def test_integrate_work_balance_comp_turbine_ker_wcool(self):
"""Соврадение работы, определенной на разности входной и выходной энтальпий, заданной величине."""
work_fluid = KeroseneCombustionProducts()
T_g_stag = self.comp_turbine_ker_wcool.T_g_stag
T_t_stag = self.comp_turbine_ker_wcool.last.T_st_stag
alpha = self.comp_turbine_ker_wcool.first.alpha_air_in
c_p = work_fluid.c_p_av_int_func(T_g_stag, T_t_stag, alpha=alpha)
L_t = c_p * (T_g_stag - T_t_stag)
L_t_res = abs(L_t - self.comp_turbine_ker_wcool.L_t_cycle) / self.comp_turbine_ker_wcool.L_t_cycle
self.assertAlmostEqual(L_t_res, 0, places=3)
def setUp(self):
self.turbine = Turbine(TurbineType.WORK,
T_g_stag=1400,
p_g_stag=300e3,
G_turbine=25,
work_fluid=KeroseneCombustionProducts(),
G_fuel=1,
l1_D1_ratio=0.25,
n=15e3,
T_t_stag_cycle=1150,
stage_number=2,
eta_t_stag_cycle=0.91,
k_n=6.8,
eta_m=0.99,
auto_compute_heat_drop=True,
precise_heat_drop=False,
auto_set_rho=True,
H01_init=120e3,
c21_init=250,
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.stage_prof = StageProfiler(
profiling_type=ProfilingType.ConstantCirculation,
p0_stag=lambda r: self.turbine[0].p0_stag,
T0_stag=lambda r: self.turbine[0].T0_stag,
c0=lambda r: 100,
alpha0=lambda r: np.radians([90])[0],
c_p=self.turbine.c_p_gas,
k=self.turbine.k_gas,
D1_in=self.turbine.geom[0].D1 - self.turbine.geom[0].l1,
D1_av=self.turbine.geom[0].D1,
D1_out=self.turbine.geom[0].D1 + self.turbine.geom[0].l1,
n=self.turbine.n,
c1_av=self.turbine[0].c1,
alpha1_av=self.turbine[0].alpha1,
L_u_av=self.turbine[0].L_u,
c2_a_av=self.turbine[0].c2_a,
c2_u_av=self.turbine[0].c2_u,
b_a_sa=self.turbine.geom[0].b_sa,
b_a_rk=self.turbine.geom[0].b_rk,
delta_a_sa=self.turbine.geom[0].delta_a_sa,
delta_a_rk=self.turbine.geom[0].delta_a_rk,
t_rel_av_sa=0.8,
t_rel_av_rk=0.7,
center=True,
section_num=3,
x0=0.,
y0=0.,
pnt_cnt=35,
gamma1_k_rel_rk=lambda r_rel: 0.5,
gamma1_rk=None,
gamma1_sa=None,
center_point_rk=lambda r_rel: 0.46 + 0.02 * r_rel,
center_point_sa=lambda r_rel: 0.51 + 0.02 * r_rel)
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.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 setUp(self):
self.turbine = Turbine(TurbineType.WORK,
T_g_stag=1450,
p_g_stag=400e3,
G_turbine=25,
work_fluid=KeroseneCombustionProducts(),
G_fuel=1,
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()
def get_theta_gas(r_in, r_out, r_max_rel, theta_max):
r_max = r_max_rel * (r_out - r_in) + r_in
a = 3 * (r_out - r_in - theta_max *
(r_out - r_in)) / ((r_out - r_max)**3 - (r_in - r_max)**3)
return lambda r: a * (r - r_max)**2 + theta_max
def get_T_gas(theta_gas, T_c_stag, T_gas_stag_av):
return lambda r: T_c_stag + theta_gas(r) * (T_gas_stag_av -
T_c_stag)
# Внутренний радиус
r_in = 0.5 * (self.turbine.geom[0].D1 - self.turbine.geom[0].l1)
# Периферийный радиус
r_out = 0.5 * (self.turbine.geom[0].D1 + self.turbine.geom[0].l1)
# Относительное положение мксимума
r_max_rel = 0.5
# Максимальная неравномерность
theta_max = 1.1
# Температура после компрессора
T_c_stag = 685
# Средняя температура газа
T_gas_stag_av = self.turbine[0].T0_stag
# Функция неравномерности
theta_gas = get_theta_gas(r_in, r_out, r_max_rel, theta_max)
# Функция температуры газа от радиуса
T_g_stag = get_T_gas(theta_gas, T_c_stag, T_gas_stag_av)
self.turbine_profiler = TurbineProfiler(
turbine=self.turbine,
p_in_stag=lambda r: self.turbine[0].p0_stag,
T_in_stag=T_g_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()
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 setUp(self):
self.precision = 0.00001
self.comp_turbine_ker_wcool = Turbine(
TurbineType.WORK,
T_g_stag=1523,
p_g_stag=16e5,
G_turbine=40,
G_fuel=0.8,
work_fluid=KeroseneCombustionProducts(),
l1_D1_ratio=0.25,
n=13e3,
T_t_stag_cycle=1000,
stage_number=3,
eta_t_stag_cycle=0.90,
k_n=6.8,
eta_m=0.99,
auto_compute_heat_drop=False,
auto_set_rho=True,
precise_heat_drop=True,
precision=self.precision,
H0_list=[290e3, 290e3, 290e3],
alpha11=np.radians([17])[0],
gamma_av=np.radians([4])[0],
gamma_sum=np.radians([10])[0]
)
self.comp_turbine_ker_wcool.compute_geometry()
self.comp_turbine_ker_wcool.compute_stages_gas_dynamics()
self.comp_turbine_ker_wcool.compute_integrate_turbine_parameters()
self.comp_turbine_ngas_wcool = Turbine(
TurbineType.WORK,
T_g_stag=1523,
p_g_stag=16e5,
G_turbine=40,
G_fuel=0.8,
work_fluid=NaturalGasCombustionProducts(),
l1_D1_ratio=0.25,
n=13e3,
T_t_stag_cycle=1000,
stage_number=3,
eta_t_stag_cycle=0.90,
k_n=6.8,
eta_m=0.99,
auto_compute_heat_drop=False,
auto_set_rho=True,
precise_heat_drop=True,
precision=self.precision,
H0_list=[290e3, 290e3, 290e3],
alpha11=np.radians([17])[0],
gamma_av=np.radians([4])[0],
gamma_sum=np.radians([10])[0]
)
self.comp_turbine_ngas_wcool.compute_geometry()
self.comp_turbine_ngas_wcool.compute_stages_gas_dynamics()
self.comp_turbine_ngas_wcool.compute_integrate_turbine_parameters()
self.power_turbine_ngas_wcool = Turbine(
TurbineType.PRESSURE,
T_g_stag=1523,
p_g_stag=16e5,
G_turbine=40,
G_fuel=0.8,
work_fluid=NaturalGasCombustionProducts(),
l1_D1_ratio=0.25,
n=13e3,
T_t_stag_cycle=1000,
stage_number=3,
eta_t_stag_cycle=0.90,
k_n=6.8,
eta_m=0.99,
auto_compute_heat_drop=False,
auto_set_rho=True,
precise_heat_drop=True,
precision=self.precision,
H0_list=[290e3, 290e3, 290e3],
alpha11=np.radians([17])[0],
gamma_av=np.radians([4])[0],
gamma_sum=np.radians([10])[0]
)
eta_t_res = 1
eta_t_stag_new = self.power_turbine_ngas_wcool.eta_t_stag_cycle
self.precision_eta_t = 0.0001
while eta_t_res >= self.precision_eta_t:
self.power_turbine_ngas_wcool.eta_t_stag_cycle = eta_t_stag_new
self.power_turbine_ngas_wcool.compute_geometry()
self.power_turbine_ngas_wcool.compute_stages_gas_dynamics()
self.power_turbine_ngas_wcool.compute_integrate_turbine_parameters()
eta_t_stag_new = self.power_turbine_ngas_wcool.eta_t_stag
eta_t_stag_old = self.power_turbine_ngas_wcool.eta_t_stag_cycle
eta_t_res = abs(eta_t_stag_old - eta_t_stag_new) / eta_t_stag_old
self.comp_turbine_ngas_cool = Turbine(
TurbineType.WORK,
T_g_stag=1523,
p_g_stag=16e5,
G_turbine=40,
G_fuel=0.8,
work_fluid=NaturalGasCombustionProducts(),
l1_D1_ratio=0.25,
n=13e3,
T_t_stag_cycle=1000,
stage_number=3,
eta_t_stag_cycle=0.90,
k_n=6.8,
eta_m=0.99,
auto_compute_heat_drop=False,
auto_set_rho=True,
precise_heat_drop=True,
precision=self.precision,
H0_list=[290e3, 290e3, 290e3],
alpha11=np.radians([17])[0],
gamma_av=np.radians([4])[0],
gamma_sum=np.radians([10])[0]
)
self.comp_turbine_ngas_cool.geom[0].g_cool = 0.05
self.comp_turbine_ngas_cool.geom[1].g_cool = 0.05
self.comp_turbine_ngas_cool.geom[2].g_cool = 0.01
self.comp_turbine_ngas_cool.compute_geometry()
self.comp_turbine_ngas_cool.compute_stages_gas_dynamics()
self.comp_turbine_ngas_cool.compute_integrate_turbine_parameters()
def setUp(self):
self.precision = 0.0005
self.comp_turb_h0_auto = Turbine(TurbineType.WORK,
T_g_stag=1523,
p_g_stag=16e5,
G_turbine=40,
G_fuel=0.8,
work_fluid=KeroseneCombustionProducts(),
l1_D1_ratio=0.25,
n=13e3,
T_t_stag_cycle=1100,
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,
precision=self.precision,
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_h0_auto.geom[0].g_cool = 0.03
self.comp_turb_h0_auto.geom[0].g_lb = 0.00
self.comp_turb_h0_auto.geom[0].g_lk = 0.00
self.comp_turb_h0_auto.geom[0].g_ld = 0.00
self.comp_turb_h0_auto.geom[0].T_cool = 750
self.comp_turb_h0_auto.geom[1].g_cool = 0.03
self.comp_turb_h0_auto.compute_geometry()
self.comp_turb_h0_auto.compute_stages_gas_dynamics()
self.comp_turb_h0_auto.compute_integrate_turbine_parameters()
self.comp_turb_h0_hand = Turbine(TurbineType.WORK,
T_g_stag=1523,
p_g_stag=16e5,
G_turbine=40,
G_fuel=0.8,
work_fluid=NaturalGasCombustionProducts(),
l1_D1_ratio=0.12,
n=13e3,
T_t_stag_cycle=1100,
stage_number=2,
eta_t_stag_cycle=0.91,
k_n=6.8,
eta_m=0.99,
auto_compute_heat_drop=False,
auto_set_rho=True,
precise_heat_drop=False,
H0_list=[160e3, 140e3],
alpha11=np.radians([17])[0],
gamma_av=np.radians([4])[0],
gamma_sum=np.radians([10])[0])
self.comp_turb_h0_hand.compute_geometry()
self.comp_turb_h0_hand.compute_stages_gas_dynamics()
self.comp_turb_h0_hand.compute_integrate_turbine_parameters()
self.comp_turb_rho_hand = Turbine(TurbineType.WORK,
T_g_stag=1400,
p_g_stag=5.5e5,
G_turbine=25,
G_fuel=1,
work_fluid=KeroseneCombustionProducts(),
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=False,
precise_heat_drop=False,
rho_list=[0.45, 0.4],
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_rho_hand.compute_geometry()
self.comp_turb_rho_hand.compute_stages_gas_dynamics()
self.comp_turb_rho_hand.compute_integrate_turbine_parameters()
self.power_turb_h0_auto = Turbine(TurbineType.PRESSURE,
T_g_stag=1400,
p_g_stag=5.5e5,
G_turbine=25,
G_fuel=1,
work_fluid=NaturalGasCombustionProducts(),
l1_D1_ratio=0.25,
n=15e3,
T_t_stag_cycle=1200,
stage_number=3,
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_in=np.radians([0])[0],
gamma_out=np.radians([10])[0])
self.power_turb_h0_auto.compute_geometry()
self.power_turb_h0_auto.compute_stages_gas_dynamics()
self.power_turb_h0_auto.compute_integrate_turbine_parameters()
def setUp(self):
self.precision = 0.001
self.heat_drop_stage = StageGasDynamics(
T0_stag=1400,
p0_stag=10e5,
T0_stag_ad_t=1400,
G_stage_in=30,
G_turbine=29.5,
G_fuel=0.7,
work_fluid=KeroseneCombustionProducts(),
rho=0.3,
phi=0.97,
psi=0.97,
l1=0.06,
l2=0.068,
D1=0.3,
D2=0.3,
delta_r_rk=0.01,
n=11e3,
epsilon=1,
g_lb=0,
g_lk=0,
g_ld=0,
g_cool=0,
precision=self.precision,
H0=120e3
)
self.heat_drop_stage.compute()
self.work_stage = StageGasDynamics(
T0_stag=1400,
p0_stag=10e5,
T0_stag_ad_t=1400,
G_stage_in=30,
G_turbine=29.5,
G_fuel=0.7,
work_fluid=KeroseneCombustionProducts(),
rho=0.3,
phi=0.97,
psi=0.97,
l1=0.06,
l2=0.068,
D1=0.3,
D2=0.3,
delta_r_rk=0.01,
n=11e3,
epsilon=1,
g_lb=0,
g_lk=0,
g_ld=0,
g_cool=0,
precision=self.precision,
L_t=50e3,
eta_t0=0.9
)
self.work_stage.compute()
self.press_stage = StageGasDynamics(
T0_stag=1400,
p0_stag=10e5,
T0_stag_ad_t=1400,
G_stage_in=30,
G_turbine=29.5,
G_fuel=0.7,
work_fluid=KeroseneCombustionProducts(),
rho=0.3,
phi=0.97,
psi=0.97,
l1=0.06,
l2=0.068,
D1=0.3,
D2=0.3,
delta_r_rk=0.01,
n=11e3,
epsilon=1,
g_lb=0,
g_lk=0,
g_ld=0,
g_cool=0,
precision=self.precision,
p2_stag=7.9e5
)
self.press_stage.compute()