def __init__(self,
T_stag_in,
p_stag_in,
G_in,
G_fuel_in,
g_cool,
G_c1_in,
T_cool,
cool_fluid: IdealGas = Air(),
work_fluid: IdealGas = NaturalGasCombustionProducts(),
precision=0.0001):
ModelSingleWorkFluid.__init__(self)
self.T_stag_in = T_stag_in
self.p_stag_in = p_stag_in
self.G_in = G_in
self.G_fuel_in = G_fuel_in
self.g_cool = g_cool
self.G_c1_in = G_c1_in
self.T_cool = T_cool
self.cool_fluid = cool_fluid
self.work_fluid = work_fluid
self.precision = precision
self.G_cool = None
self.fuel_content_in = None
self.fuel_content_out = None
self.alpha_in = None
self.alpha_out = None
def compute_cycle(eta_stag_p_c=0.88, eta_stag_p_ct=9.9, eta_stag_p_pt=0.9):
precision = 0.0001
atm = Atmosphere()
inlet = Inlet()
comp = Compressor(pi_c=17, eta_stag_p=eta_stag_p_c, precision=precision)
sink = Sink(g_cooling=0, g_outflow=0.03)
comb_chamber = CombustionChamber(T_gas=1523,
precision=precision,
alpha_out_init=2,
fuel=NaturalGas(),
T_fuel=320,
delta_p_fuel=5e5)
comp_turbine = Turbine(eta_stag_p=eta_stag_p_ct,
eta_m=0.99,
precision=precision)
source = Source(g_return=0)
power_turbine = Turbine(eta_stag_p=eta_stag_p_pt,
eta_m=0.99,
eta_r=0.99,
precision=precision,
p_stag_out_init=1e5)
outlet = Outlet()
load = Load(power=16e6)
comp_turb_zero_load = Load(power=0)
power_turb_zero_load = Load(power=0)
solver = NetworkSolver(unit_arr=[
atm, inlet, comp, sink, comb_chamber, comp_turbine, source,
power_turbine, outlet, load, comp_turb_zero_load, power_turb_zero_load
],
relax_coef=1,
precision=precision,
max_iter_number=100,
cold_work_fluid=Air(),
hot_work_fluid=NaturalGasCombustionProducts())
solver.create_gas_dynamic_connection(atm, inlet)
solver.create_gas_dynamic_connection(inlet, comp)
solver.create_gas_dynamic_connection(comp, sink)
solver.create_gas_dynamic_connection(sink, comb_chamber)
solver.create_gas_dynamic_connection(comb_chamber, comp_turbine)
solver.create_gas_dynamic_connection(comp_turbine, source)
solver.create_gas_dynamic_connection(source, power_turbine)
solver.create_gas_dynamic_connection(power_turbine, outlet)
solver.create_static_gas_dynamic_connection(outlet, atm)
solver.create_mechanical_connection(comp_turbine, comp,
comp_turb_zero_load)
solver.create_mechanical_connection(power_turbine, load,
power_turb_zero_load)
solver.solve()
G_air = load.power / power_turbine.gen_labour1
G_comp_turb = G_air * comp_turbine.g_in
G_power_turb = G_air * power_turbine.g_in
G_fuel = G_air * comb_chamber.g_fuel_prime * comb_chamber.g_in
eta_e = power_turbine.gen_labour1 / (comb_chamber.work_fluid_out.Q_n *
comb_chamber.g_fuel_prime *
comb_chamber.g_in)
return solver, G_air, G_comp_turb, G_power_turb, G_fuel, eta_e
def __init__(
self,
characteristics: Characteristics,
T_stag_in,
p_stag_in,
pi_c_stag_rel,
n_norm_rel,
T_stag_in_nom,
p_stag_in_nom,
G_in_nom,
eta_c_stag_nom,
n_nom,
pi_c_stag_nom,
G_fuel_in=0,
p_a=1e5,
T_a=288,
sigma_in=0.99,
work_fluid: IdealGas = Air(),
precision=0.0001,
):
ModelSingleWorkFluid.__init__(self)
self.characteristics = characteristics
self.T_stag_in = T_stag_in
self.p_stag_in = p_stag_in
self.pi_c_stag_rel = pi_c_stag_rel
self.n_norm_rel = n_norm_rel
self.T_stag_in_nom = T_stag_in_nom
self.p_stag_in_nom = p_stag_in_nom
self.G_in_nom = G_in_nom
self.eta_c_stag_nom = eta_c_stag_nom
self.n_nom = n_nom
self.pi_c_stag_nom = pi_c_stag_nom
self.G_fuel_in = G_fuel_in
self.p_a = p_a
self.T_a = T_a
self.sigma_in = sigma_in
self.work_fluid = work_fluid
self.precision = precision
self.n_norm_nom = None
self.G_in_norm_nom = None
self.G_in_norm_rel = None
self.G_in_norm = None
self.n_norm = None
self.n = None
self.eta_c_stag_rel = None
self.pi_c_stag = None
self.eta_c_stag = None
self.ad_proc_res = None
self.H_stag = None
self.c_p_av_old = None
self.k_av_old = None
self.k_av = None
self.k_res = None
self.L = None
self.T_stag_out_ad = None
self.N = None
def setUp(self):
stage_num = 12
self.H_t_rel_arr = QuadraticBezier(0.32,
0.33,
stage_num,
angle1=np.radians(10),
angle2=np.radians(10)).get_array()
self.eta_ad_stag_arr = QuadraticBezier(
0.85,
0.86,
stage_num,
angle1=np.radians(10),
angle2=np.radians(10)).get_array()
self.c1_a_rel_arr = QuadraticBezier(0.45,
0.51,
stage_num,
angle1=np.radians(10),
angle2=np.radians(-1)).get_array()
self.h_rk_rel_dist = lambda z: interp1d([0, stage_num - 1], [2.5, 1.6]
)(z).__float__()
self.h_na_rel_dist = lambda z: interp1d([0, stage_num - 1], [3.2, 1.8]
)(z).__float__()
self.delta_a_rk_rel = lambda z: interp1d([0, stage_num - 1],
[0.3, 0.5])(z).__float__()
self.delta_a_na_rel = lambda z: interp1d([0, stage_num - 1],
[0.3, 0.5])(z).__float__()
self.compressor = Compressor(
work_fluid=Air(),
stage_num=stage_num,
const_diam_par_arr=[0.5 for _ in range(stage_num)],
p0_stag=1e5,
T0_stag=288,
G=40,
n=11000,
H_t_rel_arr=self.H_t_rel_arr,
eta_ad_stag_arr=self.eta_ad_stag_arr,
R_av_arr=QuadraticBezier.get_array_from_dist(
lambda z: 0.5, stage_num),
k_h_arr=QuadraticBezier.get_array_from_dist(
lambda z: 0.98, stage_num),
c1_a_rel_arr=self.c1_a_rel_arr,
h_rk_rel_arr=QuadraticBezier.get_array_from_dist(
self.h_rk_rel_dist, stage_num),
h_na_rel_arr=QuadraticBezier.get_array_from_dist(
self.h_na_rel_dist, stage_num),
delta_a_rk_rel_arr=QuadraticBezier.get_array_from_dist(
self.delta_a_rk_rel, stage_num),
delta_a_na_rel_arr=QuadraticBezier.get_array_from_dist(
self.delta_a_na_rel, stage_num),
d1_in_rel1=0.5,
zeta_inlet=0.04,
zeta_outlet=0.35,
c11_init=250,
)
self.compressor.compute()
def __init__(self, unit_arr: typing.List[Unit], relax_coef=1, precision=0.01, max_iter_number=50,
cold_work_fluid: IdealGas=Air(), hot_work_fluid: IdealGas=KeroseneCombustionProducts()):
self._connection_arr: typing.List[ConnectionSet] = []
self._unit_arr = unit_arr
self.cold_work_fluid = cold_work_fluid
self.hot_work_fluid = hot_work_fluid
self.relax_coef = relax_coef
self.precision = precision
self.max_iter_number = max_iter_number
self._iter_number = 0
self._residual_arr = []
def setUp(self):
self.comb_geom = CombustionChamberGeom(work_fluid_in=Air(),
Q_n=48e6,
sigma_d=0.998,
sigma_front=0.998,
n_pipe=12,
G_in=45,
p_stag_in=15e5,
T_stag_in=550,
F_in=np.pi * 0.5**2 / 4,
D_d_av=0.5,
G_fuel_in=0,
G_fuel=0.9,
alpha_sum=3.5,
alpha1=1.1,
c_d=60,
c1=12,
H=4.5e6,
l1_rel=0.6,
eta_burn=0.99)
self.comb_geom.compute()
def __init__(self,
g_fuel,
G_c1_in,
T_stag_in,
p_stag_in,
G_in,
G_fuel_in,
eta_comb,
sigma_comb,
T_fuel=300,
fuel: Fuel = NaturalGas(),
delta_p_fuel=5e5,
work_fluid_in: IdealGas = Air(),
work_fluid_out: IdealGas = NaturalGasCombustionProducts(),
precision=0.0001):
ModelMultipleWorkFluid.__init__(self)
self.g_fuel = g_fuel
self.G_c1_in = G_c1_in
self.G_fuel_in = G_fuel_in
self.G_in = G_in
self.T_stag_in = T_stag_in
self.p_stag_in = p_stag_in
self.eta_comb = eta_comb
self.sigma_comb = sigma_comb
self.T_fuel = T_fuel
self.fuel = fuel
self.delta_p_fuel = delta_p_fuel
self.work_fluid_in = work_fluid_in
self.work_fluid_out = work_fluid_out
self.precision = precision
self.G_fuel = None
self.fuel_content_out = None
self.fuel_content_in = None
self.alpha_in = None
self.alpha_out = None
self.i_stag_in = None
self.i_stag_out = None
self.p_fuel = None
self.i_fuel = None
def get_compressor(p0_stag, T0_stag, G, n, stage_num, H_t_rel1, H_t_rel_delta,
c1_a_rel1, c1_a_rel_delta) -> CompAvLine:
H_t_rel_dist = QuadraticBezier(H_t_rel1,
H_t_rel1 - H_t_rel_delta,
stage_num=stage_num,
angle1=np.radians(10),
angle2=np.radians(10))
eta_rel_dist = QuadraticBezier(0.86,
0.86,
stage_num=stage_num,
angle1=np.radians(3),
angle2=np.radians(3))
c1_a_rel_dist = QuadraticBezier(c1_a_rel1,
c1_a_rel1 - c1_a_rel_delta,
stage_num=stage_num,
angle1=np.radians(10),
angle2=np.radians(10))
comp = CompAvLine(work_fluid=Air(),
stage_num=stage_num,
const_diam_par_arr=[0.5 for _ in range(stage_num)],
p0_stag=p0_stag,
T0_stag=T0_stag,
G=G,
n=n,
H_t_rel_arr=H_t_rel_dist.get_array(),
eta_ad_stag_arr=eta_rel_dist.get_array(),
R_av_arr=[0.5 for _ in range(stage_num)],
k_h_arr=[1.0 for _ in range(stage_num)],
c1_a_rel_arr=c1_a_rel_dist.get_array(),
h_rk_rel_arr=[3.5 for _ in range(stage_num)],
h_na_rel_arr=[3.5 for _ in range(stage_num)],
delta_a_rk_rel_arr=[0.4 for _ in range(stage_num)],
delta_a_na_rel_arr=[0.4 for _ in range(stage_num)],
d1_in_rel1=0.5,
zeta_inlet=0.04,
zeta_outlet=0.03,
c11_init=200,
precision=0.0001)
comp.compute()
return comp
def setUp(self):
self.atmosphere = Atmosphere()
self.inlet = Inlet()
self.compressor = Compressor(17, precision=0.001)
self.sink = Sink(g_cooling=0.05, g_outflow=0.01)
self.comb_chamber = CombustionChamber(1450,
alpha_out_init=2.7,
precision=0.001)
self.comb_chamber_inter_up = CombustionChamber(1300,
alpha_out_init=2.7,
precision=0.001)
self.comb_chamber_inter_down = CombustionChamber(1300,
alpha_out_init=2.7,
precision=0.001,
p_stag_out_init=4e5)
self.source = Source(g_return=0.05)
self.turbine_low_pres_power = Turbine(p_stag_out_init=1e5)
self.turbine_comp_up = Turbine()
self.outlet = Outlet()
self.N_gen = 10e6
self.eta_gen = 0.97
self.load = Load(self.N_gen / self.eta_gen)
self.zero_load1 = Load(0)
self.zero_load2 = Load(0)
self.solver = NetworkSolver(
[
self.atmosphere, self.outlet, self.turbine_comp_up, self.sink,
self.turbine_low_pres_power, self.source, self.inlet,
self.comb_chamber, self.compressor, self.load, self.zero_load1,
self.zero_load2
],
cold_work_fluid=Air(),
hot_work_fluid=NaturalGasCombustionProducts())
self.solver.create_gas_dynamic_connection(self.atmosphere, self.inlet)
self.solver.create_gas_dynamic_connection(self.inlet, self.compressor)
self.solver.create_gas_dynamic_connection(self.compressor, self.sink)
self.solver.create_gas_dynamic_connection(self.sink, self.comb_chamber)
self.solver.create_gas_dynamic_connection(self.comb_chamber,
self.turbine_comp_up)
self.solver.create_gas_dynamic_connection(self.turbine_comp_up,
self.source)
self.solver.create_gas_dynamic_connection(self.source,
self.turbine_low_pres_power)
self.solver.create_gas_dynamic_connection(self.turbine_low_pres_power,
self.outlet)
self.solver.create_static_gas_dynamic_connection(
self.outlet, self.atmosphere)
self.solver.create_mechanical_connection(self.turbine_low_pres_power,
self.load, self.zero_load1)
self.solver.create_mechanical_connection(self.turbine_comp_up,
self.compressor,
self.zero_load2)
self.solver.solve()
self.N_e_specific = self.load.consumable_labour
self.G_air = self.load.power / self.N_e_specific
self.G_fuel = self.comb_chamber.g_fuel_prime * self.comb_chamber.g_in * self.G_air
self.c_p_nat_gas_av = 2.3e3
self.k_nat_gas_av = 1.31
self.press_in_gas_comp = 1.3e6
self.T_in_gas_comp = 288
self.eta_ad_gas_comp = 0.82
self.eta_el_eng = 0.95
self.mass_rate_gas_comp = self.G_fuel
self.press_out_gas_comp = self.compressor.p_stag_out + 0.5e6
self.pi_gas_comp = self.press_out_gas_comp / self.press_in_gas_comp
self.rho_gas_comp = 6.9867 + (10.587 - 6.9867) / (1.5e6 - 1e6) * (
self.press_in_gas_comp - 1e6)
self.vol_rate_gas_comp = self.mass_rate_gas_comp / self.rho_gas_comp * 60
self.T_out_gas_comp = self.T_in_gas_comp * (1 + (self.pi_gas_comp**(
(self.k_nat_gas_av - 1) / self.k_nat_gas_av) - 1) /
self.eta_ad_gas_comp)
self.L_e_gas_comp = self.c_p_nat_gas_av * (self.T_out_gas_comp -
self.T_in_gas_comp)
self.N_gas_comp = self.L_e_gas_comp / (self.mass_rate_gas_comp *
self.eta_el_eng)
def setUp(self):
self.turbine = Turbine(TurbineType.WORK,
T_g_stag=1450,
p_g_stag=400e3,
G_turbine=25,
work_fluid=KeroseneCombustionProducts(),
G_fuel=2.5,
l1_D1_ratio=0.25,
n=15e3,
T_t_stag_cycle=1050,
stage_number=2,
eta_t_stag_cycle=0.91,
k_n=6.8,
eta_m=0.99,
auto_compute_heat_drop=False,
precise_heat_drop=False,
auto_set_rho=False,
rho_list=[0.4, 0.20],
H0_list=[235e3, 200e3],
alpha11=np.radians([17])[0],
gamma_av=np.radians([4])[0],
gamma_sum=np.radians([10])[0])
self.turbine.compute_geometry()
self.turbine.compute_stages_gas_dynamics()
self.turbine.compute_integrate_turbine_parameters()
self.turbine_profiler = TurbineProfiler(turbine=self.turbine,
p_in_stag=lambda r: self.turbine[0].p0_stag,
T_in_stag=lambda r: self.turbine[0].T0_stag,
c_in=lambda r: 90,
alpha_in=lambda r: np.radians([90])[0],
center=True)
self.turbine_profiler[0].profiling_type = ProfilingType.ConstantAngle
self.turbine_profiler[0].gamma1_k_rel_rk = lambda r_rel: 0.5
self.turbine_profiler[1].profiling_type = ProfilingType.ConstantAngle
self.turbine_profiler[1].auto_sections_par = False
self.turbine_profiler[1].rk_sections[0].gamma1_s = np.radians([15])[0]
self.turbine_profiler[1].rk_sections[0].gamma1_k = np.radians([7])[0]
self.turbine_profiler.compute_stage_profiles()
stage_prof = self.turbine_profiler[0]
lam_blade_arr = np.array([17, 19, 22, 24, 27, 29])
T_wall_arr = np.array([200, 600, 700, 800, 900, 1200]) + 273
lam_blade_int = interp1d(T_wall_arr, lam_blade_arr, bounds_error=False, fill_value='extrapolate')
x_hole_rel = [-0.8, -0.5, -0.15, 0.1, 0.35, 0.6]
self.theta = get_theta(0.5 * stage_prof.D1_in, 0.5 * stage_prof.D1_out, 0.5, 1.12)
self.T_gas_stag = get_T_gas(self.theta, 650, self.turbine[0].T0_stag)
self.G_cool0 = 0.018
self.g_cool0 = get_g_cool(self.theta, 2 * self.G_cool0 / (stage_prof.D1_out - stage_prof.D1_in))
self.film_blade = FilmBladeCooler(sections=stage_prof.sa_sections,
channel_width=0.001,
wall_thickness=0.001,
D_in=stage_prof.D1_in,
D_out=stage_prof.D1_out,
T_wall_out_av_init=1123,
lam_blade=lambda T: lam_blade_int(T).__float__(),
x_hole_rel=x_hole_rel,
hole_num=[20 for _ in x_hole_rel],
d_hole=[0.5e-3 for _ in x_hole_rel],
phi_hole=[0.9 for _ in x_hole_rel],
mu_hole=[0.86 for _ in x_hole_rel],
T_gas_stag=self.T_gas_stag,
p_gas_stag=stage_prof.p0_stag,
c_p_gas_av=stage_prof.c_p,
lam_gas_in=stage_prof.lam_c0,
lam_gas_out=stage_prof.lam_c1,
work_fluid=type(self.turbine.work_fluid)(),
T_cool0=650,
p_cool_stag0=self.turbine.p_g_stag + 20e3,
g_cool0=self.g_cool0,
cool_fluid=Air())
def setUp(self):
self.bs = BladeSection(angle1=np.radians([90])[0],
angle2=np.radians([21])[0],
delta1=np.radians([2])[0],
delta2=np.radians([2])[0],
b_a=0.07,
r1=0.01 / 2,
convex='left',
pnt_count=30,
s2=0.0003)
self.bs.compute_profile()
lam_blade_arr = np.array([19, 22, 24, 27])
T_wall_arr = np.array([600, 700, 800, 900]) + 273
lam_blade_int = interp1d(T_wall_arr, lam_blade_arr, bounds_error=False, fill_value='extrapolate')
self.conv_cooler = SectorCooler(section=self.bs,
height=67.6e-3,
T_gas_stag=1223,
G_gas=439,
D_av=0.6476,
wall_thickness=1.8e-3,
T_wall_av=980,
T_cool_fluid0=600,
G_cool=0.144,
lam_blade=lambda T: lam_blade_int(T).__float__(),
cool_fluid=Air(),
work_fluid=KeroseneCombustionProducts(),
node_num=250,
channel_width=0.001
)
mu_gas, lam_gas, Re_gas, Nu_gas, alpha_gas_av = GasBladeHeatExchange.get_alpha_gas_av(self.conv_cooler.section,
self.conv_cooler.height,
self.conv_cooler.T_gas_stag,
self.conv_cooler.G_gas,
self.conv_cooler.D_av,
self.conv_cooler.work_fluid)
self.ave_param = DeflectorAverageParamCalculator(self.conv_cooler.section,
self.conv_cooler.height,
self.conv_cooler.D_av,
self.conv_cooler.wall_thickness,
1023,
self.conv_cooler.T_cool_fluid0,
self.conv_cooler.T_gas_stag,
alpha_gas_av,
self.conv_cooler.G_cool,
self.conv_cooler.lam_blade,
self.conv_cooler.cool_fluid
)
self.x_hole1 = [-0.06, -0.04, -0.015, 0, 0.008, 0.015, 0.04]
self.film1 = FilmCalculator(x_hole=self.x_hole1,
hole_num=[15 for _ in self.x_hole1],
d_hole=[0.001 for _ in self.x_hole1],
phi_hole=[0.9 for _ in self.x_hole1],
mu_hole=[0.85 for _ in self.x_hole1],
T_gas_stag=self.conv_cooler.T_gas_stag,
p_gas_stag=9.5e5,
v_gas=lambda x: 100,
c_p_gas_av=1150,
work_fluid=KeroseneCombustionProducts(),
alpha_gas=lambda x: 4500,
T_cool=lambda x: 650,
G_cool0=0.25,
p_cool_stag0=10e5,
c_p_cool_av=1100,
cool_fluid=Air(),
height=0.03)
self.x_hole2 = [-0.015, 0.025]
self.film2 = FilmCalculator(x_hole=self.x_hole2,
hole_num=[15 for _ in self.x_hole2],
d_hole=[0.001 for _ in self.x_hole2],
phi_hole=[0.9 for _ in self.x_hole2],
mu_hole=[0.85 for _ in self.x_hole2],
T_gas_stag=self.conv_cooler.T_gas_stag,
p_gas_stag=9.5e5,
v_gas=lambda x: 100,
c_p_gas_av=1150,
work_fluid=KeroseneCombustionProducts(),
alpha_gas=lambda x: 4500,
T_cool=lambda x: 650,
G_cool0=0.25,
p_cool_stag0=10e5,
c_p_cool_av=1100,
cool_fluid=Air(),
height=0.03)
self.x_hole_rel = [-0.8, -0.6, -0.2, 0.2, 0.4, 0.7]
self.film_cooler = FilmSectorCooler(section=self.bs,
height=self.conv_cooler.height,
channel_width=1e-3,
wall_thickness=self.conv_cooler.wall_thickness,
D_av=self.conv_cooler.D_av,
lam_blade=lambda T: lam_blade_int(T).__float__(),
T_wall_av=1000,
x_hole_rel=self.x_hole_rel,
hole_num=[15 for _ in self.x_hole_rel],
d_hole=[1.5e-3 for _ in self.x_hole_rel],
phi_hole=[0.9 for _ in self.x_hole_rel],
mu_hole=[0.85 for _ in self.x_hole_rel],
T_gas_stag=self.conv_cooler.T_gas_stag,
p_gas_stag=9.5e5,
G_gas=self.conv_cooler.G_gas,
c_p_gas_av=1150,
lam_gas_in=0.1,
lam_gas_out=0.2,
work_fluid=KeroseneCombustionProducts(),
T_cool0=self.conv_cooler.T_cool_fluid0,
p_cool_stag0=10e5,
G_cool0=self.conv_cooler.G_cool,
c_p_cool_av=1100,
cool_fluid=Air(),
node_num=250,
g_cool0_s=0.6)
def setUp(self):
self.comp_turb_2st = Turbine(TurbineType.WORK,
T_g_stag=1400,
p_g_stag=5.5e5,
G_turbine=25,
G_fuel=1,
work_fluid=KeroseneCombustionProducts(),
alpha_air=2.87,
l1_D1_ratio=0.25,
n=15e3,
T_t_stag_cycle=1200,
stage_number=2,
eta_t_stag_cycle=0.91,
k_n=6.8,
eta_m=0.99,
auto_compute_heat_drop=True,
auto_set_rho=True,
precise_heat_drop=False,
H01_init=150e3,
c21_init=250,
alpha11=np.radians([17])[0],
gamma_av=np.radians([4])[0],
gamma_sum=np.radians([10])[0])
self.comp_turb_2st.geom[0].g_cool = 0.004
self.comp_turb_2st.geom[1].g_cool = 0.003
self.comp_turb_2st.compute_geometry()
self.comp_turb_2st.compute_stages_gas_dynamics()
self.comp_turb_2st.compute_integrate_turbine_parameters()
self.turb_profiler = TurbineProfiler(
turbine=self.comp_turb_2st,
p_in_stag=lambda r: self.comp_turb_2st[0].p0_stag,
T_in_stag=lambda r: self.comp_turb_2st[0].T0_stag,
c_in=lambda r: 100,
alpha_in=lambda r: np.radians([90])[0],
section_num=3,
center=True
)
self.turb_profiler[0].profiling_type = ProfilingType.ConstantAngle
self.turb_profiler[1].profiling_type = ProfilingType.ConstantAngle
self.turb_profiler.compute_stage_profiles()
x_hole_rel = [-0.5, -0.25, 0., 0.2, 0.6]
G_cool0 = 0.2
g_cool0 = G_cool0 * 2 / (self.turb_profiler[0].D1_out - self.turb_profiler[0].D1_in)
self.cooler = get_sa_cooler(
self.turb_profiler[0],
channel_width=0.001,
wall_thickness=0.001,
T_wall_out_av_init=1000,
lam_blade=lambda T: 24,
x_hole_rel=x_hole_rel,
hole_num=[35 for _ in x_hole_rel],
d_hole=[0.5e-3 for _ in x_hole_rel],
phi_hole=[0.98 for _ in x_hole_rel],
mu_hole=[0.95 for _ in x_hole_rel],
work_fluid=KeroseneCombustionProducts(),
T_cool0=650,
p_cool_stag0=0.99 * self.comp_turb_2st[0].p0_stag,
g_cool0=lambda r: g_cool0,
cool_fluid=Air(),
cover_thickness=0,
)
def __init__(self,
T0_stag,
p0_stag,
T0_stag_ad_t,
G_stage_in,
G_turbine,
G_fuel,
work_fluid: IdealGas,
rho,
phi,
psi,
l1,
l2,
D1,
D2,
delta_r_rk,
n,
epsilon,
g_lk,
g_ld,
g_lb,
g_cool,
T_cool=700,
precision=0.001,
cool_fluid: IdealGas = Air(),
**kwargs):
"""
:param T0_stag:
:param p0_stag:
:param T0_stag_ad_t: Температура на входе в ступень при адиабатическом процессе в турбине.
:param G_stage_in: расход газа на входе в ступень
:param G_turbine: расход газа через СА первой ступени
:param G_fuel: расход топлива по тракту до турбины
:param work_fluid:
:param rho:
:param phi:
:param psi:
:param l1:
:param l2:
:param D1:
:param D2:
:param delta_r_rk:
:param n:
:param epsilon: Степень парциальности. Необходима для вычисления затрат на трение и вентиляцию
:param g_lk: относительный расход утечек в концевых лабиринтах
:param g_ld: относительный расход перетечек в лабиринтных уплотнениях сопловых диафрагм
:param g_lb: относительный расход перетечек поверх бондажа рабочих лопаток
:param g_cool: Отношение расхода охлаждающего воздуха к расходу газа через СА первой ступени.
:param T_cool: температура охлаждающего воздуха.
:param precision: точность.
:param cool_fluid: рабочее тело для охлажденияю
:param kwargs: H0 - теплоперепад на ступени, p2_stag - полное давление на выходе из ступени,
L_t - работа ступени, eta_t0 - КПД ступени в первом приближении.
"""
set_logging()
self.T0_stag = T0_stag
self.p0_stag = p0_stag
self.T0_stag_ad_t = T0_stag_ad_t
self.G_stage_in = G_stage_in
self.G_turbine = G_turbine
self.work_fluid = work_fluid
self.work_fluid_ad = type(work_fluid)()
self.work_fluid_stag_ad = type(work_fluid)()
self.G_fuel = G_fuel
self.phi = phi
self.psi = psi
self.l1 = l1
self.l2 = l2
self.D1 = D1
self.D2 = D2
self.rho = rho
self.n = n
self.delta_r_rk = delta_r_rk
self.epsilon = epsilon
self.g_lk = g_lk
self.g_ld = g_ld
self.g_lb = g_lb
self.g_cool = g_cool
self.T_cool = T_cool
self.precision = precision
self.cool_fluid = cool_fluid
(self.stage_type, self.H0, self.p2_stag_pre, self.L_t_pre,
self._eta_t0) = self._get_turbine_type_specific_params(**kwargs)
self.k_res = None
self.L_t_res = None
self.p2_stag_res = None
def __init__(self,
section: BladeSection,
height=None,
wall_thickness=None,
T_cool_fluid0=None,
T_wall_av=None,
alpha_cool: typing.Callable[[float, float], float] = None,
T_out_stag: typing.Callable[[float], float] = None,
alpha_out: typing.Callable[[float], float] = None,
G_cool: typing.Callable[[float], float] = None,
lam_blade: typing.Callable[[float], float] = None,
cool_fluid: IdealGas = Air(),
cover_thickness=0.15e-3,
lam_cover=2,
node_num: int = 500):
"""
:param section: BladeSection. \n
Сечение рассчитываемого участка лопатки.
:param height: float. \n
Высота рассчитываемого участка лопакти.
:param wall_thickness: float. \n
Толщина стенки.
:param T_cool_fluid0: float. \n
Температура охраждающего тела на входе в лопатку.
:param T_wall_av: float. \n
Средняя температура стенки лопатки.
:param alpha_cool: callable. \n
Зависимость коэффициента теплоотдачи от охлаждающего тела к стенке лопатки от координаты вдоль
обвода профиля и температуры охлаждающего тела.
:param T_out_stag: callable. \n
Распределение температуры обтекающей лопатку среды вдоль обвода профиля.
:param alpha_out: callable. \n
Распределение коэффициента теплоотдачи от обтекающей лопатку среды к лопатке вдоль обвода профиля.
:param G_cool: callable. \n
Распределение расхода охлаждающего тела к лопатке вдоль обвода профиля.
:param lam_blade: callable. \n
Тепопроводность материала лопатки в зависимости от температуры.
:param cool_fluid: IdealGas. \n
Охлаждающее тело.
:param cover_thickness: float, optional. \n
Толщина защитного покрытия.
:param lam_cover: float, optional. \n
Теплопроводность защитного покрытия.
:param node_num: int, optional. \n
Число узлов на интервале решения уравнения теплового баланса.
"""
self.section = section
self.height = height
self.wall_thickness = wall_thickness
self.T_cool_fluid0 = T_cool_fluid0
self.alpha_cool = alpha_cool
self.T_wall_av = T_wall_av
self.T_out_stag = T_out_stag
self.alpha_out = alpha_out
self.G_cool = G_cool
self.lam_blade = lam_blade
self.cool_fluid = cool_fluid
self.node_num = node_num
self.cover_thickness = cover_thickness
self.lam_cover = lam_cover
self.T_cool_fluid_s_arr = None
self.T_cool_fluid_k_arr = None
self.T_cool_fluid_arr = None
self._T_cool_int = None
self._T_wall_int = None
self.alpha_cool_fluid_arr = None
self.alpha_cool_fluid_k_arr = None
self.alpha_out_arr = None
self.alpha_gas_k_arr = None
self.T_wall_arr = None
self.x_s_arr = None
self.x_k_arr = None
self.x_arr = None
self.M_s, self.N_s = None, None
self.M_k, self.N_k = None, None
self.T_wall_s_arr = None
self.T_wall_k_arr = None
def __init__(
self,
x_hole: typing.List[float] = None,
hole_num: typing.List[float] = None,
d_hole: typing.List[float] = None,
phi_hole: typing.List[float] = None,
mu_hole: typing.List[float] = None,
T_gas_stag=None,
p_gas_stag=None,
v_gas: typing.Callable[[float], float] = None,
c_p_gas_av=None,
work_fluid: IdealGas = KeroseneCombustionProducts(),
alpha_gas: typing.Callable[[float], float] = None,
T_cool: typing.Callable[[float], float] = None,
G_cool0=None,
p_cool_stag0=None,
c_p_cool_av=None,
cool_fluid: IdealGas = Air(),
height=None,
g_cool0_s=0.5,
):
"""
:param x_hole: Координаты рядов отверстий.
:param hole_num: Число отверстий в рядах.
:param d_hole: Диаметры отверстий в рядах.
:param phi_hole: Коэффициенты скорости в рядах отверстий.
:param mu_hole: Коэффициенты расхода в рядах отверстий.
:param T_gas_stag: Температура торможения газа.
:param p_gas_stag: Давление тороможения газа.
:param v_gas: Распределение скорости газа по профилю.
:param c_p_gas_av: Средняя теплоемкость газа
:param work_fluid: Рабочее тело турбины.
:param alpha_gas: Распределение коэффициента теплоотдачи со стророны газа.
:param T_cool: Распределение температуры торможения охлаждающего воздуха вдоль профиля.
:param G_cool0: Расход охлаждающего воздуха на входе в канал.
:param p_cool_stag0: Полное давление охлаждающего воздуха на входе в канал.
:param c_p_cool_av: Средняя теплоемкость охлаждающего воздуха.
:param cool_fluid: Охлаждающее тело.
:param height: Высота участка лопатки
:param g_cool0_s: Относительный расход охлаждающего воздуха на входе в канал спинки.
"""
self.x_hole = np.array(x_hole)
self.hole_num = np.array(hole_num)
self.d_hole = np.array(d_hole)
self.phi_hole = np.array(phi_hole)
self.mu_hole = np.array(mu_hole)
self._modify_hole_data()
self.T_gas_stag = T_gas_stag
self.p_gas_stag = p_gas_stag
self.v_gas = v_gas
self.c_p_gas_av = c_p_gas_av
self.work_fluid = work_fluid
self.alpha_gas = alpha_gas
self.T_cool = T_cool
self.p_cool_stag0 = p_cool_stag0
self.G_cool0 = G_cool0
self.c_p_cool_av = c_p_cool_av
self.cool_fluid = cool_fluid
self.height = height
self.g_coo0_s = g_cool0_s
self.k_gas_av = self.work_fluid.k_func(self.c_p_gas_av)
self.k_cool_av = self.cool_fluid.k_func(self.c_p_cool_av)
self.hole_step = np.zeros(self.x_hole.shape[0])
self.s = np.zeros(self.x_hole.shape[0])
self.T_cool_hole = np.zeros(self.x_hole.shape[0])
"Температура торможения охлаждающей среды у входа в отверстия"
self.v_gas_hole = np.zeros(self.x_hole.shape[0])
"Скорость газа у отверстий"
self.T_gas_hole = np.zeros(self.x_hole.shape[0])
"Статическая температура газа у отверстий"
self.p_gas_hole = np.zeros(self.x_hole.shape[0])
"Статическое давление газа у отверстий"
self.rho_gas_hole = np.zeros(self.x_hole.shape[0])
"Статичекая плотность газа у отверстий"
self.v_cool_hole_out = np.zeros(self.x_hole.shape[0])
"Скорость истечения охлаждающей среды из отвестий"
self.rho_cool_stag_hole = np.zeros(self.x_hole.shape[0])
"Плотность охлаждающей среды по параметрам торможения на входе в отверстия"
self.rho_cool_hole_out = np.zeros(self.x_hole.shape[0])
"Статическая плотность охлаждающей среды на выходе из отверстия"
self.m = np.zeros(self.x_hole.shape[0])
"Параметры вдува на отверстиях"
self.Re_s = np.zeros(self.x_hole.shape[0])
"Число Рейнольдса по ширине щели на отверстиях"
self.phi_temp = np.zeros(self.x_hole.shape[0])
"Температурный фактор на отверстиях"
self.G_cool_hole = np.zeros(self.x_hole.shape[0])
"Расход охлаждающей среды в сечении канала перед отверстиями"
self.dG_cool_hole = np.zeros(self.x_hole.shape[0])
"Расход охлаждающей среды перед отверстиями"
self.film_eff_list = []
"Список функций эффективности пленок от каждого ряда отверстий"
def __init__(self,
section: BladeSection,
height=None,
D_av=None,
wall_thickness=None,
T_wall_out=None,
T_cool_fluid0=None,
T_out_stag=None,
alpha_out=None,
G_cool=None,
lam_blade: typing.Callable[[float], float] = None,
cool_fluid: IdealGas = Air(),
cover_thickness=0.15e-3,
lam_cover=2):
"""
:param section: BladeSection. \n
Сечение рассчитываемого участка лопатки.
:param height: float. \n
Высота рассчитываемого участка лопакти.
:param D_av: float. \n
Средний диаметр участка.
:param wall_thickness: float. \n
Толщина стенки.
:param T_wall_out: float. \n
Средняя температура наружной поверхности стенки участка лопатки.
:param T_cool_fluid0: float. \n
Температура охраждающего тела на входе в лопатку.
:param T_out_stag: float. \n
Средняя температура торможения обтекающей лопатку среды.
:param alpha_out: float. \n
Средний коэффициент теплоотдачи от обтекающей лопакту среды к лопатке.
:param G_cool: float. \n
Расход охлаждающего тела.
:param lam_blade: callable. \n
Тепопроводность материала лопатки в зависимости от температуры
:param cool_fluid: IdealGas. \n
Охлаждающее тело.
:param cover_thickness: float, optional. \n
Толщина защитного покрытия.
:param lam_cover: float, optional. \n
Теплопроводность защитного покрытия.
"""
self.section = section
self.height = height
self.D_av = D_av
self.wall_thickness = wall_thickness
self.T_wall_out = T_wall_out
self.T_cool_fluid0 = T_cool_fluid0
self.T_out_stag = T_out_stag
self.alpha_out = alpha_out
self.G_cool = G_cool
self.lam_blade = lam_blade
self.cool_fluid = cool_fluid
self.cover_thickness = cover_thickness
self.lam_cover = lam_cover
self.perimeter = None
self.square = None
self.Q_blade = None
self.T_wall_av = None
self.T_wall_in = None
self.delta_T = None
self.T_cool_fluid_av = None
self.T_cool_fluid_old = None
self.cool_fluid_temp_res = None
self.heat_transfer_coef = None
self.c_p_cool_av = None
self.mu_cool_fluid = None
self.Re_cool_fluid = None
self.alpha_cool_fluid_av = None
self.lam_cool_fluid = None
self.epsilon = None
self.D = None
self.channel_width = None
def setUp(self):
self.comb_chamber = CombustionChamberModel(
g_fuel=0.02,
G_c1_in=30,
T_stag_in=800,
p_stag_in=13e5,
G_in=29,
G_fuel_in=0,
eta_comb=0.99,
sigma_comb=0.99,
)
self.turbine = Turbine(turbine_type=TurbineType.WORK,
stage_number=2,
T_g_stag=1400,
p_g_stag=15e5,
G_turbine=34,
G_fuel=0.9,
work_fluid=NaturalGasCombustionProducts(),
l1_D1_ratio=0.15,
n=10e3,
T_t_stag_cycle=1150,
eta_t_stag_cycle=0.9,
alpha11=np.radians(14),
precision=0.0001,
gamma_in=np.radians(0),
gamma_out=np.radians(10),
H01_init=200e3,
c21_init=250)
self.turbine.compute_geometry()
self.turbine.compute_stages_gas_dynamics()
self.turbine.compute_integrate_turbine_parameters()
self.turb_model = OutletTurbineModel(
T_stag_in=self.turbine.T_g_stag,
p_stag_in=self.turbine.p_g_stag,
G_in=self.turbine.G_turbine,
G_fuel_in=self.turbine.G_fuel,
pi_t_stag=self.turbine.pi_t_stag,
T_stag_in_nom=self.turbine.T_g_stag,
p_stag_in_nom=self.turbine.p_g_stag,
G_in_nom=self.turbine.G_turbine,
pi_t_stag_nom=self.turbine.pi_t_stag,
eta_t_stag_nom=self.turbine.eta_t_stag,
F_out=self.turbine.geom.last.A2,
eta_m=self.turbine.eta_m,
precision=self.turbine.precision)
comp_stage_num = 10
H_t_rel_dist = QuadraticBezier(0.3,
0.25,
stage_num=comp_stage_num,
angle1=np.radians(10),
angle2=np.radians(10))
eta_rel_dist = QuadraticBezier(0.84,
0.84,
stage_num=comp_stage_num,
angle1=np.radians(3),
angle2=np.radians(3))
c1_a_rel_dist = QuadraticBezier(0.4,
0.4,
stage_num=comp_stage_num,
angle1=np.radians(10),
angle2=np.radians(10))
self.comp = Compressor(
work_fluid=Air(),
stage_num=comp_stage_num,
const_diam_par_arr=[0.5 for _ in range(comp_stage_num)],
p0_stag=1e5,
T0_stag=288,
G=28,
n=9e3,
H_t_rel_arr=H_t_rel_dist.get_array(),
eta_ad_stag_arr=eta_rel_dist.get_array(),
R_av_arr=[0.5 for _ in range(comp_stage_num)],
k_h_arr=[1.0 for _ in range(comp_stage_num)],
c1_a_rel_arr=c1_a_rel_dist.get_array(),
h_rk_rel_arr=[3.5 for _ in range(comp_stage_num)],
h_na_rel_arr=[3.5 for _ in range(comp_stage_num)],
delta_a_rk_rel_arr=[0.4 for _ in range(comp_stage_num)],
delta_a_na_rel_arr=[0.4 for _ in range(comp_stage_num)],
d1_in_rel1=0.5,
zeta_inlet=0.04,
zeta_outlet=0.03,
c11_init=200,
precision=0.0001)
self.comp.compute()
self.comp_model = CompressorModel(characteristics=From16To18Pi(),
T_stag_in=self.comp.T0_stag,
p_stag_in=self.comp.p0_stag,
pi_c_stag_rel=1,
n_norm_rel=1,
T_stag_in_nom=self.comp.T0_stag,
p_stag_in_nom=self.comp.p0_stag,
G_in_nom=self.comp.G,
eta_c_stag_nom=self.comp.eta_c_stag,
n_nom=self.comp.n,
pi_c_stag_nom=self.comp.pi_c_stag,
precision=0.0001)
self.T_stag_in_outlet = np.linspace(300, 1000, 5)
self.G_in_outlet = np.linspace(2, 40, 5)
self.dif_outlet = np.linspace(1.1, 10.5, 5)