Source code for RCAIDE.Library.Components.Powertrain.Propulsors.Turbofan
# RCAIDE/Library/Components/Propulsors/Turbofan.py
#
#
# Created: Mar 2024, M. Clarke
# ----------------------------------------------------------------------------------------------------------------------
# IMPORT
# ----------------------------------------------------------------------------------------------------------------------
# RCAIDE imports
from RCAIDE.Framework.Core import Data
from . import Propulsor
from RCAIDE.Library.Methods.Powertrain.Propulsors.Turbofan .append_turbofan_conditions import append_turbofan_conditions
from RCAIDE.Library.Methods.Powertrain.Propulsors.Turbofan .compute_turbofan_performance import compute_turbofan_performance, reuse_stored_turbofan_data
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# Fan Component
# ----------------------------------------------------------------------------------------------------------------------
[docs]
class Turbofan(Propulsor):
"""
A turbofan propulsion system model that simulates the performance of a turbofan engine.
Attributes
----------
tag : str
Identifier for the turbofan engine. Default is 'Turbofan'.
nacelle : Component
Nacelle component of the engine. Default is None.
fan : Component
Fan component of the engine. Default is None.
ram : Component
Ram inlet component. Default is None.
inlet_nozzle : Component
Inlet nozzle component. Default is None.
low_pressure_compressor : Component
Low pressure compressor component. Default is None.
high_pressure_compressor : Component
High pressure compressor component. Default is None.
low_pressure_turbine : Component
Low pressure turbine component. Default is None.
high_pressure_turbine : Component
High pressure turbine component. Default is None.
combustor : Component
Combustor component. Default is None.
core_nozzle : Component
Core exhaust nozzle component. Default is None.
fan_nozzle : Component
Fan exhaust nozzle component. Default is None.
active_crypgenic_tanks_tanks : None or list
Collection of active cryogenoc tanks. Default is None.
diameter : float
Diameter of the engine [m]. Default is 0.0.
length : float
Length of the engine [m]. Default is 0.0.
height : float
Engine centerline height above the ground plane [m]. Default is 0.5.
exa : float
Distance from fan face to fan exit normalized by fan diameter. Default is 1.0.
plug_diameter : float
Diameter of the engine plug [m]. Default is 0.1.
geometry_xe : float
Installation effects geometry parameter. Default is 1.0.
geometry_ye : float
Installation effects geometry parameter. Default is 1.0.
geometry_Ce : float
Installation effects geometry parameter. Default is 2.0.
bypass_ratio : float
Engine bypass ratio. Default is 0.0.
design_isa_deviation : float
ISA temperature deviation at design point [K]. Default is 0.0.
design_altitude : float
Design altitude of the engine [m]. Default is 0.0.
specific_fuel_consumption_reduction_factor : float
Specific fuel consumption adjustment factor (Less than 1 is a reduction). Default is 0.0.
compressor_nondimensional_massflow : float
Non-dimensional mass flow through the compressor. Default is 0.0.
reference_temperature : float
Reference temperature for calculations [K]. Default is 288.15.
reference_pressure : float
Reference pressure for calculations [Pa]. Default is 101325.0.
design_thrust : float
Design thrust of the engine [N]. Default is 0.0.
design_mass_flow_rate : float
Design mass flow rate [kg/s]. Default is 0.0.
OpenVSP_flow_through : bool
Flag for OpenVSP flow-through analysis. Default is False.
Notes
-----
The Turbofan class inherits from the Propulsor base class and implements
methods for computing turbofan engine performance. It includes functionality
for handling different operating conditions and performance calculations.
**Definitions**
'ISA'
International Standard Atmosphere - standard atmospheric model
'SFC'
Specific Fuel Consumption - fuel efficiency metric
'OpenVSP'
Open Vehicle Sketch Pad - open-source parametric aircraft geometry tool
See Also
--------
RCAIDE.Library.Components.Powertrain.Propulsors.Propulsor
RCAIDE.Library.Components.Powertrain.Propulsors.Turbojet
RCAIDE.Library.Components.Powertrain.Propulsors.Turboprop
RCAIDE.Library.Components.Powertrain.Propulsors.Turboshaft
"""
def __defaults__(self):
# setting the default values
self.tag = 'Turbofan'
self.nacelle = None
self.fan = None
self.ram = None
self.inlet_nozzle = None
self.low_pressure_compressor = None
self.high_pressure_compressor = None
self.low_pressure_turbine = None
self.high_pressure_turbine = None
self.combustor = None
self.core_nozzle = None
self.fan_nozzle = None
self.diameter = 0.0
self.length = 0.0
self.height = 0.0 # Engine centerline heigh above the ground plane
self.plug_diameter = 0.1 # dimater of the engine plug
self.geometry_xe = 1. # Geometry information for the installation effects function
self.geometry_ye = 1. # Geometry information for the installation effects function
self.geometry_Ce = 2. # Geometry information for the installation effects function
self.bypass_ratio = 0.0
self.design_isa_deviation = 0.0
self.design_altitude = 0.0
self.specific_fuel_consumption_reduction_factor = 0.0 # Less than 1 is a reduction
self.compressor_nondimensional_massflow = 0.0
self.reference_temperature = 288.15
self.reference_pressure = 1.01325*10**5
self.design_thrust = 0.0
self.mass_flow_rate_design = 0.0
self.emission_indices = Data()
self.emission_indices.NOx = None
self.emission_indices.CO2 = None
self.emission_indices.CO = None
self.emission_indices.H2O = None
self.emission_indices.SO2 = None
self.emission_indices.Soot = None
self.OpenVSP_flow_through = False
[docs]
def append_operating_conditions(self,segment,energy_conditions,noise_conditions=None):
"""
Appends operating conditions to the segment.
"""
append_turbofan_conditions(self,segment,energy_conditions,noise_conditions)
return
[docs]
def unpack_propulsor_unknowns(self,segment):
return
[docs]
def pack_propulsor_residuals(self,segment):
return
[docs]
def append_propulsor_unknowns_and_residuals(self,segment):
return
[docs]
def reuse_stored_data(turbofan,state,network,stored_propulsor_tag = None,center_of_gravity = [[0, 0, 0]]):
"""
Reuses stored turbofan data for performance calculations.
"""
thrust,moment,power_mech,power_elec = reuse_stored_turbofan_data(turbofan,state,network,stored_propulsor_tag,center_of_gravity)
return thrust,moment,power_mech,power_elec
