RCAIDE.Library.Components.Powertrain.Propulsors.Turbojet

Turbojet#

class Turbojet(*args, **kwarg)[source]#

Bases: Propulsor

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

tag#

Identifier for the turbojet engine. Default is ‘Turbojet’.

Type:

str

nacelle#

Nacelle component of the engine. Default is None.

Type:

Component

ram#

Ram inlet component. Default is None.

Type:

Component

inlet_nozzle#

Inlet nozzle component. Default is None.

Type:

Component

low_pressure_compressor#

Low pressure compressor component. Default is None.

Type:

Component

high_pressure_compressor#

High pressure compressor component. Default is None.

Type:

Component

low_pressure_turbine#

Low pressure turbine component. Default is None.

Type:

Component

high_pressure_turbine#

High pressure turbine component. Default is None.

Type:

Component

combustor#

Combustor component. Default is None.

Type:

Component

afterburner#

Afterburner component. Default is None.

Type:

Component

core_nozzle#

Core exhaust nozzle component. Default is None.

Type:

Component

length#

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

Type:

float

bypass_ratio#

Engine bypass ratio. Default is 0.0.

Type:

float

design_isa_deviation#

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

Type:

float

design_altitude#

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

Type:

float

afterburner_active#

Flag indicating if afterburner is in use. Default is False.

Type:

bool

specific_fuel_consumption_reduction_factor#

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

design_thrust#

Design thrust of the engine [N]. Default is 0.0.

Type:

float

design_mass_flow_rate#

Design mass flow rate [kg/s]. Default is 0.0.

Type:

float

OpenVSP_flow_through#

Flag for OpenVSP flow-through analysis. Default is False.

Type:

bool

areas#

Collection of engine areas

  • wettedfloat

    Wetted area [m²]. Default is 0.0.

  • maximumfloat

    Maximum cross-sectional area [m²]. Default is 0.0.

  • exitfloat

    Exit area [m²]. Default is 0.0.

  • inflowfloat

    Inflow area [m²]. Default is 0.0.

Type:

Data

Notes

The Turbojet class inherits from the Propulsor base class and implements methods for computing turbojet engine performance. Unlike a turbofan engine, a turbojet does not have a bypass flow and all air goes through the core.

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.Turbofan

append_operating_conditions(segment, energy_conditions, noise_conditions=None)[source]#
unpack_propulsor_unknowns(segment)[source]#
pack_propulsor_residuals(segment)[source]#
append_propulsor_unknowns_and_residuals(segment)[source]#
compute_performance(state, center_of_gravity=[[0, 0, 0]])[source]#
reuse_stored_data(state, network, stored_propulsor_tag=None, center_of_gravity=[[0, 0, 0]])[source]#