RCAIDE.Library.Methods.Powertrain.Propulsors.Turbojet.compute_turbojet_performance

compute_turbojet_performance#

compute_turbojet_performance(turbojet, state, center_of_gravity=[[0.0, 0.0, 0.0]])[source]#

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

Parameters:

  • turbojet (RCAIDE.Library.Components.Propulsors.Turbojet) –

    Turbojet engine component with the following attributes:
    • tagstr

      Identifier for the turbojet

    • 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

    • low_pressure_compressorData
      Low pressure compressor component
      • tagstr

        Identifier for the low pressure compressor

      • motorData, optional

        Electric motor component

      • generatorData, optional

        Electric generator component

      • design_angular_velocityfloat

        Design angular velocity [rad/s]

    • high_pressure_compressorData
      High pressure compressor component
      • tagstr

        Identifier for the high pressure compressor

      • 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

    • afterburnerData
      Afterburner component
      • tagstr

        Identifier for the afterburner

    • core_nozzleData
      Core nozzle component
      • tagstr

        Identifier for the core nozzle

    • afterburner_activebool

      Flag indicating if afterburner is active

    • 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

    • ones_rowfunction

      Function to create array of ones with specified length

  • 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 turbojet with stored results

Notes

This function computes the performance of a turbojet 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 low pressure compressor performance

  5. Compute high pressure compressor performance

  6. Compute combustor performance

  7. Compute high pressure turbine performance

  8. Compute low pressure turbine performance

  9. Compute afterburner performance (if active)

  10. Compute core nozzle performance

  11. Compute thrust and power output

  12. Calculate efficiencies

  13. Handle electrical power generation/consumption if applicable

Major Assumptions

  • Steady state operation

  • One-dimensional flow through components

  • Adiabatic components except for the combustor and afterburner

  • 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 [2] Cantwell, B., “AA283 Course Notes”, Stanford University. https://web.stanford.edu/~cantwell/AA283_Course_Material/

See also

RCAIDE.Library.Methods.Powertrain.Propulsors.Turbojet.compute_thrust, RCAIDE.Library.Methods.Powertrain.Propulsors.Turbojet.reuse_stored_turbojet_data

reuse_stored_turbojet_data(turbojet, state, network, stored_propulsor_tag, center_of_gravity=[[0.0, 0.0, 0.0]])[source]#

Reuses results from one turbojet for identical propulsors

Assumptions: N/A

Source: N/A

Inputs: turbojet - turbojet data structure [-] state - operating conditions data structure [-] fuel_line - fuelline [-] total_thrust - thrust of turbojet group [N] total_power - power of turbojet group [W]

Outputs: total_thrust - thrust of turbojet group [N] total_power - power of turbojet group [W]

Properties Used: N.A.