Source code for RCAIDE.Library.Components.Powertrain.Converters.Combustor
# RCAIDE/Library/Components/Propulsors/Converters/Combustor.py
# (c) Copyright 2023 Aerospace Research Community LLC
#
# Created: Feb 2024, M. Clarke
# ----------------------------------------------------------------------------------------------------------------------
# IMPORT
# ----------------------------------------------------------------------------------------------------------------------
# RCAIDE imports
import RCAIDE
from .Converter import Converter
from RCAIDE.Library.Methods.Powertrain.Converters.Combustor.append_combustor_conditions import append_combustor_conditions
from RCAIDE.Library.Attributes.Gases.Air import Air
# ----------------------------------------------------------------------------------------------------------------------
# Combustor
# ----------------------------------------------------------------------------------------------------------------------
[docs]
class Combustor(Converter):
"""
A combustor component model for gas turbine engines that simulates the combustion process.
Attributes
----------
tag : str
Identifier for the combustor. Default is 'Combustor'.
alphac : float
Combustor entrance angle [rad]. Default is 0.0.
turbine_inlet_temperature : float
Temperature at turbine inlet [K]. Default is 1500.
area_ratio : float
Ratio of combustor exit to inlet area. Default is 1.0.
axial_fuel_velocity_ratio : float
Ratio of axial fuel velocity to inlet velocity. Default is 0.0.
fuel_velocity_ratio : float
Ratio of fuel velocity to inlet velocity. Default is 0.0.
burner_drag_coefficient : float
Drag coefficient of the burner. Default is 0.0.
absolute_sensible_enthalpy : float
Absolute sensible enthalpy [J/kg]. Default is 0.0.
diameter : float
Combustor diameter [m]. Default is 0.2.
length : float
Combustor length [m]. Default is 0.3.
fuel_equivalency_ratio : float
Fuel-to-air equivalency ratio. Default is 0.3.
number_of_combustors : int
Number of combustor cans. Default is 30.
f_air_PZ : float
Fraction of total air entering Primary Zone. Default is 0.18.
FAR_st : float
Stoichiometric Fuel to Air ratio. Default is 0.068.
N_comb : int
Number of can-annular combustors. Default is 10.
N_PZ : int
Number of PSR in the Primary Zone. Default is 8.
A_PZ : float
Primary Zone cross-sectional area [m²]. Default is 0.15.
L_PZ : float
Primary Zone length [m]. Default is 0.0153.
N_SZ : int
Number of dilution air inlets in the Secondary Zone. Default is 3.
A_SZ : float
Secondary Zone cross-sectional area [m²]. Default is 0.15.
L_SZ : float
Secondary Zone length [m]. Default is 0.075.
phi_SZ : float
Equivalence Ratio in the Secondary Zone. Default is 0.2.
S_PZ : float
Mixing parameter in the Primary Zone. Default is 0.6.
F_SC : float
Fuel scaler. Default is 0.425.
number_of_assigned_PSR_1st_mixers : int
Number of assigned PSRs to first row mixers. Default is 2.
number_of_assigned_PSR_2nd_mixers : int
Number of assigned mixers to second row mixers. Default is 2.
Notes
-----
The Combustor class models the combustion process in gas turbine engines,
splitting the combustor into primary and secondary zones. It uses a Chemical
Reactor Network (CRN) approach with Perfectly Stirred Reactors (PSR) and Plug Flow Reactors (PFR) for
modeling the combustion process.
**Definitions**
'PSR'
Perfectly Stirred Reactor - A reactor model assuming perfect mixing
'PZ'
Primary Zone - Initial combustion region
'SZ'
Secondary Zone - Dilution region where the combustion is completed
'FAR'
Fuel-to-Air Ratio
'PFR'
Plug Flow Reactor - A reactor model assuming no mixing in axial direction
See Also
--------
RCAIDE.Library.Methods.Emissions.Chemical_Reaction_Network.evaluate_cantera
"""
def __defaults__(self):
"""This sets the default values for the component to function.
Assumptions:
None
Source:
None
"""
self.tag = 'Combustor'
self.alphac = 0.0
self.turbine_inlet_temperature = 1500
self.area_ratio = 1.0
self.axial_fuel_velocity_ratio = 0.0
self.fuel_velocity_ratio = 0.0
self.burner_drag_coefficient = 0.0
self.absolute_sensible_enthalpy = 0.0
self.tag = 'CFM56-7B' # [-] Combustor tag
self.volume = 0.0023 # [m**3] Combustor volume
self.length = 0.2 # [m] Combustor Length
self.number_of_combustors = 1 # [-] Number of Combustors for one engine
self.F_SC = 1 # [-] Fuel scale factor
self.N_PZ = 21 # [-] Number of PSR in the Primary Zone
self.L_PZ = 0.05 # [m] Primary Zone length
self.S_PZ = 0.39 # [-] Mixing parameter in the Primary Zone
self.design_equivalence_ratio_PZ = 1.71 # [-] Design Equivalence Ratio in Primary Zone at Maximum Throttle
self.N_SZ = 500 # [-] Number of discritizations in the Secondary Zone
self.f_SM = 0.6 # [-] Slow mode fraction
self.l_SA_SM = 0.4 # [-] Secondary air length fraction (of L_SZ) in slow mode
self.l_SA_FM = 0.05 # [-] Secondary air length fraction (of L_SZ) in fast mode
self.l_DA_start = 0.95 # [-] Dilution air start length fraction (of L_SZ)
self.l_DA_end = 1.0 # [-] Dilution air end length fraction (of L_SZ)
self.joint_mixing_fraction = 0.6 # [-] Joint mixing fraction
self.design_equivalence_ratio_SZ = 0.61 # [-] Design Equivalence Ratio in Secondary Zone at Maximum Throttle
self.air_mass_flow_rate_take_off = 40 # [kg/s] Air mass flow rate at take-off
self.fuel_to_air_ratio_take_off = 0.025 # [-] Fuel to air ratio at take-off
self.air_data = Air() # [-] Air object
self.fuel_data = RCAIDE.Library.Attributes.Propellants.Jet_A1() # [-] Fuel object
[docs]
def append_operating_conditions(self,segment,energy_conditions,noise_conditions=None):
"""
Appends operating conditions to the combustor.
"""
append_combustor_conditions(self,segment,energy_conditions)
return
