RCAIDE.Library.Components.Powertrain.Propulsors.Turboprop

Turboprop

class Turboprop(*args, **kwarg)

Bases: Propulsor

A turboprop propulsion system model that simulates the performance of a turboprop engine.

tag

Identifier for the turboprop engine. Default is ‘turboprop’.

Type:

str

nacelle

Nacelle component of the engine. Default is None.

Type:

Component

compressor

Compressor component of the engine. Default is None.

Type:

Component

turbine

Turbine component of the engine. Default is None.

Type:

Component

combustor

Combustor component of the engine. Default is None.

Type:

Component

diameter

Diameter of the engine [m]. Default is 0.0.

Type:

float

length

Length of the engine [m]. Default is 0.0.

Type:

float

height

Engine centerline height above the ground plane [m]. Default is 0.5.

Type:

float

design_isa_deviation

ISA temperature deviation at design point [K]. Default is 0.0.

Type:

float

specific_fuel_consumption_reduction_factor

Specific fuel consumption adjustment factor (Less than 1 is a reduction). Default is 0.0.

Type:

float

design_altitude

Design altitude of the engine [m]. Default is 0.0.

Type:

float

propeller_efficiency

Design point propeller efficiency. Default is 0.0.

Type:

float

gearbox.efficiency

Design point gearbox efficiency. Default is 0.0.

Type:

float

design_mach_number

Design Mach number. Default is 0.0.

Type:

float

compressor_nondimensional_massflow

Non-dimensional mass flow through the compressor. Default is 0.0.

Type:

float

reference_temperature

Reference temperature for calculations [K]. Default is 288.15.

Type:

float

reference_pressure

Reference pressure for calculations [Pa]. Default is 101325.0.

Type:

float

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

append_operating_conditions(segment, energy_conditions, noise_conditions=None)

Appends operating conditions to the segment.

unpack_propulsor_unknowns(segment)

pack_propulsor_residuals(segment)

append_propulsor_unknowns_and_residuals(segment)

compute_performance(state, center_of_gravity=[[0, 0, 0]])

Computes turboprop performance including thrust, moment, and power.

reuse_stored_data(state, network, stored_propulsor_tag=None, center_of_gravity=[[0, 0, 0]])

Reuses stored turboprop data for performance calculations.