Source code for RCAIDE.Library.Components.Powertrain.Converters.Turboshaft
# RCAIDE/Library/Components/Converters/Turboshaft.py
#
#
# Created: Mar 2024, M. Clarke
# Modified: Jun 2024, M. Guidotti
# ----------------------------------------------------------------------------------------------------------------------
# IMPORT
# ----------------------------------------------------------------------------------------------------------------------
## RCAIDE imports
import RCAIDE
from .Converter import Converter
from RCAIDE.Library.Methods.Powertrain.Converters.Turboshaft.append_turboshaft_conditions import append_turboshaft_conditions
from RCAIDE.Library.Methods.Powertrain.Converters.Turboshaft.compute_turboshaft_performance import compute_turboshaft_performance, reuse_stored_turboshaft_data
# ----------------------------------------------------------------------
# Turboshaft
# ----------------------------------------------------------------------
[docs]
class Turboshaft(Converter):
"""
A turboshaft system model that simulates the performance of a turboshaft engine
Attributes
----------
tag : str
Identifier for the shaft engine. Default is 'turboshaft'.
ram : Component
Ram inlet component. Default is None.
inlet_nozzle : Component
Inlet nozzle component. Default is None.
compressor : Component
Low 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.
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.
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_mass_flow_rate : float
Design mass flow rate of turboshaft [kg/s]. Default is 0.0
conversion_efficiency : float
Conversion efficiency of turboshaft [-]. Default is 0.5
design_power : float
Design power of the engine [W]. Default is 0.0.
**Definitions**
'ISA'
International Standard Atmosphere - standard atmospheric model
'SFC'
Specific Fuel Consumption - fuel efficiency metric
See Also
--------
RCAIDE.Library.Components.Powertrain.Converters.Turboelectric_Generator
"""
def __defaults__(self):
# setting the default values
self.tag = 'turboshaft'
self.fuel_type = RCAIDE.Library.Attributes.Propellants.Jet_A1()
self.ram = None
self.inlet_nozzle = None
self.compressor = None
self.low_pressure_turbine = None
self.high_pressure_turbine = None
self.combustor = None
self.core_nozzle = None
self.active = True
self.length = 0.0
self.diamter = 0.0
self.design_isa_deviation = 0.0
self.design_altitude = 0.0
self.specific_fuel_consumption_reduction_factor = 0.0
self.reference_temperature = 288.15
self.reference_pressure = 1.01325*10**5
self.design_power = 0.0
self.design_mass_flow_rate = 0.0
self.conversion_efficiency = 0.5
self.compressor_nondimensional_massflow = 0.0
self.design_angular_velocity = 0.0
self.inverse_calculation = False
[docs]
def append_operating_conditions(self,segment,energy_conditions,noise_conditions=None):
"""
Appends operating conditions to the segment.
"""
append_turboshaft_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(turboshaft,state,network,stored_propulsor_tag = None):
power = reuse_stored_turboshaft_data(turboshaft,state,network,stored_propulsor_tag)
return power
