[특허]Thrust vectorable exhaust nozzle

[미국특허] Thrust vectorable exhaust nozzle 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-009/30 B64C-009/38 B64C-015/06 F02K-001/12
출원번호	US-0618796 (1975-10-02)
발명자 / 주소	Konarski Mieczyslaw (Fairfield OH) Nash Dudley O. (Cincinnati OH)
출원인 / 주소	General Electric Company (Cincinnati OH 02)
인용정보	피인용 횟수 : 23 인용 특허 : 0

초록 ▼

A gas turbine engine flight maneuverable nozzle for installation within an aircraft wing or the like is provided with pivotably connected convergent and divergent flaps partially defining an exhaust stream flow path. A third flap, pivotably connected to the divergent flap, partially defines the wing control surface contour. In the cruise and flight maneuver modes, an actuation system provides synchronous movement of the convergent and divergent flaps to control, in a predetermined relationship, the areas of the exhaust stream flow path throat and exit. A vectoring actuator, carried by the main actuator, overrides the main actuator in the flight maneuvering mode and causes the divergent flap to pivot downward, thus deflecting the exhaust stream. Simultaneously, the control surface contour defining flap is repositioned to increase the control surface camber thereby increasing lift. Flow separation from the wing control surface is prevented by the effect of super-circulation due to the exhaust stream. Flap actuator forces are reduced by providing the convergent flap with a pressure-balancing feature. Therein one surface of the flap is exposed to pressurized air from the compressor portion of the engine to create a moment about the flap pivot axis which is counter to the moment created by the pressure of the exhaust stream upon the flap exhaust stream flow path defining surface.

대표청구항 ▼

A flight maneuverable exhaust device for use with a gas turbine engine comprising: first variable position flap means partially defining an exhaust stream flow path having a throat and an exit, said first flap means being pivotably connected to an upstream fixed duct portion for varying exhaust stream flow path area convergence; second variable position flap means further defining the flow path, said second flap means being downStream of and pivotably connected to the first flap means for providing variable exhaust stream expansion control in a first operating mode and exhaust stream deflection in a second operating mode; third variable position flap means pivotably connected to the second flap means proximate their respective downstream extremities, said third flap means partially defining a variable contour flight control surface; and an actuation system operatively connected to at least one of said flap means for synchronously moving said first, second and third flap means to control, in a predetermined relationship, the exhaust stream flow path throat area and the exhaust stream flow path exit area.

이 특허를 인용한 특허 (23) 인용/피인용 타임라인 분석

Thayer Edward B. (Jupiter FL) Ward Eric J. (West Palm Beach FL), 2-D propulsive lift nozzle.
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Plumpe, Jr., William Henry, Apparatus and method for thrust vector control.
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Madden William M. (Palm Springs FL), Area two-dimensional converging/diverging nozzle.
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Kupratis, Daniel Bernard; Suydam, Adam Joseph; Hugill, Christopher G., Control scheme using variable area turbine and exhaust nozzle to reduce drag.
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Thayer Edward B. (Jupiter FL), Divergent flap actuation system for a two-dimensional exhaust nozzle.
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Nash Dudley O. (Cincinnati OH), Exhaust nozzle.
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Johnson,James Edward, Flade gas turbine engine with fixed geometry inlet.
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Markstein David J. ; Clements Martin A. ; Ausdenmoore Robert M. ; Lippmeier William C., Hydraulic failsafe system and method for an axisymmetric vectoring nozzle.
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Walker, Alan Richard; Wooten, Jr., William Harvey; Sutherland, William Van; Holowach, Joseph, Infrared suppressing two dimensional vectorable single expansion ramp nozzle.
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Joubert Raymond J. M. (Savigny sur Orge FRX), Movable blast pipes for jet engines.
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Zamora, Sean P.; Murphy, Michael J.; Dillard, Gary J.; Estes, Glenn R., Nozzle assembly with flow conduits.
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Hapke Donald W. (Issaquah WA), Pressure balance nonaxisymmetric high aspect ratio afterburner convergent nozzle.
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Mendez Juan A. (Miami FL) Mayers John L. (Lake Park FL), Pressure control system for convergent-divergent exhaust nozzle.
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Roberts, Steven D.; Damgaard, Jocelyn Charis, Retainer for suspended thermal protection elements in a gas turbine engine.
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Petty, Dale William, Retractable exhaust liner segment for gas turbine engines.
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Petty, Dale William, Retractable exhaust liner segment for gas turbine engines.
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Hardy Jean-Marie E. C. (Le Mee Sur Seine FRX) Jourdain Gerard E. A. (Saintry Sur Seine FRX) Soligny Marcel R. (Chevilly Larue FRX), Supersonic nozzle for a turbojet engine.
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Mazenq, Lionel, System for steering, about its axes of rotation, a moving body propelled by jet reaction, particularly a missile.
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Pierluissi, Anthony F.; Pesyna, Kenneth M., Three stream, variable area fixed aperture nozzle with pneumatic actuation.
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Nash Dudley O. (Forest Park OH), Thrust reverser for an asymmetric aircraft exhaust nozzle.
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Bouiller Philippe Pierre,FRX ; Bourquin Pierre-Yves,FRX ; Kettler Daniel,FRX ; Ruis Jean-Pierre,FRX, Turbo jet engine exhaust nozzle with masked gas jet.
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Woodward Clifford S. (Bristol GB2), Vectorable exhaust nozzle for a gas turbine engine.
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Madden William M. (Palm Springs FL), Viol exhaust nozzle with veer flap extension.
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IPC	Description
A	생활필수품
A62	인명구조; 소방(사다리 E06C)
A62B	인명구조용의 기구, 장치 또는 방법(특히 의료용에 사용되는 밸브 A61M 39/00; 특히 물에서 쓰이는 인명구조 장치 또는 방법 B63C 9/00; 잠수장비 B63C 11/00; 특히 항공기에 쓰는 것, 예. 낙하산, 투출좌석 B64D; 특히 광산에서 쓰이는 구조장치 E21F 11/00)
A62B-1/08	.. 윈치 또는 풀리에 제동기구가 있는 것

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[미국특허] Thrust vectorable exhaust nozzle 원문보기