Variable area fan nozzle fan flutter management system
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F04D-015/00
F02C-009/20
F02K-003/06
출원번호
US-0362250
(2012-01-31)
등록번호
US-9074531
(2015-07-07)
발명자
/ 주소
Grabowski, Zbigniew M.
Morris, Robert J.
Carmichael, Ray W.
출원인 / 주소
UNITED TECHNOLOGIES CORPORATION
대리인 / 주소
Carlson, Gaskey & Olds P.C.
인용정보
피인용 횟수 :
1인용 특허 :
30
초록
A gas turbine engine includes a controller that controls a fan blade flutter characteristic through control of a variable area fan nozzle.
대표청구항▼
1. A gas turbine engine for an aircraft, comprising: a core engine defined about an axis;a fan driven by said core engine about said axis;a core nacelle defined at least partially about said core engine;a fan nacelle defined around said fan and at least partially around said core nacelle;a variable
1. A gas turbine engine for an aircraft, comprising: a core engine defined about an axis;a fan driven by said core engine about said axis;a core nacelle defined at least partially about said core engine;a fan nacelle defined around said fan and at least partially around said core nacelle;a variable area fan nozzle (VAFN) to define a fan exit area downstream of said fan between said fan nacelle and said core nacelle; anda controller operable to control a fan blade flutter characteristic through control of said VAFN, said controller adjusting said VAFN based on at least one of an aircraft Mach number (M) and a low spool rotational speed (N1), said controller adjusting said VAFN based on one of at least two operating schedules, wherein said at least two operating schedules includes a normal flight conditions schedule and an icing flight conditions schedule, wherein, when in said icing flight conditions schedule, said controller limits operation of said VAFN relative to said normal flight conditions schedule such that said VAFN is instructed to be fully closed for an entirety of a first number of flight stages in said normal operating conditions flight schedule and a second number of flight stages in said icing flight conditions schedule, the second number of flight stages greater than the first number of flight stages. 2. The engine as recited in claim 1, wherein said VAFN is opened during aircraft take-off. 3. The engine as recited in claim 1, wherein, during an aircraft climb, said VAFN moves from fully open to fully closed. 4. The engine as recited in claim 3, wherein said VAFN moves from fully open to fully closed when M is less than about 0.25 and N1 is within a range of about 90%-100% of a maximum N1 (N1MAX). 5. The engine as recited in claim 4, wherein said VAFN moves from fully open to fully closed within about 7 minutes. 6. The engine as recited in claim 1, wherein, during an aircraft cruise, said VAFN is fully closed. 7. The engine as recited in claim 6, wherein said VAFN is fully closed when M is greater than about 0.6 and N1 is within a range of about 70% to about 80% of a maximum N1 (N1MAX). 8. The engine as recited in claim 1, wherein, during an aircraft descent, said VAFN moves from fully closed to fully open. 9. The engine as recited in claim 8, wherein said VAFN moves from fully closed to fully open when M is less than about 0.4 and N1 is within a range of about 70% to about 90% of a maximum N1 (N1MAX). 10. The engine as recited in claim 1, wherein said controller is operable to determine possible changes in said fan blade flutter boundary. 11. The engine as recited in claim 10, wherein said controller is operable to detect changes in said fan blade flutter boundary caused by changes in components of said engine, and changes to operating conditions. 12. The engine as recited in claim 1, including a fan and a gear train, wherein the gear train reduces the rotational speed of the fan relative to a shaft of the gas turbine engine, the shaft rotatably coupled to a low pressure compressor of the engine. 13. The engine as recited in claim 1, wherein a bypass flow path is defined between said core nacelle and said fan nacelle, said bypass flow defines a bypass ratio greater than about ten (10). 14. The engine as recited in claim 1, wherein: when said controller adjusts said VAFN based on said normal flight conditions schedule, said VAFN is open during an aircraft take-off, an aircraft climb, an aircraft descent, and an aircraft approach, and said VAFN is fully closed during the entirety of an aircraft cruise; andwhen said controller adjusts said VAFN based on said icing flight conditions schedule, said VAFN is at least partially open during an aircraft takeoff, and said VAFN is fully closed during the entirety of an aircraft climb, an aircraft cruise, an aircraft descent, and an aircraft approach. 15. A gas turbine engine for an aircraft, comprising: a core engine defined about an axis;a fan driven by said core engine about said axis;a core nacelle defined at least partially about said core engine;a fan nacelle defined around said fan and at least partially around said core nacelle;a variable area fan nozzle (VAFN) to define a fan exit area downstream of said fan between said fan nacelle and said core nacelle; anda controller operable to control a fan blade flutter characteristic through control of said VAFN, said controller adjusting said VAFN based on one of at least two operating schedules, wherein said at least two operating schedules includes a normal flight conditions schedule and an icing flight conditions schedule, wherein, when in said icing flight conditions schedule, said controller limits operation of said VAFN relative to said normal flight conditions schedule such that such that said VAFN is instructed to be fully closed for an entirety of a first number of flight stages in said normal operating conditions flight schedule and a second number of flight stages in said icing flight conditions schedule, the second number of flight stages greater than the first number of flight stages. 16. The engine as recited in claim 15, wherein said VAFN includes a first component movable relative to said fan nacelle. 17. The engine as recited in claim 16, wherein said first component is one of a flap and a cowl. 18. The engine as recited in claim 15, wherein, when said controller adjusts said VAFN based on said normal flight conditions schedule, said VAFN is open during an aircraft take-off, an aircraft climb, an aircraft descent, and an aircraft approach, and said VAFN is fully closed during an entirety of an aircraft cruise. 19. The engine as recited in claim 18, wherein, when said controller adjusts said VAFN based on said icing flight conditions schedule, said VAFN is at least partially open during an aircraft takeoff, and said VAFN is fully closed during an entirety of an aircraft climb, an aircraft cruise, an aircraft descent, and an aircraft approach.
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이 특허에 인용된 특허 (30)
Bozich Daniel J. (San Diego CA) Wagenfeld Robert (Westport CT), Active gas turbine (jet) engine noise suppression.
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.
Brodell Robert F. (Marlborough CT) Hovan Edward J. (Manchester CT) Selfors Steven T. (Somerville MA) Loffredo Constantino V. (Newington CT) Duesler Paul W. (Manchester CT), Nacelle and mounting arrangement for an aircraft engine.
Bonissone, Piero Patrone; Xue, Feng; Varma, Anil; Goebel, Kai Frank; Yan, Weizhong; Eklund, Neil Holger White, System and method for equipment remaining life estimation.
Schaum Hans H. (St. Bruno CAX) Tedstone Donald J. (St. Lambert CAX) Ma Ching-Yee (St. Lambert CAX) Sanderson John J. (St. Bruno CAX), Turbine engine with induced pre-swirl at compressor inlet.
Duesler Paul W. ; Loffredo Constantino V. ; Prosser ; Jr. Harold T. ; Jones Christopher W., Variable area fan exhaust nozzle having mechanically separate sleeve and thrust reverser actuation systems.
Banks Ivor (Georgetown CAX) Heikurinen Kari J. (Oakville CAX) Sanderson John J. (Oakville CAX) Wilford Donald F. (Oakville CAX), Variable flow radial compressor inlet flow fences.
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