Aft engine for an aircraft

General Electric Company

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Aft engine for an aircraft

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64D-029/04 B64D-027/10 B64C-021/06 F02K-003/06 B64C-001/16 B64D-027/20 B64D-033/02
출원번호	US-0859523 (2015-09-21)
등록번호	US-9957055 (2018-05-01)
발명자 / 주소	Marrinan, Patrick Michael Becker, Thomas Lee Murrow, Kurt David
출원인 / 주소	General Electric Company
대리인 / 주소	GE Aviation Patent Operation
인용정보	피인용 횟수 : 0 인용 특허 : 40

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A propulsion system for an aircraft including a plurality of primary engines is provided. The plurality of primary engines includes at least a first primary engine and a second primary engine, each configured for mounting to a respective one of a pair of wings of the aircraft. The propulsion system additionally includes an aft engine configured for mounting at a tail section of the aircraft. The plurality of primary engines are sized to provide an amount of thrust sufficient for the aircraft to takeoff without use of the aft engine, such that the aft eng...

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1. A propulsion system for an aircraft having a pair of wings and a tail section, the propulsion system comprising: a plurality of primary engines including at least a first primary engine and a second primary engine, the first primary engine configured for mounting to a first of the pair of wings of the aircraft, and the second primary engine configured for mounting to a second of the pair of wings of the aircraft; andan aft engine configured for mounting at the tail section of the aircraft, the plurality of primary engines sized to provide an amount of thrust sufficient for the aircraft to takeoff without use of the aft engine;wherein the aft engine comprises a fan shaft mechanically coupled to a power source located at least partially within a fuselage of the aircraft and one or more structural members configured as variable inlet guide vanes extending between a nacelle and the fuselage of the aircraft that include a flap at an aft end configured to rotate about a radial axis between a variety of positions to vary a direction of the air flowing thereover. 2. The propulsion system of claim 1, wherein the first primary engine and the second primary engine are each configured as a turbofan jet engine. 3. The propulsion system of claim 1, wherein the aft engine is a boundary layer ingestion fan. 4. The propulsion system of claim 3, wherein the boundary layer ingestion fan includes a nacelle defining an inlet extending approximately three hundred and sixty degrees around a fuselage of the aircraft at the tail section of the aircraft when the boundary layer ingestion fan is mounted to the aircraft. 5. The propulsion system of claim 1, wherein the first primary engine and the second primary engine are each sized to generate a maximum primary engine thrust when operated at maximum capacity, and wherein the aft engine is sized to generate up to about eighty-five percent of the maximum primary engine thrust when operated at maximum capacity. 6. The propulsion system of claim 1, wherein the first primary engine and the second primary engine are each sized to generate a maximum primary engine thrust when operated at maximum capacity, and wherein the aft engine is sized to generate up to about seventy-five percent of the maximum primary engine thrust when operated at maximum capacity. 7. An aircraft comprising: a fuselage extending between a nose end and a tail section;a pair of wings extending outward from opposing sides of the fuselage at a location between the nose end and the tail section;a plurality of primary engines, at least a first of the plurality of primary engines mounted to a first of the pair of wings and at least a second of the plurality of primary engines mounted to a second of the pair of wings, each of the plurality of primary engines sized to generate a maximum primary engine thrust when operated at maximum capacity; andan aft engine mounted at the tail section of the aircraft, the aft engine sized to generate a maximum aft engine thrust when operated at maximum capacity, the maximum aft engine thrust being at least ten percent greater than or less than the maximum primary engine thrust;wherein the aft engine comprises a fan shaft mechanically coupled to a power source located at least partially within a fuselage of the aircraft and one or more structural members configured as variable inlet guide vanes extending between a nacelle and the fuselage of the aircraft that include a flap at an aft end configured to rotate about a radial axis between a variety of positions to vary a direction of the air flowing thereover. 8. The aircraft of claim 7, wherein the plurality of primary engines are sized to generate an amount of thrust sufficient for the aircraft to takeoff without use of the aft engine. 9. The aircraft of claim 7, wherein the plurality of primary engines are sized to 1′ thrust when each of the plurality of primary engines are operated at maximum capacity, and wherein the maximum aft engine thrust is less than or equal to about thirty percent of the cumulative maximum primary engines thrust. 10. The aircraft of claim 7, wherein the plurality of primary engines are each configured as turbofan jet engines. 11. The aircraft of claim 7, wherein the aft engine is a boundary layer ingestion fan. 12. The aircraft of claim 11, wherein the boundary layer ingestion fan includes a nacelle defining an inlet extending approximately three hundred and sixty degrees around the fuselage of the aircraft at the tail section the aircraft. 13. The aircraft of claim 11, wherein the boundary layer ingestion fan includes a nacelle and a fan having a plurality of fan blades, and wherein the nacelle extends around and encloses the plurality of fan blades of the fan. 14. The aircraft of claim 7, wherein the maximum aft engine thrust is equal to about eighty-five percent or less of the maximum primary engine thrust. 15. A method for operating an aircraft having a pair of wings, an aft engine mounted at a tail section of the aircraft, and a plurality of primary aircraft engines, at least a first of the plurality of primary engines mounted to a first of the pair of wings and at least a second of the plurality of primary engines mounted to a second of the pair of wings, the method comprising: operating the plurality of primary aircraft engines to generate an amount of thrust sufficient for the aircraft to takeoff; andoperating the aft engine at less than full capacity during a takeoff operating mode of the aircraft; wherein the aft engine comprises a fan shaft mechanically coupled to a power source located at least partially within a fuselage of the aircraft and one or more structural members configured as variable inlet guide vanes extending between a nacelle and the fuselage of the aircraft that include a flap at an aft end configured to rotate about a radial axis between a variety of positions to vary a direction of the air flowing thereover. 16. The method of claim 15, wherein operating the aft engine less than full capacity during takeoff operating mode includes operating the aft engine at less than about seventy-five percent capacity during the takeoff operating mode. 17. The method of claim 15, further comprising operating the aft engine at fifty percent capacity or more during at least one of a climb operating mode of the aircraft or a cruise operating mode of the aircraft. 18. The method of claim 15, wherein each of the plurality of primary aircraft engines are sized to provide a maximum primary engine thrust when operated at full capacity, wherein the maximum primary engine thrusts of each of the plurality of primary aircraft engines are substantially the same, wherein the aft engine is sized to provide a maximum aft engine thrust when operated at full capacity, and wherein the maximum aft engine thrust is less than about eighty-five percent of the maximum primary engine thrust. 19. The method of claim 15, wherein the plurality of primary aircraft engines together generate a cumulative maximum primary engines thrust when operated at full capacity, wherein the aft engine defines a maximum aft engine thrust when operated at full capacity, and wherein the maximum aft engine thrust is less than about thirty percent of the cumulative maximum primary engines thrust. 20. The method of claim 15, further comprising providing energy from one or more of the plurality of primary aircraft engines to the aft engine to operate the aft engine after the takeoff operating mode of the aircraft is complete.

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