Module huracan.components.power.combustion
Combustion power plants
Expand source code
# SPDX-FileCopyrightText: © 2024 Antonio López Rivera <antonlopezr99@gmail.com>
# SPDX-License-Identifier: GPL-3.0-only
"""
Combustion power plants
-----------------------
"""
from copy import deepcopy
from huracan.engine import component
from huracan.components.power import plant
class combustor(component):
"""
Combustor
---------
Constant pressure heat addition.
"""
def __init__(self,
fuel,
eta,
PI=1,
t01=None,
):
"""
The total pressure and temperature
after the combustor are calculated
based on:
- The fuel mass flow (attribute of
the input fuel class instance) if provided,
if the heat added if equal or larger than
that required by the turbines.
-> Heat addition from input fuel mass flow
- The total temperature of the gas
at the exit of the combustion chamber t01
if provided, if the heat added if equal or
larger than that required by the turbines.
-> Heat addition so as to reach t01
:param fuel: Instance of fuel class.
:param eta: Isentropic efficiency.
:param t01: Temperature after the combustion chamber.
:type fuel: fuel
:type t01: float
"""
self.fuel = fuel
self.eta = eta
self.PI = PI
self.t01 = t01
def tf(self, gas):
"""
By considering combustion happens at low temperature (that
of the gas before it enters the combustion chamber), an estimate
of the total temperature of the gas when it exits the combustion
chamber is obtained.
This total temperature is then assumed to be the temperature
at which the combustion process takes place.
"""
assert hasattr(self, 'fmf'), \
'Component incorporating combustor has no fuel mass flow method implemented.'
self.fmf(gas)
self.Q = self.fuel.mf*self.fuel.LHV # Heat added to the flow
approx_process_t = deepcopy(gas).heat_exchange(eta=self.eta,
PI=self.PI,
cp=gas.cp(gas.t0),
Q_ex=self.Q).t01
return gas.heat_exchange(eta=self.eta,
PI=self.PI,
cp=gas.cp(approx_process_t),
Q_ex=self.Q)
def mf_dt(self, dt, gas):
"""
Fuel mass flow from a required change in total temperature.
"""
gas_cp = gas.cp(self.t01) # Heat addition happens at high temperature
return dt*gas.mf*gas_cp/(self.eta*self.fuel.LHV - dt*gas_cp)
class combustion_chamber(plant, combustor):
"""
Combustion chamber
------------------
Constant pressure heat addition.
"""
def __init__(self,
fuel,
eta,
PI=1,
t01=None,
):
"""
The total pressure and temperature
after the combustion chamber are calculated
based on:
- The heat required by all downstream
turbines (work which the turbines of the
engine must subtract from the flow).
-> Heat addition so as to feed the known
energy use.
- The fuel mass flow (attribute of
the input fuel class instance) if provided,
if the heat added if equal or larger than
that required by the turbines.
-> Heat addition from input fuel mass flow
- The total temperature of the gas
at the exit of the combustion chamber t01
if provided, if the heat added if equal or
larger than that required by the turbines.
-> Heat addition so as to reach t01
:param fuel: Instance of fuel class.
:param eta: Isentropic efficiency.
:param t01: Temperature after the combustion chamber.
:type fuel: fuel
:type t01: float
"""
super().__init__(fuel=fuel,
eta=eta,
PI=PI,
t01=t01)
def fmf(self, gas):
"""
At the time of execution, the fuel mass flow is
determined based on:
- The heat required by the turbines (minimum mass flow)
- The fuel mass flow if provided, if larger than the
minimum mass flow
- The total temperature of the gas at the exit of
the combustion chamber t01 if provided, if the
required mass flow for it is larger than the
minimum mass flow
"""
mf_min = self.mf_qr(self.Q_min(downstream=self.stream.downstream))
if not isinstance(self.t01, type(None)):
mf_t01 = self.mf_dt(dt=self.t01 - gas.t0, gas=gas)
self.fuel.mf = mf_t01 if mf_t01 > mf_min else mf_min
elif not isinstance(self.fuel.mf, type(None)):
self.fuel.mf = self.fuel.mf if self.fuel.mf > mf_min else self.fuel.mf
else:
self.fuel.mf = mf_min
gas += self.fuel
def mf_qr(self, qr):
"""
Fuel mass flow from heat addition required.
"""
return qr/(self.eta*self.fuel.LHV)
class afterburner(combustor):
"""
Afterburner or Reheater
-----------------------
Constant pressure heat addition.
"""
def __init__(self,
fuel,
eta,
PI=1,
t01=None):
"""
The total pressure and temperature
after the afterburner are calculated
based on:
- The fuel mass flow (attribute of
the input fuel class instance) if provided,
if the heat added if equal or larger than
that required by the turbines.
-> Heat addition from input fuel mass flow
- The total temperature of the gas
at the exit of the combustion chamber t01
if provided, if the heat added if equal or
larger than that required by the turbines.
-> Heat addition so as to reach t01
:param fuel: Instance of fuel class.
:param eta: Isentropic efficiency.
:param t01: Temperature after the combustion chamber.
:type fuel: fuel
:type t01: float
"""
super().__init__(fuel=fuel,
eta=eta,
PI=PI,
t01=t01)
def fmf(self, gas):
"""
At the time of execution, the fuel mass flow is
determined based on:
- The fuel mass flow if provided, if larger than the
minimum mass flow
- The total temperature of the gas at the exit of
the combustion chamber t01 if provided, if the
required mass flow for it is larger than the
minimum mass flow
"""
assert not isinstance(self.t01, type(None)) or not isinstance(self.fuel.mf, type(None)), \
'Afterburner: neither the fuel mass flow nor the temperature t01 after the afterburner have been' \
'provided. Input either one in the initialization of your afterburner instance to proceed.'
if not isinstance(self.t01, type(None)):
self.fuel.mf = self.mf_dt(dt=self.t01 - gas.t0, gas=gas)
elif not isinstance(self.fuel.mf, type(None)):
self.fuel.mf = self.fuel.mf
gas += self.fuelClasses
class afterburner (fuel, eta, PI=1, t01=None)-
Afterburner Or Reheater
Constant pressure heat addition.
The total pressure and temperature after the afterburner are calculated based on:
-
The fuel mass flow (attribute of the input fuel class instance) if provided, if the heat added if equal or larger than that required by the turbines. -> Heat addition from input fuel mass flow
-
The total temperature of the gas at the exit of the combustion chamber t01 if provided, if the heat added if equal or larger than that required by the turbines. -> Heat addition so as to reach t01
:param fuel: Instance of fuel class. :param eta: Isentropic efficiency. :param t01: Temperature after the combustion chamber.
:type fuel: fuel :type t01: float
Expand source code
class afterburner(combustor): """ Afterburner or Reheater ----------------------- Constant pressure heat addition. """ def __init__(self, fuel, eta, PI=1, t01=None): """ The total pressure and temperature after the afterburner are calculated based on: - The fuel mass flow (attribute of the input fuel class instance) if provided, if the heat added if equal or larger than that required by the turbines. -> Heat addition from input fuel mass flow - The total temperature of the gas at the exit of the combustion chamber t01 if provided, if the heat added if equal or larger than that required by the turbines. -> Heat addition so as to reach t01 :param fuel: Instance of fuel class. :param eta: Isentropic efficiency. :param t01: Temperature after the combustion chamber. :type fuel: fuel :type t01: float """ super().__init__(fuel=fuel, eta=eta, PI=PI, t01=t01) def fmf(self, gas): """ At the time of execution, the fuel mass flow is determined based on: - The fuel mass flow if provided, if larger than the minimum mass flow - The total temperature of the gas at the exit of the combustion chamber t01 if provided, if the required mass flow for it is larger than the minimum mass flow """ assert not isinstance(self.t01, type(None)) or not isinstance(self.fuel.mf, type(None)), \ 'Afterburner: neither the fuel mass flow nor the temperature t01 after the afterburner have been' \ 'provided. Input either one in the initialization of your afterburner instance to proceed.' if not isinstance(self.t01, type(None)): self.fuel.mf = self.mf_dt(dt=self.t01 - gas.t0, gas=gas) elif not isinstance(self.fuel.mf, type(None)): self.fuel.mf = self.fuel.mf gas += self.fuelAncestors
Methods
def fmf(self, gas)-
At the time of execution, the fuel mass flow is determined based on:
- The fuel mass flow if provided, if larger than the minimum mass flow
- The total temperature of the gas at the exit of the combustion chamber t01 if provided, if the required mass flow for it is larger than the minimum mass flow
Expand source code
def fmf(self, gas): """ At the time of execution, the fuel mass flow is determined based on: - The fuel mass flow if provided, if larger than the minimum mass flow - The total temperature of the gas at the exit of the combustion chamber t01 if provided, if the required mass flow for it is larger than the minimum mass flow """ assert not isinstance(self.t01, type(None)) or not isinstance(self.fuel.mf, type(None)), \ 'Afterburner: neither the fuel mass flow nor the temperature t01 after the afterburner have been' \ 'provided. Input either one in the initialization of your afterburner instance to proceed.' if not isinstance(self.t01, type(None)): self.fuel.mf = self.mf_dt(dt=self.t01 - gas.t0, gas=gas) elif not isinstance(self.fuel.mf, type(None)): self.fuel.mf = self.fuel.mf gas += self.fuel
Inherited members
-
class combustion_chamber (fuel, eta, PI=1, t01=None)-
Combustion Chamber
Constant pressure heat addition.
The total pressure and temperature after the combustion chamber are calculated based on:
-
The heat required by all downstream turbines (work which the turbines of the engine must subtract from the flow). -> Heat addition so as to feed the known energy use.
-
The fuel mass flow (attribute of the input fuel class instance) if provided, if the heat added if equal or larger than that required by the turbines. -> Heat addition from input fuel mass flow
-
The total temperature of the gas at the exit of the combustion chamber t01 if provided, if the heat added if equal or larger than that required by the turbines. -> Heat addition so as to reach t01
:param fuel: Instance of fuel class. :param eta: Isentropic efficiency. :param t01: Temperature after the combustion chamber.
:type fuel: fuel :type t01: float
Expand source code
class combustion_chamber(plant, combustor): """ Combustion chamber ------------------ Constant pressure heat addition. """ def __init__(self, fuel, eta, PI=1, t01=None, ): """ The total pressure and temperature after the combustion chamber are calculated based on: - The heat required by all downstream turbines (work which the turbines of the engine must subtract from the flow). -> Heat addition so as to feed the known energy use. - The fuel mass flow (attribute of the input fuel class instance) if provided, if the heat added if equal or larger than that required by the turbines. -> Heat addition from input fuel mass flow - The total temperature of the gas at the exit of the combustion chamber t01 if provided, if the heat added if equal or larger than that required by the turbines. -> Heat addition so as to reach t01 :param fuel: Instance of fuel class. :param eta: Isentropic efficiency. :param t01: Temperature after the combustion chamber. :type fuel: fuel :type t01: float """ super().__init__(fuel=fuel, eta=eta, PI=PI, t01=t01) def fmf(self, gas): """ At the time of execution, the fuel mass flow is determined based on: - The heat required by the turbines (minimum mass flow) - The fuel mass flow if provided, if larger than the minimum mass flow - The total temperature of the gas at the exit of the combustion chamber t01 if provided, if the required mass flow for it is larger than the minimum mass flow """ mf_min = self.mf_qr(self.Q_min(downstream=self.stream.downstream)) if not isinstance(self.t01, type(None)): mf_t01 = self.mf_dt(dt=self.t01 - gas.t0, gas=gas) self.fuel.mf = mf_t01 if mf_t01 > mf_min else mf_min elif not isinstance(self.fuel.mf, type(None)): self.fuel.mf = self.fuel.mf if self.fuel.mf > mf_min else self.fuel.mf else: self.fuel.mf = mf_min gas += self.fuel def mf_qr(self, qr): """ Fuel mass flow from heat addition required. """ return qr/(self.eta*self.fuel.LHV)Ancestors
Methods
def fmf(self, gas)-
At the time of execution, the fuel mass flow is determined based on:
- The heat required by the turbines (minimum mass flow)
- The fuel mass flow if provided, if larger than the minimum mass flow
- The total temperature of the gas at the exit of the combustion chamber t01 if provided, if the required mass flow for it is larger than the minimum mass flow
Expand source code
def fmf(self, gas): """ At the time of execution, the fuel mass flow is determined based on: - The heat required by the turbines (minimum mass flow) - The fuel mass flow if provided, if larger than the minimum mass flow - The total temperature of the gas at the exit of the combustion chamber t01 if provided, if the required mass flow for it is larger than the minimum mass flow """ mf_min = self.mf_qr(self.Q_min(downstream=self.stream.downstream)) if not isinstance(self.t01, type(None)): mf_t01 = self.mf_dt(dt=self.t01 - gas.t0, gas=gas) self.fuel.mf = mf_t01 if mf_t01 > mf_min else mf_min elif not isinstance(self.fuel.mf, type(None)): self.fuel.mf = self.fuel.mf if self.fuel.mf > mf_min else self.fuel.mf else: self.fuel.mf = mf_min gas += self.fuel def mf_qr(self, qr)-
Fuel mass flow from heat addition required.
Expand source code
def mf_qr(self, qr): """ Fuel mass flow from heat addition required. """ return qr/(self.eta*self.fuel.LHV)
Inherited members
-
class combustor (fuel, eta, PI=1, t01=None)-
Combustor
Constant pressure heat addition.
The total pressure and temperature after the combustor are calculated based on:
-
The fuel mass flow (attribute of the input fuel class instance) if provided, if the heat added if equal or larger than that required by the turbines. -> Heat addition from input fuel mass flow
-
The total temperature of the gas at the exit of the combustion chamber t01 if provided, if the heat added if equal or larger than that required by the turbines. -> Heat addition so as to reach t01
:param fuel: Instance of fuel class. :param eta: Isentropic efficiency. :param t01: Temperature after the combustion chamber.
:type fuel: fuel :type t01: float
Expand source code
class combustor(component): """ Combustor --------- Constant pressure heat addition. """ def __init__(self, fuel, eta, PI=1, t01=None, ): """ The total pressure and temperature after the combustor are calculated based on: - The fuel mass flow (attribute of the input fuel class instance) if provided, if the heat added if equal or larger than that required by the turbines. -> Heat addition from input fuel mass flow - The total temperature of the gas at the exit of the combustion chamber t01 if provided, if the heat added if equal or larger than that required by the turbines. -> Heat addition so as to reach t01 :param fuel: Instance of fuel class. :param eta: Isentropic efficiency. :param t01: Temperature after the combustion chamber. :type fuel: fuel :type t01: float """ self.fuel = fuel self.eta = eta self.PI = PI self.t01 = t01 def tf(self, gas): """ By considering combustion happens at low temperature (that of the gas before it enters the combustion chamber), an estimate of the total temperature of the gas when it exits the combustion chamber is obtained. This total temperature is then assumed to be the temperature at which the combustion process takes place. """ assert hasattr(self, 'fmf'), \ 'Component incorporating combustor has no fuel mass flow method implemented.' self.fmf(gas) self.Q = self.fuel.mf*self.fuel.LHV # Heat added to the flow approx_process_t = deepcopy(gas).heat_exchange(eta=self.eta, PI=self.PI, cp=gas.cp(gas.t0), Q_ex=self.Q).t01 return gas.heat_exchange(eta=self.eta, PI=self.PI, cp=gas.cp(approx_process_t), Q_ex=self.Q) def mf_dt(self, dt, gas): """ Fuel mass flow from a required change in total temperature. """ gas_cp = gas.cp(self.t01) # Heat addition happens at high temperature return dt*gas.mf*gas_cp/(self.eta*self.fuel.LHV - dt*gas_cp)Ancestors
Subclasses
Methods
def mf_dt(self, dt, gas)-
Fuel mass flow from a required change in total temperature.
Expand source code
def mf_dt(self, dt, gas): """ Fuel mass flow from a required change in total temperature. """ gas_cp = gas.cp(self.t01) # Heat addition happens at high temperature return dt*gas.mf*gas_cp/(self.eta*self.fuel.LHV - dt*gas_cp) def tf(self, gas)-
By considering combustion happens at low temperature (that of the gas before it enters the combustion chamber), an estimate of the total temperature of the gas when it exits the combustion chamber is obtained. This total temperature is then assumed to be the temperature at which the combustion process takes place.
Expand source code
def tf(self, gas): """ By considering combustion happens at low temperature (that of the gas before it enters the combustion chamber), an estimate of the total temperature of the gas when it exits the combustion chamber is obtained. This total temperature is then assumed to be the temperature at which the combustion process takes place. """ assert hasattr(self, 'fmf'), \ 'Component incorporating combustor has no fuel mass flow method implemented.' self.fmf(gas) self.Q = self.fuel.mf*self.fuel.LHV # Heat added to the flow approx_process_t = deepcopy(gas).heat_exchange(eta=self.eta, PI=self.PI, cp=gas.cp(gas.t0), Q_ex=self.Q).t01 return gas.heat_exchange(eta=self.eta, PI=self.PI, cp=gas.cp(approx_process_t), Q_ex=self.Q)
-