[특허]Propulsion system and method for efficient lift generation

The Boeing Company

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Propulsion system and method for efficient lift generation

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-003/50
미국특허분류(USC)	244/215; 244/207; 244/201; 244/213; 244/198
출원번호	US-0500419 (2009-07-09)
등록번호	US-8087618 (2012-01-03)
발명자 / 주소	Shmilovich, Arvin Yadlin, Yoram Clark, Roger W. Gregg, III, Robert D.
출원인 / 주소	The Boeing Company
대리인 / 주소	Tung & Associates
인용정보	피인용 횟수 : 7 인용 특허 : 12

초록

A propulsion system for an aircraft includes an airfoil, an engine having an engine cowling carried by the airfoil and configured to produce exhaust gases that are predominantly directed toward an aft end of the airfoil by the engine cowling as engine exhaust, a propulsion flap carried by the airfoil and disposed aft of the engine cowling and a plurality of exhaust ejection orifices provided in the propulsion flap and adapted to receive at least a portion of the exhaust gases from the engine cowling.

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1. A propulsion system for an aircraft, comprising: an airfoil;an engine having an engine cowling carried by the airfoil and configured to produce exhaust gases that are predominantly directed toward an aft end of the airfoil by the engine cowling as engine exhaust;a propulsion flap carried by the airfoil and disposed aft of the engine cowling;an extendable airfoil flap extending from the airfoil and wherein the propulsion flap extends from the airfoil flap; anda plurality of exhaust ejection orifices provided in the propulsion flap and adapted to receive at least a portion of the exhaust gases from the engine cowling. 2. The propulsion system of claim 1 further comprising a controller configured to switchably allow the at least a portion of the exhaust gases to pass through the plurality of exhaust ejection orifices in a constant distribution mode. 3. The propulsion system of claim 2 wherein the controller is further configured to switchably allow the at least a portion of the exhaust gases to pass through the plurality of exhaust ejection orifices in an intermittent distribution mode. 4. The propulsion system of claim 1 further comprising at least one duct extending through the propulsion flap and disposed in fluid communication with the engine cowling and the plurality of exhaust ejection orifices. 5. The propulsion system of claim 4 further comprising at least one exhaust flow valve provided in the at least one duct and a controller connected to the at least one exhaust flow valve. 6. The propulsion system of claim 1 wherein the propulsion flap has a generally rectangular shape. 7. The propulsion system of claim 6 wherein the propulsion flap has a flap hinge line connecting the propulsion flap to the airfoil, a pair of spaced-apart flap side edges extending from the flap hinge line, a flap trailing edge spaced-apart from the flap hinge line and a flap curvature between the flap hinge line and the flap trailing edge. 8. The propulsion system of claim 4 wherein the plurality of exhaust ejection orifices comprises a plurality of pairs of Spaced-apart exhaust ejection orifices. 9. The propulsion system of claim 8 wherein the plurality of pairs of exhaust ejection orifices comprises a pair of spaced-apart proximal exhaust ejection orifices generally adjacent to the flap hinge line, a pair of spaced-apart trailing exhaust ejection orifices generally adjacent to the flap trailing edge and a pair of spaced-apart middle exhaust ejection orifices between the proximal exhaust ejection orifices and the trailing exhaust ejection orifices. 10. A propulsion system configured for providing lift to an aircraft, comprising: an airfoil; an engine having an engine cowling carried by the airfoil and configured to produce exhaust gases that are predominantly directed toward an aft end of the airfoil by the engine cowling as engine exhaust; a generally rectangular propulsion flap carried by the airfoil and disposed aft of the engine cowling;an extendable airfoil flap extending from the airfoil and wherein the propulsion flap extends from the airfoil flap;a plurality of pairs of spaced-apart exhaust ejection orifices provided in the propulsion flap and adapted to receive at least a portion of the exhaust gases from the engine cowling; anda controller configured to facilitate intermittent flow of the at least a portion of the exhaust gases from the plurality of pairs of exhaust ejection orifices. 11. The propulsion system of claim 10 further, comprising at least one duct extending through the propulsion flap and disposed in fluid communication with the engine cowling and the plurality of exhaust ejection orifices. 12. The propulsion system of claim 11 further comprising at least one exhaust flow valve provided in the at least one duct and a controller connected to the at least one exhaust flow valve. 13. The propulsion system of claim 10 wherein the propulsion flap has a generally rectangular shape having a flap hinge line connecting the propulsion flap to the airfoil, a pair of spaced-apart flap side edges extending from the flap hinge line, a flap trailing edge spaced-apart from the flap hinge line and a flap curvature between the flap hinge line and the flap trailing edge. 14. The propulsion system of claim 13 wherein the plurality of exhaust ejection orifices comprises a plurality of pairs of spaced-apart exhaust ejection orifices. 15. The propulsion system of claim 14 wherein the plurality of pairs of exhaust ejection orifices comprises a pair of spaced-apart proximal exhaust ejection orifices generally adjacent to the flap hinge line, a pair of spaced-apart trailing exhaust ejection orifices generally adjacent to the flap trailing edge and a pair of spaced-apart middle exhaust ejection orifices between the proximal exhaust ejection orifices and the trailing exhaust ejection orifices. 16. A method for increasing lift produced along a surface of an airfoil of an aircraft having an airfoil and an engine having an engine cowling provided on the airfoil, the method comprising: providing a propulsion flap having a generally convex exhaust flow surface generally aft of the engine cowling and a plurality of exhaust ejection orifices provided in the exhaust flow surface;extending an extendable airfoil flap from the airfoil, and extending the propulsion flap from the airfoil flap;operating the engine to thereby produce exhaust gases; andejecting at least a portion of the exhaust gases through the exhaust ejection orifices of the propulsion flap. 17. The method of claim 16 wherein the providing a propulsion flap having a plurality of exhaust ejection orifices provided in the exhaust flow surface comprises providing a propulsion flap having a plurality of pairs of spaced-apart exhaust ejection orifices provided in the exhaust flow surface. 18. The method of claim 17 wherein ejecting at least a portion of the exhaust gases through the exhaust ejection orifices of the propulsion flap comprises intermittently ejecting at least a portion of the exhaust gases through the exhaust ejection orifices of the propulsion flap. 19. A propulsion system configured for providing lift to an aircraft, comprising: an aircraft wing;an engine having an engine cowling carried by the aircraft wing and configured to produce exhaust gases that are predominantly directed toward an aft end of the aircraft wing by the engine cowling as engine exhaust;a rear wing flap extendable from the aircraft wing;a generally rectangular propulsion flap disposed aft of the engine cowling and having a flap hinge line extending along the rear wing flap, a pair of spaced-apart flap side edges extending from the flap hinge line, a flap trailing edge extending between the flap side edges, a flap curvature between the flap hinge line and the flap trailing edge and a convex exhaust flow surface defined by the flap curvature;a plurality of exhaust ducts embedded in the propulsion flap and disposed in fluid communication with the engine cowling;a plurality of exhaust flow valves communicating with the plurality of exhaust ducts, respectively;a pair of proximal exhaust ejection orifices, a pair of trailing exhaust ejection orifices and a pair of middle exhaust ejection orifices provided in the exhaust flow surface of the propulsion flap and disposed in fluid communication with the plurality of exhaust ducts; anda controller connected to the plurality of exhaust flow valves and configured to facilitate intermittent flow of at least a portion of the engine exhaust from the pair of proximal exhaust ejection orifices, the pair of trailing exhaust ejection orifices and the pair of middle exhaust ejection orifices. 20. A method for increasing lift produced along a surface of an aircraft wing of an aircraft having an aircraft wing, an engine having an engine cowling provided on the aircraft wing and a rear wing flap extendable from the aircraft wing, the method comprising: providing a propulsion flap generally aft of the engine cowling and comprising: a flap hinge line extending along the rear wing flap;a pair of spaced-apart flap side edges extending from the flap hinge line;a flap trailing edge extending between the flap side edges;a flap curvature between the flap hinge line and the flap trailing edge;a convex exhaust flow surface defined by the flap curvature;a plurality of pairs of exhaust ejection orifices provided in the exhaust flow surface;a plurality of exhaust ducts embedded in the propulsion flap and establishing fluid communication between the engine cowling and the plurality of pairs of exhaust ejection orifices;a plurality of exhaust flow valves communicating with the plurality of exhaust ducts, respectively; anda controller connected to the plurality of exhaust flow valves;operating the engine to thereby produce exhaust gases; and operating the controller to intermittently eject at least a portion of the exhaust gases through the exhaust ejection orifices of the propulsion flap by actuation of the plurality of exhaust flow valves.

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이 특허를 인용한 특허 피인용횟수: 7

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Propulsion system and method for efficient lift generation

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Propulsion system and method for efficient lift generation

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