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)
thr.T0, thr.P0 = f.total_conditions(thr.T, thr.vel.V, thr.P, cp, gamma) 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
T03, P03 = f.relative_temperature_pressure(T3, P3, Mach3, gamma) # T03 = T3*(1+(gamma-1)/2*Mach3**2) # P03 = P3*(1+(gamma-1)/2*Mach3**2)**(gamma/(gamma-1)) DeltaH_T2 = cp*(T01-T03) # blade geometry at 2 R2tip, R2hub, h2, R2mean, D2mean, A2 = f.blade_geometry(mdot, rho2, V2x, RHT) # rotational velocity Omega2 = U2/R2mean RPM = f.RPM(Omega2) # massflow and characteristics at inlet rho01 = f.static_density(P01, T01, R) # = P01/T01/R rho1 = f.rhox_converge(0.9999*rho01, rho01, T01, mdot, A2, gamma, cp) # iteraciones hasta converger V1 = np.sqrt(2*cp*T01*(1-(rho1/rho01)**(gamma-1))) T1 = T01 - V1**2/2/cp P1 = f.T2P(P01, T1, T01, gamma) # = P01*(T1/T01)**(gamma/(gamma-1)) # isentropic a1, Mach1 = f.sonic(gamma, R, T1, V1) A1 = mdot/rho1/V1 # blade geometry at 1 R1tip, R1hub, h1, R1mean, D1mean, A1 = f.blade_geometry(mdot, rho1, V1, RHT) # blade geometry at 3 ########## NO ENTIENDO NADAAAAA