RCAIDE.Library.Methods.Powertrain.Converters.Turboshaft.compute_turboshaft_performance

compute_turboshaft_performance#

compute_turboshaft_performance(turboshaft, state, fuel_line=None, bus=None)[source]#

Computes the perfomrance of a turboshaft

Parameters:

  • turboshaft (RCAIDE.Library.Components.Converters.Turboshaft) –

    Turboshaft engine component with the following attributes:
    • tagstr

      Identifier for the turboshaft

    • working_fluidData

      Working fluid properties object

    • ramData

      Ram component - tag : str

      Identifier for the ram

    • inlet_nozzleData
      Inlet nozzle component
      • tagstr

        Identifier for the inlet nozzle

    • compressorData
      Compressor component
      • tagstr

        Identifier for the compressor

    • combustorData
      Combustor component
      • tagstr

        Identifier for the combustor

    • high_pressure_turbineData
      High pressure turbine component
      • tagstr

        Identifier for the high pressure turbine

    • low_pressure_turbineData
      Low pressure turbine component
      • tagstr

        Identifier for the low pressure turbine

    • core_nozzleData
      Core nozzle component
      • tagstr

        Identifier for the core nozzle

  • state (RCAIDE.Framework.Mission.Common.State) –

    State object containing:
    • conditionsData
      Flight conditions
      • freestreamData
        Freestream properties
        • densitynumpy.ndarray

          Air density [kg/m³]

      • noisedict

        Noise conditions indexed by component tag

      • energydict

        Energy conditions indexed by component tag

  • center_of_gravity (list of lists, optional) – Center of gravity coordinates [[x, y, z]] [m]. Default: [[0.0, 0.0, 0.0]]

Returns:

  • thrust (numpy.ndarray) – Thrust force vector [N]

  • moment (numpy.ndarray) – Moment vector [N·m]

  • power (numpy.ndarray) – Shaft power output [W]

  • stored_results_flag (bool) – Flag indicating if results are stored

  • stored_propulsor_tag (str) – Tag of the turboshaft with stored results

Notes

This function computes the performance of a turboshaft engine by sequentially analyzing each component in the engine’s thermodynamic cycle. It links the output conditions of each component to the input conditions of the next component in the flow path.

The function follows this sequence:

  1. Set working fluid properties

  2. Compute ram performance

  3. Compute inlet nozzle performance

  4. Compute compressor performance

  5. Compute combustor performance

  6. Compute high pressure turbine performance

  7. Compute low pressure turbine performance

  8. Compute core nozzle performance

  9. Compute power output

Major Assumptions

  • Steady state operation

  • One-dimensional flow through components

  • Adiabatic components except for the combustor

  • Perfect gas behavior with variable properties

References

[1] Mattingly, J.D., “Elements of Gas Turbine Propulsion”, 2nd Edition, AIAA Education Series, 2005. https://soaneemrana.org/onewebmedia/ELEMENTS%20OF%20GAS%20TURBINE%20PROPULTION2.pdf

See also

RCAIDE.Library.Methods.Powertrain.Converters.Turboshaft.compute_power

reuse_stored_turboshaft_data(turboshaft, state, network, fuel_line, bus, stored_converter_tag)[source]#

Reuses results from one turboshaft for identical propulsors

Assumptions: N/A

Source: N/A

Inputs: conditions - operating conditions data structure [-] fuel_line - fuelline [-] turboshaft - turboshaft data structure [-] total_power - power of turboshaft group [W]

Outputs: total_power - power of turboshaft group [W]

Properties Used: N.A.