Variable contour nacelle assembly for a gas turbine engine
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-007/042
F02K-003/06
B64D-033/02
F02C-007/045
출원번호
US-0772287
(2007-07-02)
등록번호
US-9228534
(2016-01-05)
발명자
/ 주소
Jain, Ashok K.
Winter, Michael
출원인 / 주소
United Technologies Corporation
대리인 / 주소
Carlson, Gaskey & Olds
인용정보
피인용 횟수 :
0인용 특허 :
61
초록▼
A gas turbine engine includes a compressor section, a combustor section, a turbine section and a nacelle assembly which at least partially surrounds the compressor section, the combustor section and the turbine section. At least a portion of the nacelle assembly includes an adjustable contour. The p
A gas turbine engine includes a compressor section, a combustor section, a turbine section and a nacelle assembly which at least partially surrounds the compressor section, the combustor section and the turbine section. At least a portion of the nacelle assembly includes an adjustable contour. The portion of the nacelle assembly including the adjustable contour is selectively moveable between a first portion and a second position to influence the adjustable contour of the nacelle assembly. A controller identifies an abnormal aircraft operating condition and selectively moves the portion of the nacelle assembly including the adjustable contour between the first position and the second position in response to detecting the abnormal aircraft operating condition.
대표청구항▼
1. A gas turbine engine, comprising: a compressor section, a combustor section, and a turbine section;a nacelle assembly at least partially surrounding at least one of said compressor section, said combustor section and said turbine section, wherein said nacelle assembly includes an inlet lip sectio
1. A gas turbine engine, comprising: a compressor section, a combustor section, and a turbine section;a nacelle assembly at least partially surrounding at least one of said compressor section, said combustor section and said turbine section, wherein said nacelle assembly includes an inlet lip section and a cowl section that each include an adjustable contour, each of said inlet lip section and said cowl section including a first surface that faces radially inward and a second surface that faces radially outward, each of said first surfaces and said second surfaces being moveable to influence said adjustable contours; anda controller that identifies an abnormal aircraft operating condition, wherein said controller selectively moves said inlet lip section and said cowl section of said nacelle assembly in response to detecting said abnormal aircraft operating condition. 2. The gas turbine engine as recited in claim 1, wherein said abnormal aircraft operating condition includes at least one of a windmilling engine-out condition, a crosswind take-off condition, a fan blade-out condition, a high angle of attack condition and a yaw condition. 3. The gas turbine engine as recited in claim 1, comprising a sensor that produces a signal representing said abnormal aircraft operating condition and communicates said signal to said controller. 4. The gas turbine engine as recited in claim 1, comprising an actuator assembly in communication with said controller to move said nacelle assembly in response to detecting said abnormal aircraft operating condition. 5. The gas turbine engine as recited in claim 4, comprising at least one of an internal linkage, a plurality of bellows and a shape memory alloy that is actuated by said actuator assembly to influence said adjustable contours. 6. The gas turbine engine as recited in claim 1, wherein at least one of said first surfaces and said second surfaces are moveable between a first position and a second position, and said second position is axially upstream relative to said first position. 7. The gas turbine engine as recited in claim 1, wherein at least one of said first surfaces and said second surfaces are moveable between a first position and a second position, and said second position is radially outward relative to said first position. 8. The gas turbine engine as recited in claim 1, wherein said inlet lip section is pivoted relative to said cowl section, wherein said inlet lip section is inwardly pivoted at an angle relative to a plane positioned at a foremost end of said nacelle assembly. 9. The gas turbine engine as recited in claim 1, comprising a plurality of bellows that influence said adjustable contours. 10. The gas turbine engine as recited in claim 1, comprising a shape memory alloy that influences said adjustable contours. 11. The gas turbine engine as recited in claim 1, wherein said abnormal aircraft operating condition includes at least one of a windmilling engine-out condition, a fan blade-out condition, a high angle of attack condition and a yaw condition. 12. The gas turbine engine as recited in claim 1, wherein said abnormal aircraft operating condition is a windmilling engine-out condition. 13. The gas turbine engine as recited in claim 1, wherein said abnormal aircraft operating condition is a crosswind condition. 14. The gas turbine engine as recited in claim 1, wherein said abnormal aircraft operating condition is a fan blade-out condition. 15. The gas turbine engine as recited in claim 1, wherein said abnormal aircraft operating condition is a yaw condition. 16. The gas turbine engine as recited in claim 1, wherein said first surfaces and said second surfaces are moveable between a first position and a second position, and said second position is both axially upstream and readily outward relative to said first position.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (61)
Kota,Sridhar; Hetrick,Joel A., Adaptive compliant wing and rotor system.
Lahti Daniel J. (Cincinnati OH) Yates David E. (Cincinnati OH) Mungur Parmanand (West Chester OH) Stockman Norbert O. (Batavia OH), Hybrid laminar flow nacelle.
Cornett Jack E. (Cincinnati OH) Saunders ; Jr. Andrew A. (Cincinnati OH) Marvin Ira E. (Fairfield OH) Beitler Richard S. (Cincinnati OH), Integrated control system for a gas turbine engine.
Raffy Pierre M. (Saint-Germain Laxis FRX) Andre Pierre A. (Paris FRX) Girault Jean-Pierre Y. B. (Dammarie les Lys FRX) Richter Gerhard (Boissise le Roi FRX) Thevenin Jean-Claude P. H. P. (Saint-Maur-, Method and device for reducing the noise of turbo-machines.
Maier Mark S. (West Palm Beach FL) Gamble Eric J. (Jupiter FL) Wilson Jack W. (West Palm Beach FL) Calzadilla Eliott L. (North Palm Beach FL) Goetz Gerald F. (Seattle WA), Nacelle air pump for vector nozzles for aircraft.
Laborie Daniel J. (Cincinnati OH) Marban Joseph R. (Springdale OH) Schulze Wallace M. (West Chester OH) Baumbick Robert J. (West Chester OH), Nacelle cooling and ventilation system.
Laborie Daniel J. (Cincinnati OH) Marban Joseph R. (Springdale OH) Schulze Wallace M. (West Chester OH) Baumbick Robert J. (West Chester OH), Nacelle cooling and ventilation system.
Lee Ching-Pang (Cincinnati OH) Savage Joseph W. (Maineville OH) Bobo Melvin (Cincinnati OH), Scaled heat transfer surface with protruding ramp surface turbulators.
Gupta, Anurag; Graziosi, Paolo; Mani, Ramani, System and method for actively changing an effective flow-through area of an inlet region of an aircraft engine.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.