RCAIDE.Library.Methods.Powertrain.Propulsors.Turbofan.design_turbofan

design_turbofan#

design_turbofan(turbofan)[source]#

Computes performance properties of a turbofan engine at the design point by linking and analyzing the thermodynamic cycle of its components.

Parameters:

turbofan (RCAIDE.Library.Components.Propulsors.Turbofan) –

Turbofan engine component with the following attributes:
  • tagstr

    Identifier for the turbofan

  • design_mach_numberfloat

    Design Mach number

  • design_altitudefloat

    Design altitude [m]

  • design_isa_deviationfloat

    ISA temperature deviation at design point [K]

  • working_fluidData

    Working fluid properties object

  • reference_temperaturefloat

    Reference temperature for mass flow scaling [K]

  • reference_pressurefloat

    Reference pressure for mass flow scaling [Pa]

  • bypass_ratiofloat

    Bypass ratio of the turbofan

  • ramData
    Ram component
    • tagstr

      Identifier for the ram

  • inlet_nozzleData
    Inlet nozzle component
    • tagstr

      Identifier for the inlet nozzle

  • fanData
    Fan component
    • tagstr

      Identifier for the fan

  • low_pressure_compressorData
    Low pressure compressor component
    • tagstr

      Identifier for the low pressure compressor

  • high_pressure_compressorData
    High pressure compressor component
    • tagstr

      Identifier for the high pressure 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

  • fan_nozzleData
    Fan nozzle component
    • tagstr

      Identifier for the fan nozzle

Return type:

None

Notes

This function performs a complete design analysis of a turbofan engine by:

  1. Setting up atmospheric conditions at the design point

  2. Creating a mission segment for the design point

  3. Sequentially analyzing each component in the engine’s thermodynamic cycle

  4. Linking the output conditions of each component to the input conditions of the next

  5. Sizing the core flow to meet the design requirements

  6. Computing sea level static performance

The function follows this sequence for component analysis:

  1. Ram (inlet)

  2. Inlet nozzle

  3. Fan

  4. Low pressure compressor

  5. High pressure compressor

  6. Combustor

  7. High pressure turbine

  8. Low pressure turbine

  9. Core nozzle

  10. Fan nozzle

Major Assumptions

  • US Standard Atmosphere 1976

  • 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 [2] Cantwell, B., “AA283 Course Notes”, Stanford University. https://web.stanford.edu/~cantwell/AA283_Course_Material/AA283_Course_BOOK/AA283_Aircraft_and_Rocket_Propulsion_BOOK_Brian_J_Cantwell_May_28_2024.pdf

See also

RCAIDE.Library.Methods.Powertrain.Propulsors.Turbofan.compute_turbofan_performance, RCAIDE.Library.Methods.Powertrain.Propulsors.Turbofan.size_core

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