[특허]Aircraft vapour trail control system

ROLLS-ROYCE PLC

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특허 상세정보

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내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Aircraft vapour trail control system

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	G06F-007/00 B64D-031/06 B64D-033/04
출원번호	US-0674823 (2015-03-31)
등록번호	US-9399521 (2016-07-26)
우선권정보	GB-1405894.5 (2014-04-02)
발명자 / 주소	Swann, Peter
출원인 / 주소	ROLLS-ROYCE PLC
대리인 / 주소	Oliff PLC
인용정보	피인용 횟수 : 1 인용 특허 : 3

초록
▼

The invention concerns an aircraft propulsion control system for an aircraft with a plurality of gas turbine engines mounted at different spaced positions relative to an airframe. One or more sensor is arranged to sense a condition indicative of vapor trail formation by an exhaust flow from one or more of the plurality of engines. A controller is arranged to be responsive to thrust demand for the aircraft and selectively to control each of the engines so as to modify the exhaust flow of at least one engine relative to at least one further engine according to the positions of the engines on the airframe. The proximity of an engine to a vortical wake flow created by the airframe may be used to determine suitable exhaust flow modifications. The controller may output a separate throttle control signal to each engine and/or may adjust the fuel composition supplied to each engine.

대표
청구항
▼

1. An aircraft propulsion control system comprising: a plurality of gas turbine engines mounted at different spaced positions relative to an airframe;one or more sensor arranged to sense a condition indicative of a property of a vapour trail formed by an exhaust flow from one or more of the plurality of engines; anda controller arranged to be responsive to said sensed condition and a thrust demand for the aircraft and selectively to control operation of each of the engines so as to modify the exhaust flow of at least one engine relative to at least one further engine according to the positions of the engines on the airframe relative to one or more portion of the airframe that induces a vortical wake flow during flight. 2. An aircraft propulsion control system according to claim 1, comprising three or more gas turbine engines. 3. An aircraft propulsion control system according to claim 1, wherein the controller assesses the flow interaction between the exhaust flow and the vortical wake flow for the at least one engine and the exhaust flow of the at least one engine is modified by the controller according to the outcome of said assessment. 4. An aircraft propulsion control system according to claim 1, wherein at least one engine is laterally spaced from an airframe centreline by a greater distance that at least one further engine. 5. An aircraft propulsion control system according to claim 1, wherein the exhaust flow of the at least one engine is modified by the controller according to the proximity said at least one engine to a wing tip, relative to a further engine. 6. An aircraft propulsion control system according to claim 1, wherein the controller is arranged to modify the content and/or flow rate of at least one engine exhaust flow in response to a condition indicative of vapour trail formation. 7. An aircraft propulsion control system according to claim 6, wherein the controller is arranged to control one or more engine operation variable so as to modify the throttle, efficiency and/or soot emissions of said at least one engine. 8. An aircraft propulsion control system according to claim 7, wherein the controller is arranged to concurrently increase the one or more operation variable on at least one engine and decrease the one or more operation variable on at least one further engine. 9. An aircraft propulsion control system according to claim 1, wherein the modification of the exhaust flow of at least one engine by the controller comprises controlling different levels of thrust output between the at least one engine and the at least one further engine according to the positions of the engines on the airframe. 10. An aircraft propulsion control system according to claim 1, wherein the controller accesses one or more engine thrust, efficiency or soot emission model and modifies the operation of each engine away from a normal or optimal efficiency setting in dependence upon said model. 11. An aircraft propulsion control system according to claim 1, wherein the controller undertakes a search process to identify a value of an engine operation variable for one or more engine which satisfies a threshold or target value of a contrail characteristic for one or more engine. 12. An aircraft propulsion control system according to claim 1, wherein the sensor comprises one or more ambient condition sensor and/or a contrail detection sensor. 13. An aircraft propulsion control system according to claim 1, wherein the controller determines a likelihood of persistence of a vapour trail formed under the sensed condition indicative of vapour trail formation and selectively modifies the exhaust flow of the one or more engine in response to said determination. 14. An aircraft propulsion control system according to claim 1, wherein the sensed condition comprises a level of ice super-saturation in ambient air. 15. An aircraft propulsion control system according to claim 1, wherein the controller adjusts the fuel composition delivered to the at least one engine relative to the at least one further engine responsive to said sensed condition. 16. An aircraft propulsion control system according to claim 15, comprising a plurality of fuel sources on board the aircraft, each fuel source comprising fuel of a different fuel composition, and a fuel delivery regulator arranged to receive fuel from a plurality of fuel sources, the controller being arranged to control operation of the regulator so as to vary the fuel composition delivered to the at least one engine. 17. A data carrier comprising machine readable instructions for operation of a controller of an engine control system to: receive sensor readings indicative of a vapour trail formation condition by an exhaust flow from one or more of a plurality of gas turbine engines mounted at different spaced positions relative to an airframe;receive a thrust demand signal for the aircraft; andselectively output control signals to each of the engines so as to modify the exhaust flow of at least one engine relative to at least one further engine according to the positions of the engines on the airframe relative to one or more portion of the airframe that induces a vortical wake flow during flight. 18. An aircraft propulsion control method, comprising: receiving at an aircraft engine controller sensor readings indicative of a vapour trail formation condition by an exhaust flow from one or more of a plurality of gas turbine engines mounted at different spaced positions relative to an airframe;receiving a thrust demand signal for the aircraft at the aircraft engine controller; andprocessing the received readings and thrust demand signal and selectively outputting control signals to modify the exhaust flow of at least one engine relative to at least one further engine according to the positions of the engines on the airframe relative to one or more portion of the airframe that induces a vortical wake flow during flight.

이 특허에 인용된 특허 (3)

이 특허를 인용한 특허 (1)

Swann, Peter, Aircraft vapour trail control system.

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Aircraft vapour trail control system

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Aircraft vapour trail control system

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이 특허에 인용된 특허 (3)

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IPC 상위 출원인

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IPC 상세정보(version : 201201)

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