert_rel_error(self, self.fs.FAR, .012623, .001)
assert_rel_error(self, self.fs.Pt, 400, .001)
assert_rel_error(self, self.fs.ht, 71.83056, .0001)
assert_rel_error(self, self.fs.gamt, 1.3200, .0001)
assert_rel_error(self, self.fs.WAR, .00990099, .0001)
def execute(self):
fs_tube = self.fs_tube = FlowStation()
tube_rad = cu(self.radius_tube, 'cm', 'ft') #convert to ft
inlet_rad = cu(self.radius_inlet, 'cm', 'ft')
#A = pi(r^2)
self._tube_area = pi * (tube_rad**2) #ft**2
self._inlet_area = pi * (inlet_rad**2) #ft**2
self._bypass_area = self._tube_area - self._inlet_area
self._Ts = cu(self.Ts_tube, 'degK', 'degR') #convert to R
self._Ps = cu(self.Ps_tube, 'Pa', 'psi') #convert to psi
area_ratio_target = self._tube_area / self._bypass_area
#iterate over pod speed until the area ratio = A_tube / A_bypass
def f(m_guess):
fs_tube.setStaticTsPsMN(
self._Ts, self._Ps, m_guess
) #set the static conditions iteratively until correct (Ts, Ps are known)
gam = fs_tube.gamt
g_exp = (gam + 1) / (2 * (gam - 1))
ar = ((gam + 1) / 2)**(-1 * g_exp) * (
(1 + (gam - 1) / 2 * m_guess**2)**g_exp) / m_guess
return ar - area_ratio_target
#Solve for Mach where AR = AR_target
self.limit_Mach = secant(
f, .3, x_min=0, x_max=1
) #value not actually needed, fs_tube contains necessary flow information
self.limit_speed = cu(fs_tube.Vflow, 'ft',
'm') #convert to meters/second
#excess mass flow calculation
fs_tube.setStaticTsPsMN(self._Ts, self._Ps, self.Mach_pod)
self.W_tube = cu(fs_tube.rhos * fs_tube.Vflow * self._tube_area, 'lbm',
'kg') #convert to kg/sec
fs_tube.Mach = self.Mach_bypass #Kantrowitz flow is at these total conditions, but with Mach 1
self.W_kant = cu(fs_tube.rhos * fs_tube.Vflow * self._bypass_area,
'lbm', 'kg') #convert to kg/sec
#print "test", fs_tube.rhos, fs_tube.Vflow, self._bypass_area, self.W_kant
self.W_excess = self.W_tube - self.W_kant
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 setUp(self):
self.fs = FlowStation()
self.fs.W = 100.
self.fs.setDryAir()
self.fs.setTotalTP(1100, 400)
def setUp(self):
self.fs = FlowStation()
self.fs.setDryAir()
self.fs.setTotalTP(1100, 400)
self.fs.W = 100
self.fs.burn(4, 2.5, -642)
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
