RCAIDE.Library.Methods.Powertrain.Propulsors.Turboprop.compute_turboprop_performance

compute_turboprop_performance#

compute_turboprop_performance(turboprop, state, center_of_gravity=[[0.0, 0.0, 0.0]])[source]#

Computes the performance of a turboprop engine by analyzing the thermodynamic cycle.

Parameters:

  • turboprop (RCAIDE.Library.Components.Propulsors.Turboprop) –

    Turboprop engine component with the following attributes:
    • tagstr

      Identifier for the turboprop

    • working_fluidData

      Working fluid properties object

    • ramData
      Ram component
      • tagstr

        Identifier for the ram

    • inlet_nozzleData
      Inlet nozzle component
      • tagstr

        Identifier for the inlet nozzle

    • compressorData
      Compressor component
      • tagstr

        Identifier for the compressor

      • motorData, optional

        Electric motor component

      • generatorData, optional

        Electric generator component

      • design_angular_velocityfloat

        Design angular velocity [rad/s]

    • combustorData
      Combustor component
      • tagstr

        Identifier for the combustor

      • fuel_dataData

        Fuel properties - specific_energy : float

        Fuel specific energy [J/kg]

    • 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

    • reference_temperaturefloat

      Reference temperature for mass flow scaling [K]

    • reference_pressurefloat

      Reference pressure for mass flow scaling [Pa]

    • compressor_nondimensional_massflowfloat

      Non-dimensional mass flow parameter [kg·√K/(s·Pa)]

    • originlist of lists

      Origin coordinates [[x, y, z]] [m]

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

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

          Freestream velocity [m/s]

        • temperaturenumpy.ndarray

          Freestream temperature [K]

        • pressurenumpy.ndarray

          Freestream pressure [Pa]

      • noiseData
        Noise conditions
        • propulsorsdict

          Propulsor noise conditions indexed by tag

      • energyData
        Energy conditions
        • propulsorsdict

          Propulsor energy conditions indexed by tag

        • convertersdict

          Converter energy conditions indexed by tag

        • hybrid_power_split_ratiofloat

          Ratio of power split for hybrid systems

    • numericsData
      Numerical properties
      • timeData
        Time properties
        • differentiatelist

          List of differentiation methods

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

Returns:

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

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

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

  • power_elec (numpy.ndarray) – Electrical power input/output [W]

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

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

Notes

This function computes the performance of a turboprop 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 thrust and power output

  10. Calculate efficiencies

  11. Handle electrical power generation/consumption if applicable

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.Propulsors.Turboprop.compute_thrust

reuse_stored_turboprop_data(turboprop, state, network, stored_propulsor_tag, center_of_gravity=[[0.0, 0.0, 0.0]])[source]#

Reuses results from one turboprop for identical propulsors

Assumptions: N/A

Source: N/A

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

Outputs: total_power - power of turboprop group [W]

Properties Used: N.A.