def test_outlet(self):
for T_stag_in in self.T_stag_in_outlet:
for G_in in self.G_in_outlet:
for dif in self.dif_outlet:
print('T_stag_in = %.1f, G_in = %.3f, dif = %.3f' %
(T_stag_in, G_in, dif))
p_stag_in = 1.2e5
work_fluid = NaturalGasCombustionProducts()
G_fuel = 0.1
alpha = 1 / (work_fluid.l0 * G_fuel / (G_in - G_fuel))
c_p = work_fluid.c_p_real_func(T_stag_in, alpha=alpha)
k = work_fluid.k_func(c_p)
F_in = 0.25
q = G_in * np.sqrt(work_fluid.R * T_stag_in) / (
F_in * p_stag_in * gd.m(k))
lam = gd.lam(k, q=q)
a_cr = gd.a_cr(T_stag_in, k, work_fluid.R)
c_in = a_cr * lam
outlet = OutletModel(T_stag_in=T_stag_in,
p_stag_in=1.2e5,
G_in=G_in,
G_fuel_in=G_fuel,
c_in=c_in,
F_in=F_in,
F_out=F_in * dif,
sigma=0.99)
outlet.compute()
G_in = outlet.rho_in * outlet.F_in * outlet.c_in
G_out = outlet.rho_out * outlet.F_out * outlet.c_out
G_res = abs(G_out - G_in) / G_in
self.assertAlmostEqual(G_res, 0, places=3)
def test_integrate_work_balance_power_turbine_ngas_wcool(self):
"""Соврадение работы, определенной на разности входной и выходной энтальпий, заданной величине."""
work_fluid = NaturalGasCombustionProducts()
T_g_stag = self.power_turbine_ngas_wcool.T_g_stag
T_t_stag = self.power_turbine_ngas_wcool.last.T_st_stag
work_fluid.T1 = T_g_stag
work_fluid.T2 = T_t_stag
work_fluid.alpha = self.power_turbine_ngas_wcool.first.alpha_air_in
L_t = work_fluid.c_p_av_int * (T_g_stag - T_t_stag)
L_t_res = abs(L_t - self.power_turbine_ngas_wcool.L_t_cycle) / self.power_turbine_ngas_wcool.L_t_cycle
self.assertAlmostEqual(L_t_res, 0, places=2)
def __init__(self,
T_stag_in,
p_stag_in,
G_in,
G_fuel_in,
c_in,
F_in,
F_out,
sigma,
work_fluid: IdealGas = NaturalGasCombustionProducts()):
ModelSingleWorkFluid.__init__(self)
ModelStaticPar.__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.c_in = c_in
self.F_in = F_in
self.F_out = F_out
self.sigma = sigma
self.work_fluid = work_fluid
self.fuel_content = None
self.alpha = None
self.c_p = None
self.k = None
self.static_out = None
def __init__(self,
T_stag_in,
p_stag_in,
G_in,
G_fuel_in,
pi_t_stag,
T_stag_in_nom,
p_stag_in_nom,
G_in_nom,
pi_t_stag_nom,
eta_t_stag_nom,
F_out,
eta_m=0.9,
work_fluid: IdealGas = NaturalGasCombustionProducts(),
precision=0.001):
TurbineModel.__init__(self, T_stag_in, p_stag_in, G_in, G_fuel_in,
pi_t_stag, T_stag_in_nom, p_stag_in_nom,
G_in_nom, pi_t_stag_nom, eta_t_stag_nom, eta_m,
work_fluid, precision)
self.F_out = F_out
self.c_p_out = None
self.k_out = None
self.q_out = None
self.lam_out = None
self.a_cr_out = None
self.c_out = None
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 test_integrate_work_balance_comp_turbine_ngas_cool(self):
"""Соврадение работы, определенной на разности входной и выходной энтальпий, заданной величине."""
work_fluid = NaturalGasCombustionProducts()
T_g_stag = self.comp_turbine_ngas_cool.T_g_stag
T_t_stag = self.comp_turbine_ngas_cool.last.T_st_stag
g_outlet = self.comp_turbine_ngas_cool.last.G_stage_in / self.comp_turbine_ngas_cool.G_turbine
i_stag_in = work_fluid.get_specific_enthalpy(T_g_stag, alpha=self.comp_turbine_ngas_cool.first.alpha_air_in)
i_stag_out = work_fluid.get_specific_enthalpy(
T_t_stag, alpha=self.comp_turbine_ngas_cool.last.alpha_air_in
) * g_outlet
i_cool = 0
for n, stage in enumerate(self.comp_turbine_ngas_cool):
if n != self.comp_turbine_ngas_cool.stage_number - 1:
i_cool += stage.i_cool
L_t = i_stag_in - i_stag_out + i_cool
L_t_res = abs(L_t - self.comp_turbine_ngas_cool.L_t_cycle) / self.comp_turbine_ngas_cool.L_t_cycle
self.assertAlmostEqual(L_t_res, 0, places=3)
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 test_setting_data_from_input_file(self):
turbine_input = TurbineInput(TurbineType.Compressor, 1500, 12e5, 25, 1,
NaturalGasCombustionProducts(), 1200, 0.91)
self.form.set_data_from_turbine_input(turbine_input)
self.assertEqual(self.form.turbine_type.currentIndex(), 1)
self.assertEqual(self.form.fuel.currentIndex(), 1)
self.assertAlmostEqual(self.form.T_g_stag.value(), turbine_input.T_g_stag, 2)
self.assertAlmostEqual(self.form.p_g_stag.value(), turbine_input.p_g_stag / 1e6, places=3)
self.assertAlmostEqual(self.form.G_t.value(), turbine_input.G_turbine, places=2)
self.assertAlmostEqual(self.form.G_fuel.value(), turbine_input.G_fuel, places=2)
self.assertAlmostEqual(self.form.T_t_stag_cycle.value(), turbine_input.T_t_stag_cycle, places=0)
self.assertAlmostEqual(self.form.eta_t_stag_cycle.value(), turbine_input.eta_t_stag_cycle, places=2)
def test_separate_stages_averaging_comp_turbine_ngas_cool(self):
"""Равенство работы ступеней разности энатльпий на входе и на выходе ступеней."""
for i in range(len(self.comp_turbine_ngas_cool)):
logging.info('Stage %s' % (i + 1))
stage = self.comp_turbine_ngas_cool[i]
work_fluid_in = NaturalGasCombustionProducts()
work_fluid_out = NaturalGasCombustionProducts()
work_fluid_in.T = stage.T0_stag
work_fluid_in.alpha = stage.alpha_air_in
work_fluid_out.T = stage.T_st_stag
work_fluid_out.alpha = stage.alpha_air_in
enthalpy_in = work_fluid_in.c_p_av * (stage.T0_stag - work_fluid_in.T0)
enthalpy_out = work_fluid_out.c_p_av * (stage.T_st_stag - work_fluid_out.T0)
L_st = enthalpy_in - enthalpy_out
L_res = abs(L_st - stage.L_t) / stage.L_t
self.assertAlmostEqual(L_res, 0, places=3)
self.assertEqual(stage.work_fluid.T2, stage.T_st_stag)
def __init__(
self,
T_stag_in,
p_stag_in,
G_in,
G_fuel_in,
pi_t_stag,
T_stag_in_nom,
p_stag_in_nom,
G_in_nom,
pi_t_stag_nom,
eta_t_stag_nom,
eta_m=0.9,
work_fluid: IdealGas = NaturalGasCombustionProducts(),
precision=0.001,
):
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.pi_t_stag = pi_t_stag
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.pi_t_stag_nom = pi_t_stag_nom
self.eta_t_stag_nom = eta_t_stag_nom
self.eta_m = eta_m
self.work_fluid = work_fluid
self.precision = precision
self.pi_t_stag_rel = None
self.eta_t_stag_rel = None
self.eta_t_stag = None
self.fuel_content = None
self.alpha = None
self.ad_proc_res = None
self.T_stag_out_ad = None
self.H_stag = None
self.L = None
self.G_in_char = None
self.N = None
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 compute_cycle_and_nodes(
pi_c_stag=17,
stage_num_arr=[int(i) for i in np.linspace(9, 15, 7)],
H_t_rel1_arr=np.linspace(0.2, 0.35, 10),
H_t_rel_delta=-0.06,
c1_a_rel1_arr=np.linspace(0.45, 0.55, 10),
c1_a_rel_delta=0.1):
eta_stag_p_c = 0.87
eta_stag_p_ct = 0.89
eta_stag_p_pt = 0.89
res = 1
iter_num = 1
while res >= 0.001:
print('Iter %s' % iter_num)
iter_num += 1
solver, G_air, G_comp_turb, G_power_turb, G_fuel, eta_e = compute_cycle(
eta_stag_p_c, eta_stag_p_ct, eta_stag_p_pt)
n_ct = 11e3
n_pt = 7.8e3
inlet: Inlet = solver.get_sorted_unit_list()[1]
comp_cycle: Compressor = solver.get_sorted_unit_list()[2]
comp_turbine_cycle: Turbine = solver.get_sorted_unit_list()[5]
power_turbine_cycle: Turbine = solver.get_sorted_unit_list()[7]
sink: Sink = solver.get_sorted_unit_list()[3]
comb_chamber: CombustionChamber = solver.get_sorted_unit_list()[4]
outlet: Outlet = solver.get_sorted_unit_list()[8]
load: Load = solver.get_sorted_unit_list()[9]
comp = get_optimize_compressor(comp_cycle.p_stag_in,
comp_cycle.T_stag_in, G_air, n_ct,
pi_c_stag, stage_num_arr, H_t_rel1_arr,
H_t_rel_delta, c1_a_rel1_arr,
c1_a_rel_delta)
comp_turbine = TurbAvLine(turbine_type=TurbineType.WORK,
stage_number=2,
T_g_stag=comp_turbine_cycle.T_stag_in,
p_g_stag=comp_turbine_cycle.p_stag_in,
G_turbine=G_comp_turb,
G_fuel=G_fuel,
work_fluid=NaturalGasCombustionProducts(),
l1_D1_ratio=0.15,
n=n_ct,
T_t_stag_cycle=comp_turbine_cycle.T_stag_out,
eta_t_stag_cycle=comp_turbine_cycle.eta_stag,
alpha11=np.radians(14),
precision=0.0001,
eta_m=comp_turbine_cycle.eta_m,
gamma_in=np.radians(0),
gamma_out=np.radians(10),
H01_init=200e3,
c21_init=250)
comp_turbine.compute_geometry()
comp_turbine.compute_stages_gas_dynamics()
comp_turbine.compute_integrate_turbine_parameters()
power_turbine = TurbAvLine(
turbine_type=TurbineType.WORK,
stage_number=2,
T_g_stag=power_turbine_cycle.T_stag_in,
p_g_stag=power_turbine_cycle.p_stag_in,
G_turbine=G_power_turb,
G_fuel=G_fuel,
work_fluid=NaturalGasCombustionProducts(),
l1_D1_ratio=0.15,
n=n_pt,
eta_m=power_turbine_cycle.eta_m,
T_t_stag_cycle=power_turbine_cycle.T_stag_out,
eta_t_stag_cycle=power_turbine_cycle.eta_stag,
alpha11=np.radians(14),
precision=0.0001,
gamma_in=np.radians(0),
gamma_out=np.radians(15),
H01_init=200e3,
c21_init=250)
power_turbine.compute_geometry()
power_turbine.compute_stages_gas_dynamics()
power_turbine.compute_integrate_turbine_parameters()
eta_stag_p_c_res = abs(comp.eta_c_stag_p - eta_stag_p_c) / eta_stag_p_c
eta_stag_p_ct_res = abs(comp_turbine.eta_t_stag_p -
eta_stag_p_ct) / eta_stag_p_ct
eta_stag_p_pt_res = abs(power_turbine.eta_t_stag_p -
eta_stag_p_pt) / eta_stag_p_pt
eta_stag_p_c = comp.eta_c_stag_p
eta_stag_p_ct = comp_turbine.eta_t_stag_p
eta_stag_p_pt = power_turbine.eta_t_stag_p
res = max(eta_stag_p_c_res, eta_stag_p_pt_res, eta_stag_p_ct_res)
return solver, inlet, comp, sink, comb_chamber, comp_turbine, power_turbine, outlet, load, comp_cycle
def test_setting_input_data_from_turbine(self):
turbine = Turbine(turbine_type=TurbineType.Compressor,
stage_number=2,
T_g_stag=1450,
p_g_stag=400e3,
G_turbine=25,
G_fuel=1,
work_fluid=NaturalGasCombustionProducts(),
alpha_air=2.6,
l1_D1_ratio=0.20,
n=15e3,
T_t_stag_cycle=1050,
eta_t_stag_cycle=0.91,
alpha11=np.radians([17])[0],
auto_set_rho=False,
rho_list=[0.35, 0.45],
auto_compute_heat_drop=True,
H01_init=220e3,
c21_init=250,
gamma_in=np.radians([7])[0],
gamma_out=np.radians([8])[0],
precise_heat_drop=False)
turbine.geom[0].l1_b_sa_ratio = 2.1
turbine.geom[0].l2_b_rk_ratio = 2.5
turbine.geom[0].delta_a_b_sa_ratio = 0.4
turbine.geom[0].delta_a_b_rk_ratio = 0.35
turbine.geom[0].p_r_out_l1_ratio = 0.045
turbine.geom[0].p_r_in_l1_ratio = 0.055
turbine.geom[0].p_a_out_rel = 0.35
turbine.geom[0].p_a_in_rel = 0.25
turbine.geom[0].delta_r_rk_l2_ratio = 0.02
turbine.geom[0].phi = 0.95
turbine.geom[0].psi = 0.95
turbine.geom[0].g_lb = 0.01
turbine.geom[0].g_ld = 0.02
turbine.geom[0].g_lk = 0.015
turbine.geom[0].g_cool = 0.07
self.form.set_input_from_turbine(turbine)
self.assertEqual(turbine.stage_number, self.form.stage_number.value())
self.assertEqual(self.form.turbine_type.currentIndex(), 1)
self.assertEqual(self.form.fuel.currentIndex(), 1)
self.assertTrue(self.form.gamma_in_out.isChecked())
self.assertAlmostEqual(self.form.gamma1.value(), np.degrees(turbine.gamma_out), places=1)
self.assertAlmostEqual(self.form.gamma2.value(), np.degrees(turbine.gamma_in), places=1)
self.assertFalse(self.form.checkBox_rho_auto.isChecked())
self.assertTrue(self.form.checkBox_h0_auto.isChecked())
self.assertFalse(self.form.checkBox_precise_h0.isChecked())
self.assertAlmostEqual(self.form.H01_init.value(), turbine.H01_init / 1e3, places=1)
self.assertAlmostEqual(self.form.c21.value(), turbine.c21_init, places=1)
self.assertAlmostEqual(self.form.T_g_stag.value(), turbine.T_g_stag, 2)
self.assertAlmostEqual(self.form.p_g_stag.value(), turbine.p_g_stag / 1e6, places=3)
self.assertAlmostEqual(self.form.G_t.value(), turbine.G_turbine, places=2)
self.assertAlmostEqual(self.form.G_fuel.value(), turbine.G_fuel, places=2)
self.assertAlmostEqual(self.form.alpha11.value(), np.degrees(turbine.alpha11), places=1)
self.assertAlmostEqual(self.form.l1_D1_ratio.value(), turbine.l1_D1_ratio, places=2)
self.assertAlmostEqual(self.form.n.value(), turbine.n, places=0)
self.assertAlmostEqual(self.form.T_t_stag_cycle.value(), turbine.T_t_stag_cycle, places=0)
self.assertAlmostEqual(self.form.eta_t_stag_cycle.value(), turbine.eta_t_stag_cycle, places=2)
for i in range(turbine.stage_number):
stage_data: StageDataWidget = self.form.stackedWidget.widget(i)
geom = turbine.geom[i]
self.assertAlmostEqual(stage_data.l1_b_sa_ratio.value(), geom.l1_b_sa_ratio, places=2)
self.assertAlmostEqual(stage_data.l2_b_rk_ratio.value(), geom.l2_b_rk_ratio, places=2)
self.assertAlmostEqual(stage_data.delta_a_b_sa_ratio.value(), geom.delta_a_b_sa_ratio, places=2)
self.assertAlmostEqual(stage_data.delta_a_b_rk_ratio.value(), geom.delta_a_b_rk_ratio, places=2)
self.assertAlmostEqual(stage_data.p_r_out_l1_ratio.value(), geom.p_r_out_l1_ratio, places=2)
self.assertAlmostEqual(stage_data.p_r_in_l1_ratio.value(), geom.p_r_in_l1_ratio, places=2)
self.assertAlmostEqual(stage_data.p_a_out_rel.value(), geom.p_a_out_rel, places=2)
self.assertAlmostEqual(stage_data.p_a_in_rel.value(), geom.p_a_in_rel, places=2)
self.assertAlmostEqual(stage_data.delta_r_rel.value(), geom.delta_r_rk_l2_ratio, places=2)
self.assertAlmostEqual(stage_data.phi.value(), geom.phi, places=2)
self.assertAlmostEqual(stage_data.psi.value(), geom.psi, places=2)
self.assertAlmostEqual(stage_data.g_lb.value(), geom.g_lb, places=2)
self.assertAlmostEqual(stage_data.g_ld.value(), geom.g_ld, places=2)
self.assertAlmostEqual(stage_data.g_lk.value(), geom.g_lk, places=2)
self.assertAlmostEqual(stage_data.g_cool.value(), geom.g_cool, places=2)
self.assertAlmostEqual(stage_data.T_cool.value(), geom.T_cool, places=1)
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)
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.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.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()