# RCAIDE/Library/Components/Propulsors/Turboprop.py
#
#
# Created: Mar 2024, M. Clarke
# ----------------------------------------------------------------------------------------------------------------------
# IMPORT
# ----------------------------------------------------------------------------------------------------------------------
# RCAIDE imports
from . import Propulsor
from RCAIDE.Framework.Core import Data
from RCAIDE.Library.Methods.Powertrain.Propulsors.Turboprop .append_turboprop_conditions import append_turboprop_conditions
from RCAIDE.Library.Methods.Powertrain.Propulsors.Turboprop .compute_turboprop_performance import compute_turboprop_performance, reuse_stored_turboprop_data
# ----------------------------------------------------------------------------------------------------------------------
# Fan Component
# ----------------------------------------------------------------------------------------------------------------------
[docs]
class Turboprop(Propulsor):
"""
A turboprop propulsion system model that simulates the performance of a turboprop engine.
Attributes
----------
tag : str
Identifier for the turboprop engine. Default is 'turboprop'.
nacelle : Component
Nacelle component of the engine. Default is None.
compressor : Component
Compressor component of the engine. Default is None.
turbine : Component
Turbine component of the engine. Default is None.
combustor : Component
Combustor component of the engine. 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.
design_isa_deviation : float
ISA temperature deviation at design point [K]. 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.
design_altitude : float
Design altitude of the engine [m]. Default is 0.0.
propeller_efficiency : float
Design point propeller efficiency. Default is 0.0.
gearbox.efficiency : float
Design point gearbox efficiency. Default is 0.0.
design_mach_number : float
Design Mach number. 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.
Notes
-----
The Turboprop class inherits from the Propulsor base class and implements
methods for computing turboprop engine performance. A turboprop engine uses
a gas turbine core to drive a propeller through a reduction gearbox, combining
the efficiency of a propeller at low speeds with the power of a turbine engine.
**Definitions**
'ISA'
International Standard Atmosphere - standard atmospheric model
'Mach number'
Ratio of flow velocity to the local speed of sound
See Also
--------
RCAIDE.Library.Components.Powertrain.Propulsors.Propulsor
RCAIDE.Library.Components.Powertrain.Propulsors.Turbofan
RCAIDE.Library.Components.Powertrain.Propulsors.Turbojet
"""
def __defaults__(self):
# setting the default values
self.tag = 'turboprop'
self.nacelle = None
self.compressor = None
self.turbine = None
self.combustor = None
self.diameter = 0.0
self.length = 0.0
self.height = 0.0
self.design_isa_deviation = 0.0
self.design_altitude = 0.0
self.propeller_efficiency = 0.0
self.gearbox = Data()
self.specific_fuel_consumption_reduction_factor = 0.0
self.gearbox.gear_ratio = 1.0
self.gearbox.efficiency = 0.0
self.design_angular_velocity = 0.0
self.design_mach_number = None
self.design_freestream_velocity = None
self.compressor_nondimensional_massflow = 0.0
self.reference_temperature = 288.15
self.reference_pressure = 1.01325*10**5
[docs]
def append_operating_conditions(self,segment,energy_conditions,noise_conditions=None):
"""
Appends operating conditions to the segment.
"""
append_turboprop_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(turboprop,state,network,stored_propulsor_tag = None,center_of_gravity = [[0, 0, 0]]):
"""
Reuses stored turboprop data for performance calculations.
"""
thrust,moment,power_mech,power_elec = reuse_stored_turboprop_data(turboprop,state,network,stored_propulsor_tag,center_of_gravity)
return thrust,moment,power_mech,power_elec
