RCAIDE.Library.Methods.Powertrain.Propulsors.Turboprop.compute_thrust
compute_thrust#
- compute_thrust(turboprop, conditions)[source]#
Computes thrust and other performance metrics for a turboprop engine.
- Parameters:
turboprop (RCAIDE.Library.Components.Propulsors.Turboprop) –
- Turboprop engine component with the following attributes:
- tagstr
Identifier for the turboprop
- compressorData
Compressor component
- combustorData
- Combustor component
- turbine_inlet_temperaturefloat
Combustor exit/turbine inlet temperature [K]
- fuel_dataData
- Fuel properties
- lower_heating_valuefloat
Fuel lower heating value [J/kg]
- high_pressure_turbineData
High pressure turbine component
- low_pressure_turbineData
- Low pressure turbine component
- mechanical_efficiencyfloat
Mechanical efficiency of the turbine
- core_nozzleData
Core nozzle component
- propeller_efficiencyfloat
Efficiency of the propeller
- gearboxData
- Gearbox component
- efficiencyfloat
Gearbox efficiency
- reference_temperaturefloat
Reference temperature for mass flow scaling [K]
- reference_pressurefloat
Reference pressure for mass flow scaling [Pa]
- compressor_nondimensional_massflowfloat
Non-dimensional mass flow parameter [kg·√K/(s·Pa)]
conditions (RCAIDE.Framework.Mission.Common.Conditions) –
- Flight conditions with:
- freestreamData
- Freestream properties
- gravitynumpy.ndarray
Gravitational acceleration [m/s²]
- temperaturenumpy.ndarray
Freestream temperature [K]
- pressurenumpy.ndarray
Freestream pressure [Pa]
- mach_numbernumpy.ndarray
Freestream Mach number
- speed_of_soundnumpy.ndarray
Speed of sound [m/s]
- energyData
- Energy conditions
- propulsors[turboprop.tag]Data
- Turboprop-specific conditions
- throttlenumpy.ndarray
Throttle setting [0-1]
- total_temperature_referencenumpy.ndarray
Reference total temperature [K]
- total_pressure_referencenumpy.ndarray
Reference total pressure [Pa]
- convertersdict
Converter energy conditions indexed by tag
- Returns:
- Results are stored in conditions.energy.propulsors[turboprop.tag]:
- thrustnumpy.ndarray
Thrust force [N]
- thrust_specific_fuel_consumptionnumpy.ndarray
Thrust specific fuel consumption [kg/(N·hr)]
- non_dimensional_thrustnumpy.ndarray
Non-dimensional thrust
- core_mass_flow_ratenumpy.ndarray
Core mass flow rate [kg/s]
- fuel_flow_ratenumpy.ndarray
Fuel flow rate [kg/s]
- powernumpy.ndarray
Shaft power output [W]
- specific_powernumpy.ndarray
Specific power [W·s/kg]
- power_specific_fuel_consumptionnumpy.ndarray
Power specific fuel consumption [kg/(W·hr)]
- thermal_efficiencynumpy.ndarray
Thermal efficiency
- propulsive_efficiencynumpy.ndarray
Propulsive efficiency
- Return type:
None
Notes
This function implements a thermodynamic model for a turboprop engine to calculate thrust, fuel consumption, and efficiencies. It uses the outputs from each component in the engine cycle to determine overall performance.
- Major Assumptions
Perfect gas behavior
Constant component efficiencies
Propeller efficiency is constant
Theory The turboprop performance is calculated using gas turbine cycle analysis. The thrust is determined by the power output of the low pressure turbine, the propeller efficiency, and the core exhaust momentum.
The specific thrust is calculated as:
\[F_{sp} = \frac{W_{total} \cdot c_p \cdot T_0}{V_0}\]- where:
\(W_{total}\) is the total work output coefficient
\(c_p\) is the specific heat at constant pressure
\(T_0\) is the freestream temperature
\(V_0\) is the freestream velocity
References
[1] Mattingly, J.D., “Elements of Gas Turbine Propulsion”, AIAA Education Series, 1996.