def solve_geometry(RHT, one, two, thr, mdot, R, gamma, cp):
# def f_geometry(geometry, one, two, thr, mdot, R, gamma, cp):
# blade geometry at 2
f.blade_geometry(mdot, two.rho, two.vel.Vx, RHT, two)
# rotational velocity
two.vel.Omega = two.vel.U/two.geo.Rm
two.vel.RPM = f.RPM(two.vel.Omega)
# massflow and characteristics at inlet
one.rho0 = f.static_density(one.P0, one.T0, R) # = one.P0/one.T0/R
one.rho, one.vel.V, one.geo.A = solve_rhox(0.9999*one.rho0, one.rho0, one.T0, mdot, two.geo.A, gamma, cp) # iteraciones hasta converger
one.vel.Vx = one.vel.V
one.T = one.T0 - one.vel.V**2/2/cp
one.P = f.T2P(one.P0, one.T, one.T0, gamma) # = one.P0*(one.T/one.T0)**(gamma/(gamma-1)) # isentropic
one.vel.a, one.vel.M = f.sonic(gamma, R, one.T, one.vel.V)
# blade geometry at 1
f.blade_geometry(mdot, one.rho, one.vel.V, RHT, one)
# blade geometry at 3
# what
thr.geo.A = mdot/thr.vel.Vx/thr.rho
thr.geo.h = thr.geo.A/np.pi/2/two.geo.Rm
thr.geo.Rt = two.geo.Rm+thr.geo.h/2
thr.geo.Dm = thr.geo.Rt*2 - thr.geo.h
thr.geo.Rm = thr.geo.Dm/2
thr.vel.Omega = thr.vel.U/thr.geo.Rm
thr.vel.RPM = f.RPM(thr.vel.Omega)
DeltaH_T2 = cp*(one.T0-thr.T0) # blade geometry at 2 two.geo.Rt, two.geo.Rh, two.geo.h, two.geo.Rm, two.geo.Dm, A2 = f.blade_geometry(mdot, two.rho, two.vel.Vx, RHT) # rotational velocity two.vel.Omega = two.vel.U/two.geo.Rm two.vel.RPM = f.RPM(two.vel.Omega) # massflow and characteristics at inlet one.rho0 = f.static_density(one.P0, one.T0, R) # = one.P0/one.T0/R one.rho = solve_rhox(0.9999*one.rho0, one.rho0, one.T0, mdot, A2, gamma, cp) # iteraciones hasta converger one.vel.V = np.sqrt(2*cp*one.T0*(1-(one.rho/one.rho0)**(gamma-1))) one.T = one.T0 - one.vel.V**2/2/cp one.P = f.T2P(one.P0, one.T, one.T0, gamma) # = one.P0*(one.T/one.T0)**(gamma/(gamma-1)) # isentropic one.vel.a, one.vel.M = f.sonic(gamma, R, one.T, one.vel.V) one.geo.A = mdot/one.rho/one.vel.V # blade geometry at 1 one.geo.Rt, one.geo.Rh, one.geo.h, one.geo.Rm, one.geo.Dm, one.geo.A = f.blade_geometry(mdot, one.rho, one.vel.V, RHT) # blade geometry at 3 ########## NO ENTIENDO NADAAAAA thr.geo.A = mdot/thr.vel.Vx/thr.rho thr.geo.h = thr.geo.A/np.pi/2/two.geo.Rm thr.geo.Rt = two.geo.Rm+thr.geo.h/2
def f_mach3(Mach3, one, two, thr, stator, rotor, gamma, cp, R, GR, phi,
DeltaH_prod, bounds_angles):
thr.vel.M = Mach3
# using mach, find static pressure
thr.P = f.static_pressure(
thr.P0, gamma, thr.vel.M
) # = thr.P0/(1+(gamma-1)/2*thr.vel.M**2)**(gamma/(gamma-1))
thr.Ts = f.P2T(thr.T0, thr.P, thr.P0,
gamma) # = thr.T0*(thr.P/thr.P0)**((gamma-1)/gamma)
# find intermediate static pressure
two.P = one.P0 * ((GR - 1) * (1 - (thr.P / one.P0)**(
(gamma - 1) / gamma)) + 1)**(gamma /
(gamma - 1)) # GP rp definition
### where does that definition come from? doublecheck GR definition
# isentropic evolution in stator: absolute total temperature is same
two.T0 = one.T0
two.Ts = f.P2T(one.T0, two.P, one.P0,
gamma) # = one.T0*(two.P/one.P0)**((gamma-1)/gamma)
two.vel.Vs = f.isen_velocity(
cp, two.T0, two.Ts) # = np.sqrt(2*cp*(two.T0 - two.Ts))
# assume rotor efficiency
two.T = f.stage_efficiency(
stator.eta, two.T0,
two.Ts) # = two.T0 - stator.eta*(two.T0-two.Ts)
two.vel.V = f.isen_velocity(cp, two.T0,
two.T) # = np.sqrt(2*cp*(two.T0 - two.T))
# density (from static quantities)
two.rho = f.static_density(two.P, two.T, R) # = two.P/two.T/R
# speed of sound and Mach
two.vel.a, two.vel.M = f.sonic(
gamma, R, two.T,
two.vel.V) # = np.sqrt(gamma*R*two.T), = two.vel.V/two.vel.a
# get initial guess for angles
angles_init = np.array([two.alpha, thr.beta])
angles = solve_angles(angles_init, one, two, thr, stator, rotor, gamma,
cp, R, GR, phi, DeltaH_prod, bounds_angles)
two.alpha = angles[0]
thr.beta = angles[1]
two.vel.Vx, two.vel.Vu = f.velocity_projections(two.vel.V, two.alpha)
# assume a loading factor and calculate peripheral speed
two.vel.U = np.sqrt(DeltaH_prod / phi)
# velocity triangle (pithagoras)
two.vel.Wu = two.vel.Vu - two.vel.U
two.vel.Wx = two.vel.Vx
two.vel.W = f.mag(two.vel.Wu, two.vel.Wx)
# relative inlet angle and relative Mach number
two.vel.Mr = two.vel.W / two.vel.a
# relative total quantities at rotor inlet
two.T0r, two.P0r = f.relative_temperature_pressure(
two.T, two.P, two.vel.Mr, gamma)
############ ROTOR #############
# in the rotor, the relative total temperature is constant (se conservan rotalpías)
thr.T0r = two.T0r
# ideal outlet temperature, real outlet temperature
# assuming the expanse to thr.P, calculated with the assumed M3
thr.Ts = f.P2T(thr.T0r, thr.P, two.P0r,
gamma) # = thr.T0r*(thr.P/two.P0r)**((gamma-1)/gamma)
thr.T = f.stage_efficiency(
rotor.eta, thr.T0r,
thr.Ts) # = thr.T0r - rotor.eta*(thr.T0r - thr.Ts)
# velocities
thr.vel.W = f.isen_velocity(cp, thr.T0r,
thr.T) # = np.sqrt(2*cp*(thr.T0r - thr.T))
# speed of sound and relative mach number
thr.vel.a, thr.vel.Mr = f.sonic(gamma, R, thr.T,
thr.vel.W) # = np.sqrt(gamma*R*thr.T)
# velocity projections, axial and tangential
thr.vel.Wx, thr.vel.Wu = f.velocity_projections(thr.vel.W, thr.beta)
# constant radius, constant peripheral speed
thr.vel.U = two.vel.U
# tangential outlet speed
thr.vel.Vu = thr.vel.Wu + thr.vel.U
# V3u_euler = -DeltaH_prod/two.vel.U + two.vel.Vu
# assume axial speed constant
thr.vel.Vx = thr.vel.Wx
thr.vel.V = f.mag(
thr.vel.Vx, thr.vel.Vu) # = np.sqrt(thr.vel.Vx**2 + thr.vel.Vu**2)
Mach3_calculated = thr.vel.V / thr.vel.a
return Mach3_calculated - Mach3
P2 = GR*(P01-P3)+P3 # Siverding rp definition P2 = P01*((GR-1)*(1-(P3/P01)**((gamma-1)/gamma) ) +1)**(gamma/(gamma-1)) # GP rp definition ### where does that definition come from? doublecheck GR definition # isentropic evolution in stator: absolute total temperature is same T02 = T01 T2s = f.P2T(T01, P2, P01, gamma) # = T01*(P2/P01)**((gamma-1)/gamma) V2s = f.isen_velocity(cp, T02, T2s) # = np.sqrt(2*cp*(T02 - T2s)) # assume rotor efficiency T2 = f.stage_efficiency(eta_stator, T02, T2s) # = T02 - eta_stator*(T02-T2s) V2 = f.isen_velocity(cp, T02, T2) # = np.sqrt(2*cp*(T02 - T2)) # density (from static quantities) rho2 = f.static_density(P2,T2,R) # = P2/T2/R # speed of sound and Mach a2, Mach2 = f.sonic(gamma, R, T2, V2) # = np.sqrt(gamma*R*T2), = V2/a2 # check if pressure calculated meets the restriction T02b = T2+V2**2/2/cp ### include this in the check loop P02 = f.T2P(P2, T02, T2, gamma) # = P2*(T02/T2)**(gamma/(gamma-1)) # stator kinetic loss coefficient # check loss inpose ??? ### # Total pressure loss # stator pressure loss coefficient, Total pressure loss down 02 xi_stator, loss_stator, tpl_stator, omega_stator = f.losses(V2, V2s, P01, P02, P2) # = (V2s**2 - V2**2)/V2s**2, = V2**2/V2s**2, = (P01 - P02)/(P01 - P2), = (P01 - P02)/(P02 - P2) ### equation for xi is different in report and excel sheet (corregir)
def converge_mach3(one, two, thr, stator, rotor, gamma, cp, R, GR, psi,
DeltaH_prod):
def f_mach3(Mach3, one, two, thr, stator, rotor, gamma, cp, R, GR, psi,
DeltaH_prod):
thr.vel.M = Mach3
# using mach, find static pressure
thr.P = f.static_pressure(
thr.P0, gamma, thr.vel.M
) # = thr.P0/(1+(gamma-1)/2*thr.vel.M**2)**(gamma/(gamma-1))
thr.Ts = f.P2T(thr.T0, thr.P, thr.P0,
gamma) # = thr.T0*(thr.P/thr.P0)**((gamma-1)/gamma)
# find intermediate static pressure
two.P = one.P0 * ((GR - 1) * (1 - (thr.P / one.P0)**(
(gamma - 1) / gamma)) + 1)**(gamma /
(gamma - 1)) # GP rp definition
### where does that definition come from? doublecheck GR definition
# isentropic evolution in stator: absolute total temperature is same
two.T0 = one.T0
two.Ts = f.P2T(one.T0, two.P, one.P0,
gamma) # = one.T0*(two.P/one.P0)**((gamma-1)/gamma)
two.vel.Vs = f.isen_velocity(
cp, two.T0, two.Ts) # = np.sqrt(2*cp*(two.T0 - two.Ts))
# assume rotor efficiency
two.T = f.stage_efficiency(
stator.eta, two.T0,
two.Ts) # = two.T0 - stator.eta*(two.T0-two.Ts)
two.vel.V = f.isen_velocity(cp, two.T0,
two.T) # = np.sqrt(2*cp*(two.T0 - two.T))
# density (from static quantities)
two.rho = f.static_density(two.P, two.T, R) # = two.P/two.T/R
# speed of sound and Mach
two.vel.a, two.vel.M = f.sonic(
gamma, R, two.T,
two.vel.V) # = np.sqrt(gamma*R*two.T), = two.vel.V/two.vel.a
## ANGLE CONVERGENCE FOR ALPHA2 AND BETA3
solve_angles(one, two, thr, stator, rotor, gamma, cp, R, GR, psi,
DeltaH_prod)
two.vel.Vx, two.vel.Vu = f.velocity_projections(two.vel.V, two.alpha)
# assume a loading factor and calculate peripheral speed
two.vel.U = np.sqrt(DeltaH_prod / psi)
# velocity triangle (pithagoras)
two.vel.Wu = two.vel.Vu - two.vel.U
two.vel.Wx = two.vel.Vx
two.vel.W = f.mag(two.vel.Wu, two.vel.Wx)
# relative inlet angle and relative Mach number
two.vel.Mr = two.vel.W / two.vel.a
# relative total quantities at rotor inlet
two.T0r, two.P0r = f.relative_temperature_pressure(
two.T, two.P, two.vel.Mr, gamma)
############ ROTOR #############
# in the rotor, the relative total temperature is constant (se conservan rotalpías)
thr.T0r = two.T0r
# ideal outlet temperature, real outlet temperature
# assuming the expanse to thr.P, calculated with the assumed M3
thr.Ts = f.P2T(thr.T0r, thr.P, two.P0r,
gamma) # = thr.T0r*(thr.P/two.P0r)**((gamma-1)/gamma)
thr.T = f.stage_efficiency(
rotor.eta, thr.T0r,
thr.Ts) # = thr.T0r - rotor.eta*(thr.T0r - thr.Ts)
# velocities
thr.vel.W = f.isen_velocity(cp, thr.T0r,
thr.T) # = np.sqrt(2*cp*(thr.T0r - thr.T))
# speed of sound and relative mach number
thr.vel.a, thr.vel.Mr = f.sonic(gamma, R, thr.T,
thr.vel.W) # = np.sqrt(gamma*R*thr.T)
# velocity projections, axial and tangential
thr.vel.Wx, thr.vel.Wu = f.velocity_projections(thr.vel.W, thr.beta)
# constant radius, constant peripheral speed
thr.vel.U = two.vel.U
# tangential outlet speed
thr.vel.Vu = thr.vel.Wu + thr.vel.U
# V3u_euler = -DeltaH_prod/two.vel.U + two.vel.Vu
# assume axial speed constant
thr.vel.Vx = thr.vel.Wx
thr.vel.V = f.mag(
thr.vel.Vx, thr.vel.Vu) # = np.sqrt(thr.vel.Vx**2 + thr.vel.Vu**2)
Mach3_calculated = thr.vel.V / thr.vel.a
return Mach3_calculated - Mach3
thr.vel.M = fsolve(f_mach3,
thr.vel.M,
args=(one, two, thr, stator, rotor, gamma, cp, R, GR,
psi, DeltaH_prod))[0]
# speed of sound and relative mach number AT 3
thr.vel.a, thr.vel.Mr = f.sonic(gamma, R, thr.T,
thr.vel.W) # = np.sqrt(gamma*R*thr.T)
# using mach, find static pressure
thr.P = f.static_pressure(
thr.P0, gamma,
thr.vel.M) # = thr.P0/(1+(gamma-1)/2*thr.vel.M**2)**(gamma/(gamma-1))
thr.Ts = f.P2T(thr.T0, thr.P, thr.P0,
gamma) # = thr.T0*(thr.P/thr.P0)**((gamma-1)/gamma)
# find intermediate static pressure
two.P = one.P0 * ((GR - 1) * (1 - (thr.P / one.P0)**(
(gamma - 1) / gamma)) + 1)**(gamma / (gamma - 1)) # GP rp definition
# isentropic evolution in stator: absolute total temperature is same
two.T0 = one.T0
two.Ts = f.P2T(one.T0, two.P, one.P0,
gamma) # = one.T0*(two.P/one.P0)**((gamma-1)/gamma)
two.vel.Vs = f.isen_velocity(cp, two.T0,
two.Ts) # = np.sqrt(2*cp*(two.T0 - two.Ts))
# assume rotor efficiency
two.T = f.stage_efficiency(stator.eta, two.T0,
two.Ts) # = two.T0 - stator.eta*(two.T0-two.Ts)
two.vel.V = f.isen_velocity(cp, two.T0,
two.T) # = np.sqrt(2*cp*(two.T0 - two.T))
# density (from static quantities)
two.rho = f.static_density(two.P, two.T, R) # = two.P/two.T/R
# speed of sound and Mach
two.vel.a, two.vel.M = f.sonic(
gamma, R, two.T,
two.vel.V) # = np.sqrt(gamma*R*two.T), = two.vel.V/two.vel.a
two.P0 = f.T2P(two.P, two.T0, two.T,
gamma) # = two.P*(two.T0/two.T)**(gamma/(gamma-1))
# assume an two.alpha and project velocities
two.vel.Vx, two.vel.Vu = f.velocity_projections(two.vel.V, two.alpha)
if two.vel.Vx == 0:
two.vel.Vx = 0.00000001
# assume a loading factor and calculate peripheral speed
two.vel.U = np.sqrt(DeltaH_prod / psi)
# velocity triangle (pithagoras)
two.vel.Wu = two.vel.Vu - two.vel.U
two.vel.Wx = two.vel.Vx
two.vel.W = f.mag(two.vel.Wu, two.vel.Wx)
# relative inlet angle and relative Mach number
two.beta = np.arctan(two.vel.Wu / two.vel.Vx)
two.vel.Mr = two.vel.W / two.vel.a
# relative total quantities at rotor inlet
# (add relative speed to static conditions)
# two.T0r = two.T*(1 + two.vel.Mr**2*(gamma-1)/2) # total temperature is conserved
# two.P0r = two.P*(1 + (gamma-1)/2*two.vel.Mr**2)**(gamma/(gamma-1))
two.T0r, two.P0r = f.relative_temperature_pressure(two.T, two.P,
two.vel.Mr, gamma)
############ ROTOR #############
# in the rotor, the relative total temperature is constant (se conservan rotalpías)
thr.T0r = two.T0r
# ideal outlet temperature, real outlet temperature
# assuming the expanse to thr.P, calculated with the assumed M3
thr.Ts = f.P2T(thr.T0r, thr.P, two.P0r,
gamma) # = thr.T0r*(thr.P/two.P0r)**((gamma-1)/gamma)
thr.T = f.stage_efficiency(
rotor.eta, thr.T0r, thr.Ts) # = thr.T0r - rotor.eta*(thr.T0r - thr.Ts)
# velocities
thr.vel.W = f.isen_velocity(cp, thr.T0r,
thr.T) # = np.sqrt(2*cp*(thr.T0r - thr.T))
thr.vel.Ws = f.isen_velocity(cp, thr.T0r,
thr.Ts) # = np.sqrt(2*cp*(thr.T0r - thr.Ts))
# density
thr.rho = f.static_density(thr.P, thr.T, R) # = thr.P/thr.T/R
# speed of sound and relative mach number
thr.vel.a, thr.vel.Mr = f.sonic(gamma, R, thr.T,
thr.vel.W) # = np.sqrt(gamma*R*thr.T)
# total absolute pressure
thr.P0r = f.T2P(thr.P, thr.T0r, thr.T,
gamma) # = thr.P*(thr.T0r/thr.T)**(gamma/(gamma-1))
# assume a value for thr.beta
# velocity projections, axial and tangential
thr.vel.Wx, thr.vel.Wu = f.velocity_projections(thr.vel.W, thr.beta)
# constant radius, constant peripheral speed
thr.vel.U = two.vel.U
# tangential outlet speed
thr.vel.Vu = thr.vel.Wu + thr.vel.U
# V3u_euler = -DeltaH_prod/two.vel.U + two.vel.Vu
# assume axial speed constant
thr.vel.Vx = thr.vel.Wx
thr.vel.V = f.mag(thr.vel.Vx,
thr.vel.Vu) # = np.sqrt(thr.vel.Vx**2 + thr.vel.Vu**2)
thr.alpha = np.arctan(thr.vel.Vu / thr.vel.Vx)
