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1. 发明授权

US08020367B2 Nozzle with yaw vectoring vane 有权
标题翻译：喷嘴与偏航矢量叶片
公开(公告)号：US08020367B2
公开(公告)日：2011-09-20
申请号：US11687539
申请日：2007-03-16
申请人： Michael Jay Toffan , James Lee Salmon , Ronald Clement Hollett , Arthur McCardle
发明人： Michael Jay Toffan , James Lee Salmon , Ronald Clement Hollett , Arthur McCardle
IPC分类号： F02K1/00
CPC分类号： F02K1/085 , F02C3/13 , F02K1/11
摘要： An exhaust vane disposed in a divergent section of an aircraft gas turbine engine exhaust nozzle is sideways pivotable about a vane pivot axis. The nozzle vane pivot axis may be centrally located at an unvectored nozzle throat. Transversely spaced apart upper and lower tips of the exhaust vane may be incorporated to sealingly engage a nozzle outer wall along upper and lower surfaces of the outer wall of the nozzle. The exhaust vane has flat or contoured vane sidewalls and contoured vane sidewalls may be concave. The exhaust vane may have transversely biased apart upper and lower vane sections extending transversely inwardly from the upper and lower tips of the exhaust vane respectively. The exhaust vane may be articulated having upstream and downstream sections separately sideways pivotable about the vane pivot axis and a second pivot axis downstream of and parallel to the vane pivot axis respectively.
摘要翻译：布置在飞机燃气涡轮发动机排气喷嘴的发散部分中的排气扇可围绕叶片枢转轴线侧向枢转。喷嘴叶片枢转轴线可以位于未打开的喷嘴喉部的中心。可以结合排气叶片的相对间隔开的上部和下部尖端，以沿着喷嘴的外壁的上表面和下表面密封地接合喷嘴外壁。排气叶片具有平坦或轮廓的叶片侧壁，并且轮廓叶片侧壁可以是凹形的。排气叶片可以具有横向偏置的上部和下部叶片部分，分别从排气叶片的上部和下部末端横向向内延伸。排气叶片可以铰接，其具有分别侧向地围绕叶片枢转轴线枢转的上游和下游部分，以及分别在叶片枢转轴线的下游并平行于叶片枢转轴线的第二枢转轴线。

2. 发明授权

US06910328B1 Vectorable variable area nozzle 失效
标题翻译：可变面积喷嘴
公开(公告)号：US06910328B1
公开(公告)日：2005-06-28
申请号：US07647524
申请日：1991-01-18
申请人： Nicolas J. Joyce
发明人： Nicolas J. Joyce
IPC分类号： F02K1/00 , F02K1/11 , F02K1/12
CPC分类号： F02K1/11 , F02K1/004 , F02K1/1223
摘要： A vectorable variable area nozzle is formed by a pair of parallel sidewalls, a pair of opposed clamshell elements arranged between the sidewalls and each able to rotate about an axis perpendicular to the sidewalls and a pair of flaps each pivotally lined to the downstream end of one of the clamshell elements.In use the thrust produced by the nozzle can be vectored by rotating the two clamshells about their respective axes.
摘要翻译：可向导的可变区域喷嘴由一对平行的侧壁形成，一对相对的蛤壳元件布置在侧壁之间，每个能够围绕垂直于侧壁的轴线旋转，并且一对翼片各自枢转地排列到一个的下游端的蛤壳元素。在使用中，由喷嘴产生的推力可以通过围绕它们各自的轴线旋转两个蛤壳来驱动。

3. 发明申请

US20030159430A1 Thrust vectoring and variable exhaust area for jet engine nozzle 失效
标题翻译：喷气发动机喷嘴的推力矢量和可变排气区域
公开(公告)号：US20030159430A1
公开(公告)日：2003-08-28
申请号：US10379633
申请日：2003-03-05
发明人： Jean-Pierre Lair
IPC分类号： F02K001/00
CPC分类号： B64C15/02 , F02K1/002 , F02K1/006 , F02K1/04 , F02K1/11 , F02K1/1261 , F02K1/15 , F02K1/54 , F02K1/60 , F02K1/70 , F02K1/76 , F02K1/805 , F05D2240/55 , Y02T50/672
摘要： A jet engine nozzle having a pair of pivoting extension arms and a pair of pivoting shells connected to a jet pipe is provided. The first extension arm is pivotally connected to the jet pipe at a first location, while the second extension arm is pivotally connected to the jet pipe at a second location. Each shell is pivotally connected at both the first and second locations. An axis of rotation associated with the first location is coaxial to an axis of rotation associated with the second location. Independent actuation means are provided to rotate the extension arms and the shells, thereby enabling adjustment of the thrust-vector angle or the exhaust area of the nozzle.
摘要翻译：提供具有一对枢转延伸臂和连接到喷射管的一对枢转壳体的喷气发动机喷嘴。第一延伸臂在第一位置处枢转地连接到喷射管，而第二延伸臂在第二位置枢转地连接到喷射管。每个壳体在第一和第二位置处枢转地连接。与第一位置相关联的旋转轴线与与第二位置相关联的旋转轴线共轴。提供独立的致动装置以旋转延伸臂和壳体，由此能够调节喷嘴的推力矢量角或排气区域。

4. 发明授权

US06381950B1 Engine nozzle arrangement for an aircraft 失效
标题翻译：飞机的发动机喷嘴装置
公开(公告)号：US06381950B1
公开(公告)日：2002-05-07
申请号：US09688682
申请日：2000-10-17
申请人： Colin Whaites , Peter R. House , Robert Brown
发明人： Colin Whaites , Peter R. House , Robert Brown
IPC分类号： F02K304
CPC分类号： B64D33/04 , B64C15/02 , F02K1/11 , F02K1/383 , F02K1/60 , F05D2260/20 , Y02T50/675
摘要： An engine nozzle arrangement for an aircraft comprises a nozzle (18) for hot exhaust gases, and a shroud (20) for the stream of hot exhaust gases emerging from the exhaust nozzle. The shroud includes an intake for a boundary layer of air for cooling the stream of exhaust gases.
摘要翻译：用于飞行器的发动机喷嘴装置包括用于热排气的喷嘴（18）和用于从排气喷嘴出来的热废气流的护罩（20）。护罩包括用于冷却废气流的空气的边界层的进气口。

5. 发明授权

US5392991A Thrust reversing device for jet aircraft engines 失效
标题翻译：喷气式飞机发动机推力换向装置
公开(公告)号：US5392991A
公开(公告)日：1995-02-28
申请号：US71646
申请日：1993-06-03
申请人： Alfredo Gatti , Luigi Gerbi
发明人： Alfredo Gatti , Luigi Gerbi
IPC分类号： F02K1/11 , F02K1/60
CPC分类号： F02K1/60 , F02K1/11
摘要： A thrust reversing nozzle for a jet engine in which a collar is mounted on the discharge nozzle so as to be movable axially relative thereto and between the collar and the nozzle, two thrust reversal half shells are pivotally mounted and, in their closed position, register with and are flush with the collar so that these half shells and the collar extend the nozzle.
摘要翻译：一种用于喷气发动机的推力反向喷嘴，其中轴环安装在排放喷嘴上以便可相对于其并且在轴环和喷嘴之间轴向移动，两个推力反转半壳枢转地安装，并且在其关闭位置中，与套环齐平，使得这些半壳和衣领延伸喷嘴。

6. 发明授权

US4732324A Variable flow area nozzle 失效
标题翻译：可变流域喷嘴
公开(公告)号：US4732324A
公开(公告)日：1988-03-22
申请号：US683675
申请日：1984-12-19
申请人： Douglas J. Nightingale
发明人： Douglas J. Nightingale
IPC分类号： B64D33/04 , F02K1/00 , F02K1/11 , B63H11/00
CPC分类号： F02K1/11 , B64D33/04 , F02K1/002
摘要： A variable flow area nozzle suitable for a gas turbine engine equipped with afterburning means comprises first and second ducts, the second duct pivotably mounted to the first and extending downstream from the first duct thereby defining a fluid flow therethrough. The first duct includes a lip which extends downstream through the second duct, the lip being of width corresponding to the internal width of the second duct thereby defining an exit orifice the flow area of which is controlled by the position of the second duct with respect to the lip. The nozzle further comprises a pressurizable chamber located on a side of the lip remote from the fluid flow path, the chamber being defined at least in part by the lip and a portion of the second duct. A vent hole in the lip is provided for admitting fluid into the chamber from fluid flow path. Fluid pressure in the pressurizable chamber exerts a force on the second duct to provide a moment about the pivotal mounting of the second duct which to an extent counteracts a moment exerted by the fluid flowing through the nozzle. A second pressurizable chamber may also be used for the same purpose.
摘要翻译：适用于配备有后燃烧装置的燃气涡轮发动机的可变流动区域喷嘴包括第一和第二管道，第二管道可枢转地安装到第一管道并且从第一管道的下游延伸，从而限定通过其中的流体流动。第一管道包括通过第二管道向下游延伸的唇缘，该唇缘的宽度对应于第二管道的内部宽度，从而限定出口孔，其流动面积由第二管道相对于嘴唇所述喷嘴还包括位于所述唇缘的远离所述流体流路的一侧的可加压室，所述室至少部分地由所述唇缘和所述第二管道的一部分限定。提供唇缘中的通气孔用于从流体流动路径将流体引入腔室。加压室中的流体压力在第二管道上施加力，以提供围绕第二管道的枢转安装的力矩，其在与流过喷嘴的流体施加的力的作用下抵消。第二可加压室也可以用于相同的目的。

7. 发明授权

US4093122A Integrated divergent exhaust nozzle thrust reverser 失效
标题翻译：集成发散排气喷头推力反向器
公开(公告)号：US4093122A
公开(公告)日：1978-06-06
申请号：US738578
申请日：1976-11-03
申请人： Duane L. Linderman , Felix Hom
发明人： Duane L. Linderman , Felix Hom
IPC分类号： F02K1/11 , F02K1/60 , B64C15/06 , B64D33/04
CPC分类号： F02K1/60 , F02K1/11 , F05D2250/324
摘要： A relatively simple variable area divergent exhaust nozzle and low drag afterbody integrated with a target-type thrust reverser and used in conjunction with a convergent nozzle for application to the propulsion system of a high performance jet powered aircraft. Two or more aerodynamically shaped afterbody surfaces may be pivoted with a common actuation system to form: first an efficient nozzle-afterbody suitable for subsonic operation; second, a divergent nozzle-afterbody for efficient supersonic operation and; third, a target-type thrust reverser for in-flight or ground roll deceleration.
摘要翻译：一个相对简单的可变区域发散排气喷嘴和低阻力后置体与目标型推力反向器集成，并与会聚喷嘴结合使用，适用于高性能喷气动力飞机的推进系统。两个或多个空气动力学形状的后体表面可以用共同的致动系统枢转以形成：首先是适合于亚音速操作的有效的喷嘴后置体; 第二，有效的超音速操作的发散喷嘴; 第三，用于飞行中或地面转向减速的目标型推力反向器。

8. 发明授权

US3874620A Reversing apparatus for a jet engine 失效
标题翻译：喷气发动机的倒车装置
公开(公告)号：US3874620A
公开(公告)日：1975-04-01
申请号：US33972573
申请日：1973-03-09
申请人： BOEING CO
发明人： KAHLER CHARLES , KIMES LUCAS JAMES
IPC分类号： B64D33/04 , F02K1/11 , F02K1/60 , B64C15/04
CPC分类号： B64D33/04 , F02K1/11 , F02K1/60
摘要： A STOL aircraft employs upper surface blowing by mounting jet engines forwardly and above the wings so that the exhaust nozzles of the engines normally open onto the upper airfoil surfaces of the wings. An engine exhaust nozzle is formed by a portion of the upper airfoil surface adjacent to the leading edge of the wing, spaced connecting members extending upwardly from the airfoil, and a channel-shaped panel movably mounted on the connecting members. The panel is movable from a cruise position in which the nozzle directs the engine exhaust stream rearwardly with respect to the longitudinal axis of the engine and a reversing position in which the nozzle directs the exhaust stream upwardly and forwardly with respect to the longitudinal axis of the engine. The movable panel includes a lip door which is nested within the forward portion of the panel during cruise, but which moves forwardly when the panel is in a reversing position to assist in turning the exhaust stream forwardly and to direct the stream outboard with respect to the aircraft. A single powered actuator moves the panel and the lip door from the cruise position to the reversing position.
摘要翻译： STOL飞机采用上表面吹风，通过在机翼的前方和上方安装喷气发动机，使得发动机的排气喷嘴通常打开到机翼的上翼面上。发动机排气喷嘴由上机翼表面的与翼的前缘相邻的部分形成，间隔开的连接构件从翼型向上延伸，以及可移动地安装在连接构件上的通道形面板。面板可以从巡航位置移动，在该位置喷嘴将发动机排气流相对于发动机的纵向轴线向后引导，并且反向位置，喷嘴将废气流相对于所述发动机的纵向轴线向上和向前引导发动机。可移动面板包括在巡航期间嵌套在面板的前部内的唇门，但是当面板处于反转位置时向前移动以帮助向前转动排气流并将流引导到外侧飞机。单个动力执行器将面板和唇门从巡航位置移动到反转位置。

9. 发明授权

US2930186A Discharge nozzles for propulsive jets 失效
标题翻译：推进喷气喷头
公开(公告)号：US2930186A
公开(公告)日：1960-03-29
申请号：US54910755
申请日：1955-11-25
申请人： FREDERICK ASHWOOD PETER , WILLIAM GROSSE GEORGE
发明人： FREDERICK ASHWOOD PETER , WILLIAM GROSSE GEORGE
IPC分类号： F02K1/11
CPC分类号： F02K1/11

10. 发明授权

US2761277A Variable nozzle actuator 失效
标题翻译：可变喷嘴执行器
公开(公告)号：US2761277A
公开(公告)日：1956-09-04
申请号：US27306852
申请日：1952-02-23
申请人： GEN MOTORS CORP
发明人： HOLBROOK GORDON E
IPC分类号： F02K1/11
CPC分类号： F02K1/11 , Y02T50/671 , Y10T74/18944

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