def test_6_88(self):
# Letra A
Pa = 60E5
Ta = 650
benz = thermo.Chemical('benzene')
cyclo = thermo.Chemical('cyclohexane')
bc = thermo.Mixture(['benzene','cyclohexane'],zs = [0.5,0.5],T=Ta,P=Pa)
Za = z_find.Lee_Kesler(bc.Tc,bc.Pc,bc.omega,Ta,Pa)
eosamix = thermo.eos_mix.SRKMIX([benz.Tc,cyclo.Tc],[benz.Pc,cyclo.Pc],[benz.omega,cyclo.omega],[0.5,0.5],[[0,0],[0,0]],Ta,Pa)
# Z = thermo.utils.Z(Ta,Pa,eosamix.V_g)
# ZRK,eosa = z_find.SRK(bc.Tc,bc.Pc,bc.omega,Ta,Pa)
#eos_PR = thermo.eos.PR(bc.Tc,bc.Pc,bc.omega,T,P)
# Letra B
Pb = 100E5
Tb = 300
#cd = thermo.Chemical('carbon dioxide')
#cm = thermo.Chemical('carbon monoxide')
cmd = thermo.Mixture(['carbon dioxide','carbon monoxide'],zs=[0.5,0.5],T=Tb,P=Pb)
Zb = z_find.Lee_Kesler(cmd.Tc,cmd.Pc,cmd.omega,Tb,Pb)
# Letra C
Pc = 100E5
Tc = 600
cdo = thermo.Mixture(['carbon dioxide','n-octane'],zs=[0.5,0.5],T=Tc,P=Pc)
Zc = z_find.Lee_Kesler(cdo.Tc,cdo.Pc,cdo.omega,Tc,Pc)
self.assertEqual([Za,Zb,Zc],[0.68,0.794,0.813],'ValueError:Failed') # values are different, based on what I saw,
def __init__(self, coolant, coolant_massfraction, coolant_massflow,
total_massflow, fuel, oxidiser, mixture_ratio,
chamber_pressure, coolant_temperature, coolant_pressure,
geometry, wall_thickness, thermal_conductivity):
"""[summary]
Coolant flow properties stored as total conditions
Hot gas properties from CEA, currently assumes constant gas properties in chamber
USE SI UNITS
"""
self.chamber_pressure = chamber_pressure
self.mixture_ratio = mixture_ratio
self.massflow = total_massflow
self.coolant_massflow = coolant_massflow
self.coolant = thermo.Mixture(coolant,
ws=coolant_massfraction,
T=coolant_temperature,
P=coolant_pressure)
self.chamber_diameter = 2 * geometry[0, 1]
self.throat_diameter = 2 * min(geometry[:, 1])
self.expansion_ratio = np.pi * geometry[-1][1]**2 / (
np.pi * self.throat_diameter**2 / 4)
self.wall_thickness = wall_thickness
self.thermal_conductivity = thermal_conductivity
# get hot gas properties from CEA, use 'throat' as this is the most critical area
self.cea = CEA(fuel, oxidiser, self.chamber_pressure)
self.cea.metric_cea_output('chamber', self.mixture_ratio,
self.expansion_ratio)
def __init__(self,
thermal_conductivity,
max_wall_thickness,
fluid_temperature,
fluid_pressure,
fluid_massflow,
fluid,
fluid_mixture,
hydrolic_diameter,
massflow,
chamber_pressure,
velocity,
gas_temperature=0):
"""
Estimates wall temperature at injection element. Using convective and radiative heat transfer
"""
self.thermal_conductivity = thermal_conductivity
self.max_wall_thickness = max_wall_thickness
self.fluid = thermo.Mixture(fluid,
ws=fluid_mixture,
T=fluid_temperature,
P=fluid_pressure)
self.flow_velocity = velocity
self.chamber_diameter = std.chamber_diameter
self.throat_diameter = std.throat_diameter
self.chamber_pressure = chamber_pressure
self.massflow = massflow
self.hydrolic_diameter = hydrolic_diameter
self.fluid_massflow = fluid_massflow
self.gas_temperature = gas_temperature
self.cea = std.cea
def __init__(self, fluid, mixture, temperature, pressure, length, massflow,
pressuredrop, inletangle):
self.fluid = thermo.Mixture(fluid,
ws=mixture,
T=temperature,
P=pressure)
self.length = length
self.massflow = massflow
self.pressuredrop = pressuredrop
self.inletangle = inletangle
def __init__(self, fluid, mixture, temperature, pressure, length,
pressuredrop, massflow, r_i):
self.fluid = thermo.Mixture(fluid,
ws=mixture,
T=temperature,
P=pressure)
self.length = length
self.pressuredrop = pressuredrop
self.r_i = r_i
self.massflow = massflow
def iterator(self,
y_coordinate,
x_coordinate,
section_length,
section_number,
initial_guess,
mach,
t_aw,
eta=1,
max_iter=1000,
tol=1e-6):
wall_temperature = 300
coolant_wall_temperature = 300
wall_thickness = self.cooling_geometry.wt1_arr[section_number]
iteration = 0
difference = 1
while difference > tol:
halpha = self.heat_trans_coeff_gas(
mach, wall_temperature, t_aw,
y_coordinate) * eta # film cooling correction
halpha_c, Re, Nu, flowvelocity = self.heat_trans_coeff_coolant(
wall_temperature, coolant_wall_temperature, x_coordinate,
y_coordinate, section_length, section_number)
radiation = self.radiation(y_coordinate, mach)
heat_flux = (t_aw - self.coolant.T + radiation / halpha) / (
1 / halpha + wall_thickness / self.thermal_conductivity +
1 / halpha_c)
new_wall_temp = -((heat_flux - radiation) / halpha - t_aw)
difference = abs(new_wall_temp - wall_temperature)
iteration += 1
if iteration > max_iter:
raise ValueError('Non-convergence, iteration number exceeded ',
max_iter)
wall_temperature = new_wall_temp
coolant_wall_temperature = -heat_flux * wall_thickness / self.thermal_conductivity + new_wall_temp
T_new = self.coolant.T + heat_flux * 2 * np.pi * y_coordinate * section_length / (
self.coolant_massflow * self.coolant.Cp)
dp = self.pressure_drop(6e-6, section_length, section_number,
y_coordinate)
self.coolant = thermo.Mixture(self.coolant_species,
ws=self.coolant_massfraction,
T=T_new,
P=self.coolant.P - dp)
print(section_number)
print(self.coolant.T)
return heat_flux, wall_temperature, Re, Nu, flowvelocity, radiation, halpha, halpha_c
def test_6_86(self):
P = 5500E3
T = 363.15
mponto = 1.4 #kg/s
Vmax = 30 #m/s
ymet = 0.5
yprop = 1 - ymet
pm = thermo.Mixture(['methane','propane'],zs = [ymet,yprop],T=T,P=P)
Z = z_find.Lee_Kesler(pm.Tc,pm.Pc,pm.omega,T,P)
v = Z*R*T/(P*pm.MW*10**(-3))
A = mponto*v/Vmax
d = math.sqrt(A*4/math.pi)
self.assertAlmostEqual(d,0.0297,3,'ValueError:Failed') #D = 0.002964
def heat_trans_coeff_coolant(self, hydrolic_diameter, wall_temperature): coolant_area = hydrolic_diameter**2/4 * np.pi * self.number_of_channels flowvelocity = self.coolant_massflow/(self.coolant.rho * coolant_area) Pr = self.coolant.Pr Re = self.coolant.rho*flowvelocity*hydrolic_diameter/self.coolant.mu k = self.coolant.Cp*self.coolant.mu/Pr #Nu = 0.023*Re**0.8*Pr**0.4 wall_fluid = thermo.Mixture(self.coolant_species, ws=self.coolant_massfraction, P=self.coolant.P, T=wall_temperature) Nu = 0.0208*Re**0.8*Pr**0.4*(1+0.01457*wall_fluid.mu/self.coolant.mu) #Hess & Kunz relationship halpha = Nu*k/hydrolic_diameter return halpha, Re, Nu
def __init__(self,
coolant,
coolant_massfraction,
coolant_massflow,
total_massflow,
fuel,
oxidiser,
mixture_ratio,
chamber_pressure,
coolant_temperature,
coolant_pressure,
geometry,
number_of_channels,
thermal_conductivity,
method,
k_tbc=0,
t_tbc=0):
"""[summary]
Coolant flow properties stored as total conditions
Hot gas properties from CEA, currently assumes constant gas properties in chamber
USE SI UNITS
"""
self.geometry = geometry
self.chamber_pressure = chamber_pressure
self.mixture_ratio = mixture_ratio
self.massflow = total_massflow
self.coolant_massflow = coolant_massflow
self.coolant = thermo.Mixture(coolant,
ws=coolant_massfraction,
T=coolant_temperature,
P=coolant_pressure)
self.chamber_diameter = 2 * geometry[0, 1]
self.throat_diameter = 2 * min(geometry[:, 1])
self.expansion_ratio = np.pi * geometry[-1][1]**2 / (
np.pi * self.throat_diameter**2 / 4)
self.thermal_conductivity = thermal_conductivity
self.coolant_species = coolant
self.coolant_massfraction = coolant_massfraction
self.number_of_channels = number_of_channels
self.k_tbc = k_tbc
self.t_tbc = t_tbc
self.method = method
# get hot gas properties from CEA
self.cea = CEA(fuel, oxidiser, self.chamber_pressure)
self.cea.metric_cea_output('throat', self.mixture_ratio,
self.expansion_ratio)
def __init__(self, fluid, mixture, temperature, pressure, length,
annulusdiameter, massflow, pressuredrop):
"""UNVARIFIED model of annular injectors. Uses numerical solution to Darcey Weisbach eqaution to determine discharge coefficent with cryo test data
:param fluid: fluid flowing through annulus
:type fluid: string
:param length: length of annulus flow passage (coaxial distance)
:param annulusdiameter: mean diameter of annulus
:param pressuredrop: design pressure drop over injector
"""
self.fluid = thermo.Mixture(fluid,
ws=mixture,
T=temperature,
P=pressure)
self.annulusdiameter = annulusdiameter
self.length = length
self.massflow = massflow
self.pressuredrop = pressuredrop
def heat_trans_coeff_coolant(self, hydraulic_diameter, wall_temperature,
coolant_wall_temperature, x_coordinate,
y_coordinate, section_length):
coolant_area = hydraulic_diameter**2 / 4 * np.pi * self.number_of_channels #hydraulic_diameter / 2 * y_coordinate * 2 * np.pi
flowvelocity = self.coolant_massflow / (self.coolant.rho *
coolant_area)
Pr = self.coolant.Pr
Re = self.coolant.rho * flowvelocity * hydraulic_diameter / self.coolant.mu
k = self.coolant.Cp * self.coolant.mu / Pr
wall_fluid = thermo.Mixture(self.coolant_species,
ws=self.coolant_massfraction,
P=self.coolant.P,
T=coolant_wall_temperature)
#Nu = 0.023*Re**0.8*Pr**0.4#*(self.coolant.T/coolant_wall_temperature) ** (0.57 - 1.59*hydraulic_diameter/x_coordinate)
Nu = 0.0208 * Re**0.8 * Pr**0.4 * (
1 + 0.01457 * wall_fluid.mu / self.coolant.mu
) #Hess & Kunz relationship
'''
def curvature_correction():
idx = np.where(self.geometry[:,0] == x_coordinate)[0][0]
if idx == 0 or idx == len(self.geometry[:,1])-1:
return 1, 0
dydx = (self.geometry[idx+1,1] - self.geometry[idx-1,1]) / (2*section_length)
d2ydx2 = (self.geometry[idx+1,1] - 2*self.geometry[idx,1] + self.geometry[idx-1,1]) / section_length**2
Rc = (1 + dydx**2)**(3/2) / (abs(d2ydx2))
if Rc > 100:
return 1, 0
if d2ydx2 > 0:
c = 0.05
else:
c = -0.05
return Rc,c
Rc, c = curvature_correction()
eta = (Re*(hydraulic_diameter / (2*Rc))**2)**c
'''
eta = 1
halpha = Nu * eta * k / hydraulic_diameter
return halpha, Re, Nu, flowvelocity
def __init__(self):
#def __init__(self, massflow, V_channel,V_chamber, x_loc_ind, inlet_angle,R,P_channel,T_channel,P_chamber,fluid,mixture,wt_channel):
"""
self.fluid = thermo.Mixture(fluid, ws=mixture, T=T_channel[x_loc_ind], P=P_channel[x_loc_ind])
self.wt = wt_channel[x_loc_ind]
self.massflow = massflow
self.pressuredrop = (P_channel[x_loc_ind] - 1/2*self.fluid.rho*V_channel[x_loc_ind]**2)-P_chamber
self.inletangle = inlet_angle
self.V_chamber = V_chamber[x_loc_ind]
self.R = R[x_loc_ind]
"""
self.fluid = thermo.Mixture(['c2h5oh', 'h2o'], [0.9, 0.1],
T=350,
P=65e5)
self.wt = 0.6e-3
self.massflow = 0.2
self.pressuredrop = 15e5
self.inletangle = 30 / 180 * np.pi
self.V_chamber = 200
self.R = 25e-3
def __init__(self, coolant, coolant_massfraction, coolant_massflow, total_massflow, cea, chamber_pressure, coolant_temperature, coolant_pressure, geometry, number_of_channels, thermal_conductivity, k_tbc=0, t_tbc=0): """[summary] Coolant flow properties stored as total conditions Hot gas properties from CEA, currently assumes constant gas properties in chamber """ self.chamber_pressure = chamber_pressure self.massflow = total_massflow self.coolant_massflow = coolant_massflow self.coolant = thermo.Mixture(coolant, ws = coolant_massfraction, T=coolant_temperature, P=coolant_pressure) self.chamber_diameter = 2*geometry[0,1] self.throat_diameter = 2*min(geometry[:,1]) self.expansion_ratio = np.pi*geometry[-1][1]**2/(np.pi*self.throat_diameter**2/4) self.thermal_conductivity = thermal_conductivity self.coolant_species = coolant self.coolant_massfraction = coolant_massfraction self.number_of_channels = number_of_channels self.k_tbc = k_tbc self.t_tbc = t_tbc # get hot gas properties from CEA self.cea = cea
def heat_trans_coeff_coolant(self, wall_temperature,
coolant_wall_temperature, x_coordinate,
y_coordinate, section_length, section_number):
d_h = self.cooling_geometry.dhi_arr[section_number]
A = self.cooling_geometry.Ai_arr[section_number]
flowvelocity = self.coolant_massflow / (self.coolant.rho * A * 2 *
self.cooling_geometry.N)
if self.coolant.phase == 'l':
Pr = self.coolant.Prl
Cp = self.coolant.Cpl
mu = self.coolant.mul
if self.coolant.phase == 'g':
Pr = self.coolant.Prg
Cp = self.coolant.Cpg
mu = self.coolant.mug
Pr = 0.75 + 1.63 / np.log(1 + Pr / 0.0015) # turbulent Pr correction
Re = self.coolant.rho * flowvelocity * d_h / mu
k = Cp * mu / Pr
wall_fluid = thermo.Mixture(self.coolant_species,
ws=self.coolant_massfraction,
P=self.coolant.P,
T=coolant_wall_temperature)
Nu = 0.0208 * Re**0.8 * Pr**0.4 * (1 + 0.01457 * wall_fluid.mug / mu
) #Hess & Kunz relationship
halpha = Nu * k / d_h
#halpha = 0.023*self.coolant.Cp**0.333*k**0.667 / (self.coolant.mu**0.467*d_h**0.2) * (self.coolant_massflow/(np.pi/4 * d_h**2))**0.8 # McAdams
#halpha = 0.023*k/d_h * (self.coolant.Cp / (k*self.coolant.mu))**0.4 * (self.coolant_massflow*d_h/A)**0.8
#Nu = halpha / k * d_h
return halpha, Re, Nu, flowvelocity
an_inj = AnnulusInjector(['c2h5oh', 'h2o'], [0.9, 0.1], 410, 62.5e5, 2e-3,
30e-3, 2.227, 13.3e5)
an_inj.injector()
print(an_inj.mu)
print(an_inj.diameter * 1000)
print(an_inj.velocity)
an_orifice = AnnularOrifice(['c2h5oh', 'h2o'], [0.9, 0.1], 410, 62.5e5,
2e-3, 13.3e5, 2.227, 30e-3 / 2)
an_orifice.injector()
print(an_orifice.mu)
print(an_orifice.diameter * 1000)
print(an_orifice.velocity)
#print((liq_inj.velocity*liq_inj.massflow*n_holes)/(an_inj.velocity*an_inj.massflow))
mass_fraction = [0.9, 0.1]
mole_fraction = [46 / 64, 18 / 64]
n_holes = np.arange(20, 100, 1)
massflow = 3.5858
print(thermo.Mixture(['c2h5oh', 'h2o'], [0.8, 0.2], T=288.15, P=1e5).rho)
print(thermo.Mixture(['c2h5oh', 'h2o'], [0.8, 0.2], T=288.15, P=70e5).rho)
print(thermo.Chemical('o2', T=90, P=1e5).rho)
#ohnesorge_number(liq_inj, n_holes, massflow, mass_fraction, mole_fraction)
#annulus_verification(24.2e-3/2, 25.32e-3/2, 'h2o', np.arange(1e5, 15e5, 0.1e5), 288, 0.61)
# CEA input values
OF = 1.49
oxidiser = 'LOX'
ethanol80 = rocketcea.blends.newFuelBlend(fuelL=['C2H5OH', 'H2O'], fuelPcentL=[80,20]) # new fuel blend for CEA
cea = ht.CEA(ethanol80, oxidiser, chamber_pressure)
cea.metric_cea_output('throat', OF, expansion_ratio)
# Thermo input values
total_massflow = 5.8 # [kg/s]
fuel_massflow = total_massflow / (1+OF)
mu = 0.15
film_massflow = fuel_massflow * mu / (1-mu)
coolant_velocity = 10
film_start_idx = 46
film_coolant = thermo.Mixture(['c2h5oh','h2o'], ws=[0.8,0.2], P=60e5, T=288)
ox_massflow = total_massflow - fuel_massflow
fuel_massflow += film_massflow
fuel_composition = ['c2h5oh']
fuel_mass_fraction = [1]
# Film cooling BETA
heat = ht.Heattransfer(fuel_composition, fuel_mass_fraction, fuel_massflow, total_massflow, ethanol80, oxidiser, OF, chamber_pressure, fuel_temperature, fuel_inlet_pressure, geometry, cooling_channels, thermal_conductivity, method)
heat.heatflux(geometry, eta_film=1, x_film_injection=0)
film = fm.FilmCooling(film_coolant, cea, total_massflow, chamber_pressure, coolant_velocity)
film.film_effectiveness(film_start_idx, heat.section_length[::-1], heat.mach[::-1], heat.q[::-1], heat.q_rad[::-1], film_massflow, geometry[:,1])
heat = ht.Heattransfer(fuel_composition, fuel_mass_fraction, fuel_massflow, total_massflow, ethanol80, oxidiser, OF, chamber_pressure, fuel_temperature, fuel_inlet_pressure, geometry, cooling_channels, thermal_conductivity, method)
flowrateCoolant5 = 40 #GPM
tempAir5 = 30 # Celsius
#constants
tempCoolant = 95 # Celsius
finHeight= 10.0/1000
finSpacing = 1.7/1000 #ref 1.59
tubeWall = .5/1000
tubeHeight = 2.0/1000 #outer dimension
##fluid constants
##coolant mixture calcs using thermo module
percentGlycol = .5
Coolant = thermo.Mixture(['water', 'glycol'], Vfls=[1-percentGlycol, percentGlycol], T= 273+tempCoolant, P=2E5)
k_Coolant = Coolant.k # W/(m K), thermal conductivity
C_Coolant = Coolant.Cp # J/(kg K), Specific Heat
rho_Coolant = Coolant.rho # kg/m3, Density
mu_Coolant = Coolant.mu # Pa s, Dynamic Viscosity
k_Air = 0.02664 # W/(m K), thermal conductivity
C_Air = 1004.16 # J/(kg K), Specific Heat
rho_Air = 1.13731 # kg/m3, Density
mu_Air = 0.00001912 # Pa s, Dynamic Viscosity
def radCalc(coreHeight, coreWidth, coreThickness, fanFlow, flowrateCoolant, tempAir):
## operating conditions
fanFlow = fanFlow / 60. / 35.3 #convert to m3/s
def get_Tout(T, flow, rho):
coreHeight = x * 25.4/1000 #all dims in meters
coreWidth = y * 25.4/1000 #coolant tank to tank
coreThickness = z * 25.4/1000
wallThickness = 0.5/1000
finHeightAir= 6.0/1000
finSpacingAir = 25.4/12.5/1000 #ref frozen spec
finHeightCoolant= 2.0/1000
finSpacingCoolant = 25.4/8.5/1000 #ref frozen spec
## calculate surface areas
numberofBars = math.floor((coreHeight - wallThickness)/(finHeightAir + wallThickness + finHeightCoolant + wallThickness))
numberCoolantPass = (coreThickness/finSpacingCoolant + 1) * numberofBars
numberAirPass = (coreWidth/finSpacingAir + 1) * numberofBars
areaCoolant = numberCoolantPass * 2 * coreWidth * (finSpacingCoolant + finHeightCoolant)
areaAir = numberAirPass * 2 * coreThickness * (finSpacingAir + finHeightAir)
##fluid constants
##coolant to 50-50 glycol/water
tempAir = T-273.0 # Celsius
tempCoolant = var.coolantTemp # Celsius
percentGlycol = .5
Coolant = thermo.Mixture(['water', 'glycol'], Vfls=[1-percentGlycol, percentGlycol], T= 273+tempCoolant, P=2E5)
k_Coolant = Coolant.k # W/(m K), thermal conductivity
C_Coolant = Coolant.Cp # J/(kg K), Specific Heat
rho_Coolant = Coolant.rho # kg/m3, Density
mu_Coolant = Coolant.mu # Pa s, Dynamic Viscosity
k_Air = 0.02664 # W/(m K), thermal conductivity
C_Air = 1004.16 # J/(kg K), Specific Heat
rho_Air = rho # kg/m3, Density
mu_Air = 0.00001912 # Pa s, Dynamic Viscosity
## operating conditions
flowrateCoolant = 5 #GPM, volumetric
flowrateCoolant = flowrateCoolant * 3.8 #LPM
flowrateCoolant = flowrateCoolant /60.0/1000. # convert to m3/s
massflowCoolant = flowrateCoolant *rho_Coolant
massflowAir = flow
flowrateAir = massflowAir/rho_Air
## fluids calcs
#Coolant
Dh_Coolant = 4 * (finHeightCoolant * finSpacingCoolant) / (2*(finHeightCoolant + finSpacingCoolant))
tubeVelocity = flowrateCoolant/numberCoolantPass/(finHeightCoolant*finSpacingCoolant)
reynoldsCoolant = fluids.core.Reynolds(D=Dh_Coolant, rho=rho_Coolant, V=tubeVelocity, mu=mu_Coolant)
reynoldsCoolant = 5000.0 #force turbulent
prandltCoolant = fluids.core.Prandtl(Cp=C_Coolant , k=k_Coolant , mu=mu_Coolant, nu=None, rho=None, alpha=None)
if reynoldsCoolant<2600:
nusseltCoolant = ht.conv_internal.laminar_Q_const()
else:
nusseltCoolant = ht.conv_internal.turbulent_Dittus_Boelter(Re=reynoldsCoolant, Pr=prandltCoolant, heating=True)
h_Coolant = nusseltCoolant * k_Coolant / Dh_Coolant
#AIR
Dh_Air = 4 * (finHeightAir * finSpacingAir) / (2*(finHeightAir + finSpacingAir))
airVelocity = flowrateAir/numberAirPass/(finHeightAir*finSpacingAir)
reynoldsAir = fluids.core.Reynolds(D=Dh_Air, rho=rho_Air, V=airVelocity, mu=mu_Air)
reynoldsAir = 5000.0 # force turbulent
prandltAir = fluids.core.Prandtl(Cp=C_Air , k=k_Air , mu=mu_Air, nu=None, rho=None, alpha=None)
if reynoldsAir<2600:
nusseltAir = ht.conv_internal.laminar_Q_const()
else:
nusseltAir = ht.conv_internal.turbulent_Dittus_Boelter(Re=reynoldsAir, Pr=prandltAir, heating=False)
#nusseltAir =ht.conv_external.Nu_cylinder_Zukauskas(Re=reynoldsAir, Pr=prandltAir, Prw=None)
#nusseltAir = 10 # manual overide for laminare flow
h_Air = nusseltAir * k_Air / Dh_Air
#calculate UA
UA = 1/(h_Coolant*areaCoolant) + 1/(h_Air*areaAir)
UA = 1/UA
#NTU = ht.hx.effectiveness_NTU_method(mh=massflowCoolant, mc=massflowAir, Cph=C_Coolant, Cpc=C_Air, subtype='crossflow', Thi=tempCoolant, Tho=None, Tci=tempAir, Tco=None, UA=UA)
NTU = ht.hx.effectiveness_NTU_method(mh=massflowAir, mc=massflowCoolant, Cph=C_Air, Cpc=C_Coolant, subtype='crossflow', Thi=tempAir, Tho=None, Tci=tempCoolant, Tco=None, UA=UA)
#print NTU
#print NTU['Q']
Tout = NTU['Tho'] + 273 #kelvin
Pwr = NTU['Q'] / 1000 #kW
TCout = NTU['Tco']
#output = [Tout, flowrateAir2]
return Tout, Pwr
elevation = var.elevation # ft
elevation = ft_to_m(elevation)
ambient = var.ambient #C
ambient += 273 #K
#get air components and pressure at given elevation
atm = fluids.ATMOSPHERE_NRLMSISE00(Z=elevation) #z is meters
Patm = atm.P
N2 = atm.zs[0]
O2 = atm.zs[1]
Ar = atm.zs[2]
#create air mixture so I can get some properties I need
air = thermo.Mixture(['nitrogen', 'oxygen', 'argon'],
Vfgs=[N2, O2, Ar],
T=ambient,
P=Patm)
k = air.isentropic_exponent
D1 = air.rho
# recalculate air density at given temp and pressure
def air_density_calc(T, P):
air.calculate(T=T, P=P)
density = air.rho
return density
#compressor values
Pgage = var.boost #psi gage
Pgage = psi_to_Pa(Pgage) #Pa gage
# Hot gas properties
# can choose beteen 'chamber'. 'throat' and 'exit' for metric_cea_output\
cea = heatflux.CEA(ethanol90, oxidiser, chamber_pressure)
cea.metric_cea_output('chamber', OF, expansion_ratio)
if __name__ == "__main__":
print('gas static temperature: ', cea.T_static, '[K]')
print('gas dynamic viscosity: ', cea.mu, '[Pa s]')
print('gas Prandtl number: ', cea.Pr, '[-]')
print('ratio of specific heats: ', cea.gamma, '[-]')
print('gas thermal conductivity: ', cea.k, '[W/m/K]')
#print('gas mole fractions: ', cea.mole_fractions)
# liquid properties
liquid_fuel = thermo.Mixture(fuel_composition,
ws=fuel_mass_fraction,
T=fuel_temperature,
P=pre_injection_pressure)
liquid_ox = thermo.Chemical(ox_composition,
T=ox_temperature,
P=pre_injection_pressure)
print('fuel density: ', liquid_fuel.rho, '[kg/m^3]')
print('fuel dynamic visconsity', liquid_fuel.mu, '[Pa s]')
print('fuel specific heat at constant pressure: ', liquid_fuel.Cpl,
'[J/kg/K]')
print('fuel thermal conductivity: ', liquid_fuel.k, '[W/m/K]')
print('oxidiser density: ', liquid_ox.rho, '[kg/m^3]')
print('oxidiser dynamic visconsity', liquid_ox.mu, '[Pa s]')
print('oxidiser specific heat at constant pressure: ', liquid_ox.Cpl,
'[J/kg/K]')
'sparrow_50bar.txt', delimiter='', dtype=None,
skip_header=13) / 1000 # conversion to [m]
massflow = 5.8
film_massflow = 0.5
chamber_pressure = 50e5
mach = 0.2
radius_at_injection = 60e-3
cea = CEA(ethanol90, oxidiser, chamber_pressure)
cea.metric_cea_output('throat', OF, 12)
isnetropic = Isentropic(chamber_pressure, cea.T_static, cea.gamma)
mach = isnetropic.mach(geometry)[::-1]
T_aw_uncooled = isnetropic.adiabatic_wall_temp(mach, geometry, cea.Pr)
coolant = thermo.Mixture(['C2H5OH', 'H2O'], ws=[0.9, 0.1], P=60e5, T=350)
film = FilmCooling(coolant, cea, massflow, film_massflow, chamber_pressure,
geometry[42, 1], geometry)
film.local_conditions(mach)
#print(film.liquid_lenght())
#print(film.nasa_liquid_film(0.3))
#print(film.nasa_gaseous_film(0.2,10,0.4e-3))
T_aw_cooled = film.T_aw(42, 100, mach, T_aw_uncooled, 40, chamber_pressure)
f, axes = plt.subplots(4, 1)
axes[0].plot(geometry[:, 0], geometry[:, 1] * 1000)
axes[0].set_ylabel('contour height [mm]')
axes[1].plot(geometry[:, 0], T_aw_uncooled)
import numpy as np
import thermo
import injectors
from standard_fluid_config import ox_massflow, fuel_massflow
fuel = thermo.Mixture(['c2h5oh', 'h2o'], ws=[0.8, 0.2], T=288, P=7.5e6)
ox = thermo.Mixture(['o2'], [1], T=90, P=6.5e6)
# values form Wolfram Alpha
p_vap_water = 1204 #[Pa]
p_vap_ethanol = 3861 #[Pa]
p_vap_ox = 97.18e3 #[Pa]
p_vap_fuel = fuel.zs[0] * p_vap_ethanol + fuel.zs[
1] * p_vap_water # molar averaged vapor pressure of fuel [Pa]
dp_fuel = fuel.P - p_vap_fuel
dp_ox = ox.P - p_vap_ox
orifice_len = 3e-3
ethanol_bypass = injectors.LiquidInjector(['c2h5oh', 'h2o'], [0.8, 0.2],
fuel.T, fuel.P, orifice_len,
fuel_massflow * 0.1, dp_fuel, 0)
ethanol_bypass.injector()
lox_bypass = injectors.LiquidInjector(['o2'], [1], ox.T, ox.P, orifice_len,
ox_massflow * 0.1, dp_ox, 0)
lox_bypass.injector()
print(ethanol_bypass.mu)
print(ethanol_bypass.diameter * 1000)
# Thermo input values
total_massflow = 0.4964 # [kg/s]
fuel_massflow = total_massflow / (1 + OF)
coolant_massflow = 0.498 #1.96
coolant_composition = ['H2O']
coolant_mass_fraction = [1]
# Film Cooling BETA
mu = 0.05
film_massflow = fuel_massflow * mu / (1 - mu)
isnetropic = film.Isentropic(chamber_pressure, cea.T_static, cea.gamma)
mach = isnetropic.mach(geometry)[::-1]
T_aw_uncooled = isnetropic.adiabatic_wall_temp(mach, geometry, cea.Pr)
coolant = thermo.Mixture(['benzine'], ws=[1], P=chamber_pressure + 10e5, T=273)
film = film.FilmCooling(coolant, cea, total_massflow, film_massflow,
chamber_pressure, geometry[49, 1], geometry)
T_aw_cooled = film.T_aw(film_start=49,
film_end=100,
mach=mach,
T_aw_uncooled=T_aw_uncooled,
n_holes=number_of_channels,
chamber_pressure=chamber_pressure)[::-1]
heat = ht.Heattransfer(coolant_composition, coolant_mass_fraction,
coolant_massflow, total_massflow, fuel, oxidiser, OF,
chamber_pressure, fuel_temperature, fuel_inlet_pressure,
geometry, cooling_channels, thermal_conductivity,
method, T_aw_cooled)
heat.heatflux(geometry)
