def get_last_work_stage(stage_geom: StageGeomAndHeatDrop,
prev_stage: StageGasDynamics, L_stage_rel,
eta_t0) -> StageGasDynamics:
logger.info('get_last_work_stage')
L_stage = L_stage_rel / (
prev_stage.G_stage_out / prev_stage.G_turbine -
(stage_geom.g_lb + stage_geom.g_ld + stage_geom.g_lk))
p0_stag = prev_stage.p2 * (1 + (stage_geom.mu * prev_stage.c2) ** 2 / (2 * prev_stage.c_p_gas *
prev_stage.T_st)) ** \
(prev_stage.k_gas / (prev_stage.k_gas - 1))
result = StageGasDynamics(prev_stage.T_st_stag,
p0_stag,
prev_stage.G_stage_out,
prev_stage.G_turbine,
prev_stage.alpha_air,
KeroseneCombustionProducts(),
stage_geom.rho,
stage_geom.phi,
stage_geom.psi,
stage_geom.l1,
stage_geom.l2,
stage_geom.D1,
stage_geom.D2,
stage_geom.delta_r_rk,
stage_geom.n,
stage_geom.epsilon,
stage_geom.g_lk,
stage_geom.g_ld,
stage_geom.g_lb,
L_t=L_stage,
eta_t0=eta_t0)
return result
def get_last_pressure_stage(turbine_geom: TurbineGeomAndHeatDropDistribution,
stage_geom: StageGeomAndHeatDrop,
prev_stage: StageGasDynamics) -> StageGasDynamics:
logger.info('get_last_pressure_stage')
p0_stag = prev_stage.p2 * (1 + (stage_geom.mu * prev_stage.c2)**2 / (2 * prev_stage.c_p_gas * prev_stage.T_st)) ** \
(prev_stage.k_gas / (prev_stage.k_gas - 1))
result = StageGasDynamics(prev_stage.T_st_stag,
p0_stag,
prev_stage.G_stage_out,
prev_stage.G_turbine,
prev_stage.alpha_air,
KeroseneCombustionProducts(),
stage_geom.rho,
stage_geom.phi,
stage_geom.psi,
stage_geom.l1,
stage_geom.l2,
stage_geom.D1,
stage_geom.D2,
stage_geom.delta_r_rk,
stage_geom.n,
stage_geom.epsilon,
stage_geom.g_lk,
stage_geom.g_ld,
stage_geom.g_lb,
p2=turbine_geom.p_t)
return result
def get_intermediate_stage(stage_geom: StageGeomAndHeatDrop, prev_stage: StageGasDynamics, precise_heat_drop=True) -> \
StageGasDynamics:
logger.info('get_intermediate_stage')
if precise_heat_drop:
H0 = stage_geom.H0 * (1 + (1 - stage_geom.mu)**2 * prev_stage.c2**2 /
(2 * prev_stage.c_p_gas * prev_stage.T_st)
) + 0.5 * (stage_geom.mu * prev_stage.c2)**2
else:
H0 = stage_geom.H0
p0_stag = prev_stage.p2 * (1 + (stage_geom.mu * prev_stage.c2)**2 / (2 * prev_stage.c_p_gas * prev_stage.T_st)) ** \
(prev_stage.k_gas / (prev_stage.k_gas - 1))
result = StageGasDynamics(prev_stage.T_st_stag,
p0_stag,
prev_stage.G_stage_out,
prev_stage.G_turbine,
prev_stage.alpha_air,
KeroseneCombustionProducts(),
stage_geom.rho,
stage_geom.phi,
stage_geom.psi,
stage_geom.l1,
stage_geom.l2,
stage_geom.D1,
stage_geom.D2,
stage_geom.delta_r_rk,
stage_geom.n,
stage_geom.epsilon,
stage_geom.g_lk,
stage_geom.g_ld,
stage_geom.g_lb,
H0=H0)
return result
def get_first_stage_gas_dynamics(stage_geom: StageGeomAndHeatDrop, T0_stag,
p0_stag, G_turbine,
alpha_air) -> StageGasDynamics:
logger.info('get_first_stage_gas_dynamics')
result = StageGasDynamics(T0_stag,
p0_stag,
G_turbine,
G_turbine,
alpha_air,
KeroseneCombustionProducts(),
stage_geom.rho,
stage_geom.phi,
stage_geom.psi,
stage_geom.l1,
stage_geom.l2,
stage_geom.D1,
stage_geom.D2,
stage_geom.delta_r_rk,
stage_geom.n,
stage_geom.epsilon,
stage_geom.g_lk,
stage_geom.g_ld,
stage_geom.g_lb,
H0=stage_geom.H0)
return result
def _compute_outlet(self):
self._outlet.input.alpha = self._combustion_chamber.output.alpha
self._outlet.input.lam_out = self.lam_out
self._outlet.input.p_out = self.p_a
self._outlet.input.sigma_out = self.sigma_out
self._outlet.input.work_fluid = KeroseneCombustionProducts()
logger.info('%s _compute_outlet' % str(self))
self._outlet.compute_output()
def _compute_power_turbine(self):
self._power_turbine.input.alpha = self._combustion_chamber.output.alpha
self._power_turbine.input.work_fluid = KeroseneCombustionProducts()
self._power_turbine.input.eta_turb_stag_p = self.eta_power_turb_stag_p
self._power_turbine.input.p_in_stag = self._compressor_turbine.output.p_out_stag
self._power_turbine.input.T_in_stag = self._compressor_turbine.output.T_out_stag
self._power_turbine.input.T_out_stag_init = 600
logger.info('%s _compute_power_turbine' % str(self))
self._power_turbine.compute_output()
def _compute_compressor_turbine(self):
self._compressor_turbine.input.T_in_stag = self.T_comb_stag
self._compressor_turbine.input.p_in_stag = self._combustion_chamber.output.p_out_stag
self._compressor_turbine.input.alpha = self._combustion_chamber.output.alpha
self._compressor_turbine.input.eta_m = self.eta_m
self._compressor_turbine.input.eta_turb_stag_p = self.eta_comp_turb_stag_p
self._compressor_turbine.input.g_gas = self._combustion_chamber.output.g_gas
self._compressor_turbine.input.L_comp = self._compressor.output.L_comp
self._compressor_turbine.input.pi_turb_stag_init = 3
self._compressor_turbine.input.work_fluid = KeroseneCombustionProducts()
logger.info('%s _compute_compressor_turbine' % str(self))
self._compressor_turbine.compute_output()
def __init__(self, turbine_type: TurbineType, **kwargs):
"""
:param turbine_type:
:param kwargs: gamma_av, gamma_sum, gamma_in, gamma_out
"""
self._T_g_stag = None
self._p_g_stag = None
self._G_turbine = None
self._kwargs = kwargs
self._alpha_air = None
self._stage_number = None
self._k_n = 6.8
self._work_fluid = KeroseneCombustionProducts()
self._l1_D1_ratio = None
self._n = None
self._c21_init = None
self._H01_init = None
self._rho1 = None
self._phi1 = 0.97
self._T_t_stag_cycle = None
self._p_t_stag_cycle = None
self._L_t_cycle = None
self._alpha11 = None
self._eta_t_stag_cycle = None
self._H_t_stag_cycle = None
self._geom = None
self.c_p_gas = None
self.k_gas = None
self.c_p_gas_stag = None
self.k_gas_stag = None
self._gas_dynamics = list()
self._type = turbine_type
if ('gamma_av' in kwargs) and ('gamma_sum' in kwargs):
self._gamma_av = kwargs['gamma_av']
self._gamma_in = None
self._gamma_out = None
self._gamma_sum = kwargs['gamma_sum']
elif ('gamma_in' in kwargs) and ('gamma_out' in kwargs):
self._gamma_av = None
self._gamma_in = kwargs['gamma_in']
self._gamma_out = kwargs['gamma_out']
self._gamma_sum = None
else:
assert False, 'gamma_av and gamma_sum or gamma_in and gamma_out must be set'
self.L_t_sum = None
self.H_t = None
self.H_t_stag = None
self.eta_t = None
self.eta_t_stag = None
self.eta_l = None
self.N = None
self.eta_m = None
def _init_turbine_geom(self):
try:
self._geom = TurbineGeomAndHeatDropDistribution(self.stage_number, self.eta_t_stag_cycle,
self.H_t_stag_cycle,
self.c21_init, self.n, KeroseneCombustionProducts(),
self.T_g_stag, self.p_g_stag, self.alpha_air,
self.G_turbine, self.l1_D1_ratio, self.H01_init,
self.rho1, self.phi1, self.alpha11, self.k_n,
self.T_t_stag_cycle,
self.p_t_stag_cycle, **self._kwargs)
except AssertionError:
pass
def _compute_combustion_chamber(self):
self._combustion_chamber.input.T_out_stag = self.T_comb_stag
self._combustion_chamber.input.eta_comb = self.eta_comb
self._combustion_chamber.input.g_cooling = self.g_cooling
self._combustion_chamber.input.g_outflow = self.g_outflow
self._combustion_chamber.input.g_return = self.g_return
self._combustion_chamber.input.l0 = self.l0
self._combustion_chamber.input.p_in_stag = self._compressor.output.p_out_stag
self._combustion_chamber.input.Q_n = self.Q_n
self._combustion_chamber.input.sigma_comb = self.sigma_comb
self._combustion_chamber.input.T_in_stag = self._compressor.output.T_out_stag
self._combustion_chamber.input.work_fluid_in = Air()
self._combustion_chamber.input.work_fluid_out = KeroseneCombustionProducts()
logger.info('%s _compute_combustion_chamber' % str(self))
self._combustion_chamber.compute_output()
turbine_geometry.compute_output()
dh01_rel = abs(turbine_geometry.first.H0 -
turbine_geometry.H01) / turbine_geometry.H01
logger.debug('specify_h01 dh01_rel = %s' % dh01_rel)
H01 = turbine_geometry.first.H0
if __name__ == '__main__':
deg = np.pi / 180
turbine_geom = TurbineGeomAndHeatDropDistribution(
2,
0.91,
300e3,
150,
10e3,
KeroseneCombustionProducts(),
1400,
1.3e6,
2.4,
9,
1 / 3.5,
180e3,
0.8,
0.96,
15 * deg,
6.8,
850,
120e3,
gamma_av=0 * deg,
gamma_sum=15 * deg)
turbine_geom[0].delta_a_b_sa_ratio = 0.23