RCAIDE.Library.Methods.Powertrain.Propulsors.Turboprop.design_turboprop

design_turboprop

design_turboprop(turboprop)

Sizes a turboprop engine based on design point conditions and computes its performance characteristics.

Parameters:

turboprop (Turboprop) –

Turboprop engine object containing all component definitions and design parameters

• 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 the turboprop object attributes:

• design_thrust_specific_fuel_consumptionfloat

  TSFC at design point [kg/N/s]

• design_non_dimensional_thrustfloat

  Non-dimensional thrust at design point [-]

• design_core_mass_flow_ratefloat

  Core mass flow rate at design point [kg/s]

• design_fuel_flow_ratefloat

  Fuel flow rate at design point [kg/s]

• design_powerfloat

  Power output at design point [W]

• design_specific_powerfloat

  Specific power at design point [W/kg]

• design_power_specific_fuel_consumptionfloat

  Power specific fuel consumption [kg/W/s]

• design_thermal_efficiencyfloat

  Thermal efficiency at design point [-]

• design_propulsive_efficiencyfloat

  Propulsive efficiency at design point [-]

Return type:

None

Notes

The function performs the following steps:

1. Computes atmospheric conditions at design altitude

2. Sets up freestream conditions

3. Analyzes flow through each component sequentially

4. Sizes the core based on design point requirements

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

Theory

The design process follows standard gas turbine cycle analysis, with each component modeled using appropriate thermodynamic relations. The core sizing is based on achieving the required power output while maintaining component matching throughout the engine.

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