Module huracan.components.channels
Engine channels
Expand source code
# SPDX-FileCopyrightText: © 2024 Antonio López Rivera <antonlopezr99@gmail.com>
# SPDX-License-Identifier: vGPL-3.0-only
"""
Engine channels
---------------
"""
from huracan.engine import component
class intake(component):
"""
Intake
------
Airflow fed directly to engine.
"""
def __init__(self,
eta=1,
PI=1,
TAU=1):
"""
:type eta: float
:type PI: float
:type TAU: float
"""
self.eta = eta
self.PI = PI
self.TAU = TAU
def tf(self, gas):
return gas.diffusion(eta=self.eta, PI=self.PI, TAU=self.TAU)
class inlet(intake):
"""
Inlet
-----
Adiabatic diffusion.
"""
def __init__(self,
eta=None,
PI=None,
TAU=None):
"""
:type eta: float
:type PI: float
:type TAU: float
"""
super().__init__(eta=eta,
PI=PI,
TAU=TAU)
assert not isinstance(eta, type(None)) or not isinstance(PI, type(None)) or not isinstance(TAU, type(None))
class bleed_duct(component):
"""
Bleed duct
----------
"""
def __init__(self,
t01,
eta,
PI=1,
):
"""
:param t01: Temperature after the bleed duct.
:param eta: Isentropic efficiency.
:param PI: Pressure ratio.
"""
self.t01 = t01
self.eta = eta
self.PI = PI
def tf(self, gas):
dt = self.t01 - gas.t0
self.Q_out = dt*gas.mf*gas.cp(gas.t0) / self.eta
return gas.heat_exchange(eta=self.eta,
PI=self.PI,
cp=gas.cp(gas.t0),
Q_ex=self.Q_out,
)
class nozzle(component):
"""
Nozzle
------
Adiabatic expansion.
"""
def __init__(self,
eta,
PI=None
):
"""
:type eta: float
:type PI: float
"""
self.eta = eta
self.PI = PI
self.choked = False
def tf(self, gas):
return gas.expansion(eta=self.eta, PI=self.pi(gas), TAU=None)
def pi(self, gas):
"""
Nozzle pressure ratio.
If the nozzle pressure ratio is not provided, it is set as
the ratio between the gas total pressure before the nozzle
and the ambient pressure.
If the inverse of the nozzle pressure ratio is larger than
the critical inverse pressure ratio, the flow is choked and
the nozzle pressure ratio will not exceed the critical pressure
ratio.
"""
inv_PI = gas.p0/gas.p_0 if isinstance(self.PI, type(None)) else 1/self.PI
if inv_PI > self.inv_pi_crit(gas):
PI = 1/self.inv_pi_crit(gas)
self.choked = True
else:
PI = 1/inv_PI
return PI
def inv_pi_crit(self, gas):
"""
Inverse critical pressure ratio.
Ratio of the pressure **before** the inlet over that
**after** the inlet (inversely to the widely used pressure
ratio), starting from which supersonic flow happens in the
expansion process, causing the nozzle to become choked.
With a choked nozzle the expansion of the gas is incomplete,
with a maximum total pressure ratio in the nozzle equal to
1/PI_crit
"""
k = gas.k(gas.t0)
return 1/(1-1/self.eta*((k-1)/(k+1)))**(k/(k-1))Classes
class bleed_duct (t01, eta, PI=1)-
Bleed Duct
:param t01: Temperature after the bleed duct. :param eta: Isentropic efficiency. :param PI: Pressure ratio.
Expand source code
class bleed_duct(component): """ Bleed duct ---------- """ def __init__(self, t01, eta, PI=1, ): """ :param t01: Temperature after the bleed duct. :param eta: Isentropic efficiency. :param PI: Pressure ratio. """ self.t01 = t01 self.eta = eta self.PI = PI def tf(self, gas): dt = self.t01 - gas.t0 self.Q_out = dt*gas.mf*gas.cp(gas.t0) / self.eta return gas.heat_exchange(eta=self.eta, PI=self.PI, cp=gas.cp(gas.t0), Q_ex=self.Q_out, )Ancestors
Methods
def tf(self, gas)-
Expand source code
def tf(self, gas): dt = self.t01 - gas.t0 self.Q_out = dt*gas.mf*gas.cp(gas.t0) / self.eta return gas.heat_exchange(eta=self.eta, PI=self.PI, cp=gas.cp(gas.t0), Q_ex=self.Q_out, )
class inlet (eta=None, PI=None, TAU=None)-
Inlet
Adiabatic diffusion.
:type eta: float :type PI: float :type TAU: float
Expand source code
class inlet(intake): """ Inlet ----- Adiabatic diffusion. """ def __init__(self, eta=None, PI=None, TAU=None): """ :type eta: float :type PI: float :type TAU: float """ super().__init__(eta=eta, PI=PI, TAU=TAU) assert not isinstance(eta, type(None)) or not isinstance(PI, type(None)) or not isinstance(TAU, type(None))Ancestors
class intake (eta=1, PI=1, TAU=1)-
Intake
Airflow fed directly to engine.
:type eta: float :type PI: float :type TAU: float
Expand source code
class intake(component): """ Intake ------ Airflow fed directly to engine. """ def __init__(self, eta=1, PI=1, TAU=1): """ :type eta: float :type PI: float :type TAU: float """ self.eta = eta self.PI = PI self.TAU = TAU def tf(self, gas): return gas.diffusion(eta=self.eta, PI=self.PI, TAU=self.TAU)Ancestors
Subclasses
Methods
def tf(self, gas)-
Expand source code
def tf(self, gas): return gas.diffusion(eta=self.eta, PI=self.PI, TAU=self.TAU)
class nozzle (eta, PI=None)-
Nozzle
Adiabatic expansion.
:type eta: float :type PI: float
Expand source code
class nozzle(component): """ Nozzle ------ Adiabatic expansion. """ def __init__(self, eta, PI=None ): """ :type eta: float :type PI: float """ self.eta = eta self.PI = PI self.choked = False def tf(self, gas): return gas.expansion(eta=self.eta, PI=self.pi(gas), TAU=None) def pi(self, gas): """ Nozzle pressure ratio. If the nozzle pressure ratio is not provided, it is set as the ratio between the gas total pressure before the nozzle and the ambient pressure. If the inverse of the nozzle pressure ratio is larger than the critical inverse pressure ratio, the flow is choked and the nozzle pressure ratio will not exceed the critical pressure ratio. """ inv_PI = gas.p0/gas.p_0 if isinstance(self.PI, type(None)) else 1/self.PI if inv_PI > self.inv_pi_crit(gas): PI = 1/self.inv_pi_crit(gas) self.choked = True else: PI = 1/inv_PI return PI def inv_pi_crit(self, gas): """ Inverse critical pressure ratio. Ratio of the pressure **before** the inlet over that **after** the inlet (inversely to the widely used pressure ratio), starting from which supersonic flow happens in the expansion process, causing the nozzle to become choked. With a choked nozzle the expansion of the gas is incomplete, with a maximum total pressure ratio in the nozzle equal to 1/PI_crit """ k = gas.k(gas.t0) return 1/(1-1/self.eta*((k-1)/(k+1)))**(k/(k-1))Ancestors
Methods
def inv_pi_crit(self, gas)-
Inverse critical pressure ratio.
Ratio of the pressure before the inlet over that after the inlet (inversely to the widely used pressure ratio), starting from which supersonic flow happens in the expansion process, causing the nozzle to become choked.
With a choked nozzle the expansion of the gas is incomplete, with a maximum total pressure ratio in the nozzle equal to
1/PI_critExpand source code
def inv_pi_crit(self, gas): """ Inverse critical pressure ratio. Ratio of the pressure **before** the inlet over that **after** the inlet (inversely to the widely used pressure ratio), starting from which supersonic flow happens in the expansion process, causing the nozzle to become choked. With a choked nozzle the expansion of the gas is incomplete, with a maximum total pressure ratio in the nozzle equal to 1/PI_crit """ k = gas.k(gas.t0) return 1/(1-1/self.eta*((k-1)/(k+1)))**(k/(k-1)) def pi(self, gas)-
Nozzle pressure ratio.
If the nozzle pressure ratio is not provided, it is set as the ratio between the gas total pressure before the nozzle and the ambient pressure. If the inverse of the nozzle pressure ratio is larger than the critical inverse pressure ratio, the flow is choked and the nozzle pressure ratio will not exceed the critical pressure ratio.
Expand source code
def pi(self, gas): """ Nozzle pressure ratio. If the nozzle pressure ratio is not provided, it is set as the ratio between the gas total pressure before the nozzle and the ambient pressure. If the inverse of the nozzle pressure ratio is larger than the critical inverse pressure ratio, the flow is choked and the nozzle pressure ratio will not exceed the critical pressure ratio. """ inv_PI = gas.p0/gas.p_0 if isinstance(self.PI, type(None)) else 1/self.PI if inv_PI > self.inv_pi_crit(gas): PI = 1/self.inv_pi_crit(gas) self.choked = True else: PI = 1/inv_PI return PI def tf(self, gas)-
Expand source code
def tf(self, gas): return gas.expansion(eta=self.eta, PI=self.pi(gas), TAU=None)