Nacelle drag reduction device for a turbofan gas turbine engine
AssigneePratt & Whitney Canada Corp.
InventorDaniel T. Alecu
Life of this patent
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Abstract
The nacelle drag reduction device comprises a substantially circular and axis symmetrical external airfoil concentric with a aft section of the nacelle and located outside a propulsive jet zone defined behind the engine when operating, the airfoil being positioned at a location providing a maximum streamline angle with reference to the main axis of the engine and a highest streamline curvature.
Claims10
A nacelle drag reduction device for a confluent flow nacelle of a turbofan gas turbine engine having a main axis, with flow stream lines of ambient air along the nacelle resulting from forward movement of the nacelle during operation of the turbofan gas turbine engine, the device comprising a substantially circular and axis symmetrical external airfoil concentric with a aft section of the nacelle and located outside a propulsive jet zone defined behind the engine when operating, the airfoil being positioned at a location providing a maximum angle of the stream lines with reference to the main axis of the engine and a highest curvature of the stream lines.
A method of enhancing external flow conditions around a nacelle of an aircraft-mounted confluent flow gas turbine engine, the method comprising:
- operating the engine and creating fluid stream lines along the nacelle, and an ambient fluid entrainment behind the engine;
- and
- deflecting the fluid stream lines of ambient air to reduce jet induced nacelle drag, the ambient air being deflected upstream the propulsive jet zone.
Dependencies are inferred from the claim text.