simple_turboprop.py

class openconcept.propulsion.systems.simple_turboprop.TurbopropPropulsionSystem(**kwargs)

Bases: Group

This is an example model of the simplest possible propulsion system consisting of a constant-speed prop and a turboshaft.

This is the Pratt and Whitney Canada PT6A-66D with 4-bladed propeller used by the SOCATA-DAHER TBM-850.

Inputs:

  • ac|propulsion|engine|rating (float) – The maximum rated shaft power of the engine (scalar, default 850 hp)

  • ac|propulsion|propeller|diameter (float) – Diameter of the propeller (scalar, default 2.3 m)

  • throttle (float) – Throttle for the turboshaft (vector)

  • fltcond|rho (float) – Air density (vector, kg/m**3)

  • fltcond|Utrue (float) – True airspeed (vector, m/s)

Outputs:

  • thrust (float) – Thrust force (vector, N)

  • fuel_flow (float) – Fuel mass flow rate (vector, kg/s)

Options:

num_nodes (float) – Number of analysis points to run (default 1)

class openconcept.propulsion.systems.simple_turboprop.TwinTurbopropPropulsionSystem(**kwargs)

Bases: Group

This is an example model multiple constant-speed props and turboshafts. These are two P&W Canada PT6A-135A with 4-bladed Hartzell propellers used by the Beechcraft King Air C90GT https://www.easa.europa.eu/sites/default/files/dfu/TCDS_EASA-IM-A-503_C90-Series%20issue%206.pdf

Inputs:

  • ac|propulsion|engine|rating (float) – The maximum rated shaft power of the engine (scalar, default 850 hp)

  • ac|propulsion|propeller|diameter (float) – Diameter of the propeller (scalar, default 2.3 m)

  • throttle (float) – Throttle for the turboshaft (vector)

  • fltcond|rho (float) – Air density (vector, kg/m**3)

  • fltcond|Utrue (float) – True airspeed (vector, m/s)

  • propulsor_active (float) – 1 if second propulsor is active or 0 if not (vector)

Outputs:

  • thrust (float) – Thrust force (vector, N)

  • fuel_flow (float) – Fuel mass flow rate (vector, kg/s)

Options:

num_nodes (float) – Number of analysis points to run (default 1)