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11. 发明授权

US4591097A Thrust reverser/exhaust nozzle assembly for a gas turbine engine 失效
标题翻译：用于燃气涡轮发动机的推力反向器/排气喷嘴组件
公开(公告)号：US4591097A
公开(公告)日：1986-05-27
申请号：US611041
申请日：1984-05-16
申请人： Edward B. Thayer
发明人： Edward B. Thayer
IPC分类号： B64C25/42 , B64D33/04 , F02K1/62 , B64C15/00
CPC分类号： B64C25/423 , B64D33/04 , F02K1/62 , Y02T50/671
摘要： An improved thrust reverser/exhaust nozzle assembly has a plurality of blocker devices located in the divergent section of the exhaust nozzle and a plurality of deflector devices located in the convergent section of the nozzle. The blocker and deflector devices are linked together such that they move simultaneously and maintain a substantially constant engine flowrate during transitions of the engine between forward and reverse thrust conditions.
摘要翻译：改进的推力反向器/排气喷嘴组件具有位于排气喷嘴的发散部分中的多个阻塞装置和位于喷嘴的会聚部分中的多个偏转装置。阻塞器和偏转装置连接在一起，使得它们同时移动，并且在前进和反向推力条件之间的发动机转变期间保持基本恒定的发动机流量。

12. 发明授权

US3973731A Flap-type two-dimensional nozzle 失效
标题翻译：翼型二维喷嘴
公开(公告)号：US3973731A
公开(公告)日：1976-08-10
申请号：US640377
申请日：1975-12-12
申请人： Edward B. Thayer
发明人： Edward B. Thayer
IPC分类号： F02K1/00 , F02K1/12 , B64C15/06
CPC分类号： F02K1/12 , F02K1/006
摘要： A flap-type, two-dimensional nozzle for use with thrust creating vehicles which operate at both subsonic and supersonic speeds includes a rectangular exhaust with a convergent-divergent balanced flap system at the top and the bottom thereof. The top and bottom flap systems can be controlled individually or together in order to achieve their desired objective. The flap systems move between a position of minimum throat area and maximum throat area to achieve one range of control while both flap systems can move to an inner position providing for thrust reversal. Thrust vector control can be obtained by assymmetric individual positioning of the flap systems with respect to the engine centerline.
摘要翻译：用于以亚音速和超音速操作的推力产生车辆的翼形二维喷嘴包括在顶部和底部具有会聚发散平衡翼片系统的矩形排气口。顶部和底部襟翼系统可以单独控制或一起控制，以达到其期望的目的。翼片系统在最小喉部区域和最大喉部区域的位置之间移动，以实现一个范围的控制，同时两个翼片系统可以移动到提供推力反转的内部位置。推力矢量控制可以通过翼片系统相对于发动机中心线的不对称单独定位来获得。

13. 发明授权

US4993641A Gas turbine spherical exhaust nozzle 失效
标题翻译：燃气轮机球形排气喷嘴
公开(公告)号：US4993641A
公开(公告)日：1991-02-19
申请号：US427054
申请日：1989-10-26
申请人： Debora F. Kehret , Edward B. Thayer
发明人： Debora F. Kehret , Edward B. Thayer
IPC分类号： F02K1/00
CPC分类号： F02K1/008 , F05D2250/241
摘要： A spherical exhaust nozzle for a gas turbine engine having gimbal mounted convergent-divergent flaps in which cooling air for the flaps is ducted through the convergent flap pivots and the convergent flaps are actuated by actuators connected to the gimbal structure.
摘要翻译：一种用于燃气涡轮发动机的球形排气喷嘴，其具有万向节安装的会聚 - 发散翼片，其中用于翼片的冷却空气通过会聚翼片枢转并且会聚翼片由连接到万向节结构的致动器致动。

14. 发明授权

US4848664A Yaw thrust vectoring exhaust nozzle 失效
标题翻译： Yaw推力矢量排气喷嘴
公开(公告)号：US4848664A
公开(公告)日：1989-07-18
申请号：US129819
申请日：1987-12-07
申请人： Edward B. Thayer
发明人： Edward B. Thayer
IPC分类号： F02K1/00 , F02K1/12 , F02K1/62
CPC分类号： F02K1/12 , F02K1/008 , F02K1/1223 , F02K1/62 , Y02T50/671
摘要： A yaw and pitch thrust vectoring exhaust nozzle (10) includes upper and lower divergent flap assemblies (22, 24) each divided by oppositely skewed diagonal hinges (58, 60). Vertical sidewalls (27, 28) are also hinged to open the nozzle outlet laterally during yaw thrust.
摘要翻译：偏航和俯仰推力向量排气喷嘴（10）包括上和下发散翼片组件（22,24），每个翼片组件由相对倾斜的对角铰链（58,60）分开。垂直侧壁（27,28）也铰接以在偏航推力期间横向打开喷嘴出口。

15. 发明授权

US4836451A Yaw and pitch convergent-divergent thrust vectoring nozzle 失效
标题翻译：俯仰和俯仰会聚发散推力矢量喷嘴
公开(公告)号：US4836451A
公开(公告)日：1989-06-06
申请号：US095294
申请日：1987-09-10
申请人： Paul W. Herrick , Edward B. Thayer , Jim D. Stewart
发明人： Paul W. Herrick , Edward B. Thayer , Jim D. Stewart
IPC分类号： F02K1/00 , F02K1/11 , F02K1/12 , F02K1/60
CPC分类号： F02K1/11 , F02K1/008 , F02K1/1223 , F02K1/123 , F02K1/60 , F05D2250/323 , F05D2250/324 , Y02T50/671
摘要： A yaw and pitch thrust vectoring exhaust nozzle includes a spherical collar, and two surrounding clam shells hinged to a gimbal ring and pivotal about an axis perpendicular to the clam shell hinge axis. The clam shells define a variable area nozzle throat (42) which can be selectively directed vertically by rotation of the clam shells about the hinge axis (38), or horizontally by rotation of the clam shells and gimbal ring about the pivot axis (30), thereby biasing the nozzle exhaust flow vector. Divergent flaps (44, 46) further direct the exhaust downstream of the nozzle throat (42). '
摘要翻译：偏航和俯仰推力矢量排气喷嘴包括球形轴环和两个环绕的蛤壳，铰接到万向节环上并围绕垂直于蛤壳铰链轴线的轴线枢转。蛤壳限定可变区域喷嘴喉部42，其可以通过蛤壳围绕铰链轴线（38）旋转而被选择性地垂直定向，或者通过围绕枢转轴线（30）的蛤壳和万向节环的旋转水平地选择性地定向，从而偏压喷嘴排气流动矢量。发散翼片（44,46）进一步引导喷嘴喉部（42）下游的排气。

16. 发明授权

US4805401A Control vent for diverting exhaust nozzle 失效
标题翻译：用于转向排气喷嘴的排气口
公开(公告)号：US4805401A
公开(公告)日：1989-02-21
申请号：US86342
申请日：1987-08-18
申请人： Edward B. Thayer , Herman L. Stevens
发明人： Edward B. Thayer , Herman L. Stevens
IPC分类号： F02K1/00 , F02K1/62 , F02K3/02
CPC分类号： F02K1/002 , F02K1/62 , Y02T50/671
摘要： A thrust vectoring exhaust nozzle (6) is provided with a vent bypass (38) and flow control valve (44) to vent a portion (43) of the exhaust gas (2) only during diversion of the exhaust gas (2) into an alternative gas flow path (18).
摘要翻译：推力向量排气喷嘴（6）设置有排气旁路（38）和流量控制阀（44），以仅在排气（2）转入排气口（2）时排出废气（2）的一部分（43）替代气体流动路径（18）。

17. 发明授权

US4753392A Two dimensional gas turbine engine exhaust nozzle 失效
标题翻译：二维燃气轮机发动机排气喷嘴
公开(公告)号：US4753392A
公开(公告)日：1988-06-28
申请号：US667708
申请日：1984-11-02
申请人： Edward B. Thayer , George H. McLafferty
发明人： Edward B. Thayer , George H. McLafferty
IPC分类号： F02K9/86 , F02K1/12 , F02K1/60 , F02K1/62
CPC分类号： F02K1/60 , F02K1/12 , F02K1/1223
摘要： A two dimensional exhaust nozzle for a gas turbine engine having reverse thrust capability includes a pair of spaced apart converging flaps which are able to rotate about their respective axes until their downstream edges meet along the engine centerline to block the flow of gases through the engine and to redirect the flow through fixed area reverser outlet ports. The axes about which each convergent flap rotates are spaced inwardly from their respective convergent flap surfaces. The flaps themselves cover the outlet ports when the flaps are in forward thrust operating positions. The flaps move away from and unblock the outlets as they rotate to their reverse thrust position. The distance between the flap axis and its convergent surface is critical to being able to use short flaps while obtaining large reverser outlet areas.
摘要翻译：用于具有反向推力能力的燃气涡轮发动机的二维排气喷嘴包括一对间隔开的会聚翼片，其能够围绕它们各自的轴线旋转，直到它们的下游边缘沿着发动机中心线相遇，以阻挡气体通过发动机的流动，将流量重定向通过固定区域反向器出口端口。每个收敛翼片旋转的轴线与它们各自的收敛翼片表面间隔开。当襟翼处于向前推力操作位置时，襟翼本身覆盖出口。当它们旋转到其反向推力位置时，翼片离开和解除插座。襟翼轴与其收敛表面之间的距离对于能够在获得大的逆向出口区域时能够使用短襟翼是至关重要的。

18. 发明授权

US5683033A Rocket nozzle for a rocket engine 失效
标题翻译：用于火箭发动机的火箭喷嘴
公开(公告)号：US5683033A
公开(公告)日：1997-11-04
申请号：US629112
申请日：1990-12-11
申请人： Edward B. Thayer
发明人： Edward B. Thayer
IPC分类号： F02K9/82 , B63H25/46 , B05B12/00 , F02C7/10
CPC分类号： F02K9/82
摘要： This invention relates to rocket engines which have a rocket nozzle for expanding hot, highly pressurized rocket gases and more particularly, to a high expansion ratio nozzle for such an engine.
摘要翻译：本发明涉及具有火箭喷嘴的火箭发动机，该火箭发动机用于扩展热的，高度加压的火箭气体，更具体地说，涉及用于这种发动机的高膨胀比喷嘴。

19. 发明授权

US5292069A Convertible plug nozzle 失效
标题翻译：可转换插头喷嘴
公开(公告)号：US5292069A
公开(公告)日：1994-03-08
申请号：US87827
申请日：1993-07-07
申请人： Edward B. Thayer
发明人： Edward B. Thayer
IPC分类号： F02K1/00 , F02K1/40
CPC分类号： F02K1/006
摘要： A plug nozzle is convertible to and from an open nozzle by moving several components. The convergent flap moves between an outboard convergent flap position and a central plug position. Divergent flaps, hinged to the convergent flaps, move between the outboard divergent flap position and a central contacting position within the plug. Plug surface flaps are moved to the inboard position where they form the plug surface from an outboard position.
摘要翻译：塞子喷嘴通过移动多个部件可转换到开放喷嘴和从开口喷嘴转换。收敛翼片在外侧收敛舌片位置和中心插头位置之间移动。铰接在会聚翼片上的发散襟翼在舷外发散襟翼位置和插头内的中心接触位置之间移动。插头表面襟翼移动到内侧位置，在那里它们从外侧位置形成插头表面。

20. 发明授权

US5209432A Aircraft reverser port door 失效
标题翻译：飞机倒车门口
公开(公告)号：US5209432A
公开(公告)日：1993-05-11
申请号：US908138
申请日：1992-07-02
申请人： Gary D. Roberge , Edward B. Thayer
发明人： Gary D. Roberge , Edward B. Thayer
IPC分类号： F02K1/80
CPC分类号： F02K1/805
摘要： Doors sealing radial flow ports are opened by rotation which slides the doors away from the ports. All doors rotate about a longitudinal centerline of the aircraft. Each flow port has its inlet seal surface with a center of curvature offset from the longitudinal axis. Rotation of the door toward the open position relieves and releases contact between the door and the port inlet seal surface.
摘要翻译：密封径向流动端口的门通过旋转而打开，门将门从端口滑出。所有门围绕飞机的纵向中心线旋转。每个流动口具有其入口密封表面，其中心曲率偏离纵向轴线。门向打开位置的旋转释放并释放门与入口密封面之间的接触。

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