RCAIDE.Library.Methods.Powertrain.Converters.Turboshaft.compute_power
compute_power#
- compute_power(turboshaft, conditions)[source]#
Computes power and other performance properties for a turboshaft engine.
- Parameters:
turboshaft (RCAIDE.Library.Components.Converters.Turboshaft) –
- Turboshaft engine component with the following attributes:
- tagstr
Identifier for the turboshaft
- fuel_typeData
- Fuel properties object
- lower_heating_valuefloat
Fuel lower heating value [J/kg]
- working_fluidData
Working fluid properties object
- reference_temperaturefloat
Reference temperature for mass flow scaling [K]
- reference_pressurefloat
Reference pressure for mass flow scaling [Pa]
- compressorData
- Compressor component
- pressure_ratiofloat
Compressor pressure ratio
- mass_flow_ratefloat
Design mass flow rate [kg/s]
- conversion_efficiencyfloat
Efficiency of converting thermal energy to shaft power
- inverse_calculationbool
Flag for inverse calculation mode (power to throttle)
conditions (RCAIDE.Framework.Mission.Common.Conditions) –
- Flight conditions with:
- freestreamData
- Freestream properties
- isentropic_expansion_factornumpy.ndarray
Ratio of specific heats (gamma)
- speed_of_soundnumpy.ndarray
Speed of sound [m/s]
- mach_numbernumpy.ndarray
Flight Mach number
- gravitynumpy.ndarray
Gravitational acceleration [m/s²]
- energy.converters[turboshaft.tag]Data
- Turboshaft operating conditions
- throttlenumpy.ndarray
Throttle setting [0-1]
- total_temperature_referencenumpy.ndarray
Reference total temperature [K]
- total_pressure_referencenumpy.ndarray
Reference total pressure [Pa]
- combustor_stagnation_temperaturenumpy.ndarray
Combustor exit stagnation temperature [K]
- powernumpy.ndarray
Required power output (for inverse calculation) [W]
- Return type:
None
Notes
This function implements a thermodynamic model for a turboshaft engine with a free power turbine. It can operate in two modes: direct (throttle to power) or inverse (power to throttle).
- Major Assumptions
Perfect gas behavior
Turboshaft engine with free power turbine
Constant component efficiencies
Theory The turboshaft performance is calculated using gas turbine cycle analysis. The power output is determined by the temperature rise in the combustor, the compressor pressure ratio, and the component efficiencies.
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] Stuyvenberg, L., “Helicopter Turboshafts”, University of Colorado, 2015. https://www.colorado.edu/faculty/kantha/sites/default/files/attached-files/70652-116619_-_luke_stuyvenberg_-_dec_17_2015_1258_pm_-_stuyvenberg_helicopterturboshafts.pdf