RCAIDE.Library.Methods.Powertrain.Converters.Turboshaft.design_turboshaft

design_turboshaft

design_turboshaft(turboshaft)

Designs and sizes a turboshaft engine based on design point conditions and performance requirements.

Parameters:

turboshaft (Turboshaft) –

Turboshaft engine object containing design parameters and components

• design_mach_numberfloat

  Design point Mach number

• design_altitudefloat

  Design point altitude [m]

• design_isa_deviationfloat

  ISA temperature deviation [K]

• working_fluidFluidProperties

  Working fluid properties object

• Components:

  • ram : Ram

  • inlet_nozzle : Compression_Nozzle

  • compressor : Compressor

  • combustor : Combustor

  • high_pressure_turbine : Turbine

  • low_pressure_turbine : Turbine

  • core_nozzle : Expansion_Nozzle

Returns:

Results are stored in turboshaft attributes:

• design_thrust_specific_fuel_consumptionfloat

  TSFC at design point [kg/N/s]

• design_non_dimensional_thrustfloat

  Non-dimensional thrust [-]

• design_core_mass_flow_ratefloat

  Core mass flow rate [kg/s]

• design_fuel_flow_ratefloat

  Fuel flow rate [kg/s]

• design_powerfloat

  Power output [W]

• design_specific_powerfloat

  Specific power [W/kg]

• design_power_specific_fuel_consumptionfloat

  Power specific fuel consumption [kg/W/s]

• design_thermal_efficiencyfloat

  Thermal efficiency [-]

• design_propulsive_efficiencyfloat

  Propulsive efficiency [-]

Return type:

None

Notes

The function performs the following steps:

1. Computes atmospheric conditions at design altitude

2. Initializes design point conditions

3. Analyzes flow through each component sequentially:

   • Ram inlet

   • Inlet nozzle

   • Compressor

   • Combustor

   • High pressure turbine

   • Low pressure turbine

   • Core nozzle

4. Sizes core components

5. Computes sea level static performance

Major Assumptions

• Standard atmospheric conditions (with possible ISA deviation)

• Steady state operation

• Perfect gas behavior

• Adiabatic component processes except combustor

• No bleed air extraction

• Design point sizing determines component characteristics

Theory

The design process follows standard gas turbine cycle analysis principles. Component sizing is based on achieving required power output while maintaining appropriate component matching throughout the engine.

Extra modules required

• RCAIDE.Framework.Analyses.Atmospheric.US_Standard_1976

• RCAIDE.Library.Attributes.Planets.Earth

See also

RCAIDE.Library.Methods.Powertrain.Converters.Ram.compute_ram_performance, RCAIDE.Library.Methods.Powertrain.Converters.Combustor.compute_combustor_performance, RCAIDE.Library.Methods.Powertrain.Converters.Compressor.compute_compressor_performance, RCAIDE.Library.Methods.Powertrain.Converters.Turbine.compute_turbine_performance