Method and system for limiting power of an engine
AssigneePratt & Whitney Canada Corp.
InventorsSylvain LAMARRE, Simon LOPEZ, Nicolas DES ROCHES-DIONNE, Michael CONCIATORI
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Abstract
Systems and methods for limiting power of a gas turbine engine for an aircraft are described herein. A blade angle of a propeller blade of the engine and a commanded power for the engine are obtained. A thrust transition direction is determined. The commanded power is compared to a selected threshold based on the blade angle and the thrust transition direction. Power to the engine is limited when the commanded power exceeds the selected threshold.
Claims19
A method for limiting power of a gas turbine engine for an aircraft, the method comprising:
- obtaining a blade angle of a propeller blade of the engine and a commanded power for the engine;
- determining a thrust transition direction of the engine;
- comparing the commanded power to a selected threshold based on the blade angle and the thrust transition direction;
- and
- limiting power to the engine when the commanded power exceeds the selected threshold.
A system for limiting power of a gas turbine engine for an aircraft, the system comprising:
- a processing unit;
- and
- a non-transitory computer-readable memory having stored thereon program instructions executable by the processing unit for:
- obtaining a blade angle of a propeller blade of the engine and a commanded power for the engine;
- determining a thrust transition direction of the engine;
- comparing the commanded power to a selected threshold based on the blade angle and the thrust transition direction;
- and
- limiting power to the engine when the commanded power exceeds the selected threshold.
A non-transitory computer-readable medium having stored thereon program instructions for limiting power of a gas turbine engine for an aircraft, the program instructions executable by a processing unit for:
- obtaining a blade angle of a propeller blade of the engine and a commanded power for the engine;
- determining a thrust transition direction of the engine;
- comparing the commanded power to a selected threshold based on the blade angle and the thrust transition direction;
- and
- limiting power to the engine when the commanded power exceeds the selected threshold.
Dependencies are inferred from the claim text.