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1. 发明授权

US5343698A Hexagonal cluster nozzle for a rocket engine 失效
标题翻译：用于火箭发动机的六角形集束喷嘴
公开(公告)号：US5343698A
公开(公告)日：1994-09-06
申请号：US54915
申请日：1993-04-28
申请人： Lane Porter , Edward B. Thayer
发明人： Lane Porter , Edward B. Thayer
IPC分类号： B64G1/00 , F02K9/30 , F02K9/97 , F02K1/00
CPC分类号： F02K9/97 , F05D2250/132
摘要： A rocket engine thrust nozzle assembly is disclosed wherein combustion products from a plurality of rocket engines having hexagonally-shaped exhaust areas flow to the inlet of a main nozzle that transitions the flow of the combustion products from a non-circular flow area to a circular flow area.
摘要翻译：公开了一种火箭发动机推力喷嘴组件，其中具有六角形排气区域的多个火箭发动机的燃烧产物流到主喷嘴的入口，该主喷嘴将燃烧产物的流动从非圆形流动区域转变为圆形流动区。

2. 发明授权

US5706650A Vectoring nozzle using injected high pressure air 失效
标题翻译：使用注射高压空气的矢量喷嘴
公开(公告)号：US5706650A
公开(公告)日：1998-01-13
申请号：US513100
申请日：1995-08-09
申请人： Edward B. Thayer
发明人： Edward B. Thayer
IPC分类号： F02K1/00 , F02K1/28
CPC分类号： F02K1/008 , F02K1/28 , Y02T50/671
摘要： An exhaust nozzle for a gas turbine engine where pitch and yaw vectoring is achieved using fluidics by injecting high pressure air into the exhaust stream. The injected high pressure air deflects the exhaust stream, vectoring the aircraft accordingly. The injected high pressure air for vectoring is selectively injected. A pivoting manifold 44 allows for injection of either ram air (52) or vectoring high pressure air (56) into the exhaust flow.
摘要翻译：一种用于燃气涡轮发动机的排气喷嘴，其中使用流体通过将高压空气注入排气流中来实现俯仰和偏航矢量。喷射的高压空气使排气流偏转，相应地对飞机进行引导。注入用于矢量化的高压空气被选择性地注入。枢转歧管44允许将冲压空气（52）或向高压空气（56）引导到排气流中。

3. 发明授权

US5619851A 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：US5619851A
公开(公告)日：1997-04-15
申请号：US308156
申请日：1989-02-08
申请人： Donald E. Johnson , Rafael A. Bustamante , Edward B. Thayer , Richard J. Peckham
发明人： Donald E. Johnson , Rafael A. Bustamante , Edward B. Thayer , Richard J. Peckham
IPC分类号： F02K9/97 , F02K11/00
CPC分类号： F02K9/97 , F02K9/972 , F02K9/976
摘要： A diverging rocket engine nozzle has a system to allow ambient gases to flow from the outside to the inside of the nozzle's chamber. The system includes a plurality of coolant conduits adjacent the inside surface of the nozzle. The conduits are spaced apart to provide a plurality of vent openings which extends from the inside to the outside of the nozzle's chamber. A plurality of valves controls gas flow through the vent passages when the pressure outside of the nozzle is greater than the pressure directly adjacent the inside surface of the nozzle. The coolant conduits cool and shield the valves at their points of attachment to the outside of the nozzle.
摘要翻译：发散火箭发动机喷嘴具有允许环境气体从外部流到喷嘴室的内部的系统。该系统包括与喷嘴的内表面相邻的多个冷却剂导管。导管间隔开以提供从喷嘴室的内部延伸到外部的多个通气口。当喷嘴外部的压力大于直接靠近喷嘴内表面的压力时，多个阀门控制通过通气通道的气体流动。冷却剂管道在其连接到喷嘴外部的点处冷却并屏蔽阀。

4. 发明授权

US4760960A Linkage for area controlled, thrust vectoring vane cascade 失效
标题翻译：联动区域控制，推力矢量叶栅级联
公开(公告)号：US4760960A
公开(公告)日：1988-08-02
申请号：US53289
申请日：1987-05-22
申请人： Eric J. Ward , Philip R. Scott , Edward B. Thayer
发明人： Eric J. Ward , Philip R. Scott , Edward B. Thayer
IPC分类号： F02K1/00 , F02K1/62 , F02K1/12
CPC分类号： F02K1/62 , F02K1/002 , Y02T50/671
摘要： A linkage for area controlled thrust vectoring comprising of vane cascade (26) having a plurality of vanes (28, 29, 30) pivotable in unison and a flow regulating vane (36) oriented to provide a constant collection gas flow area is provided with a mechanical linkage for orienting the vanes (28, 29, 30) and the flow regulating vane (36) responsive to a single linear actuator (59).

5. 发明授权

US5335489A Gas turbine vectoring exhaust nozzle 失效
标题翻译：燃气轮机矢量排气喷嘴
公开(公告)号：US5335489A
公开(公告)日：1994-08-09
申请号：US89921
申请日：1993-07-09
申请人： Edward B. Thayer
发明人： Edward B. Thayer
IPC分类号： F02K1/00 , F02K1/12
CPC分类号： F02K1/002 , F02K1/008
摘要： An exhaust nozzle has variable convergent flaps, ejector flaps, and short divergent flaps spaced inwardly from the ejector flaps, cooling air is introduced through the opening between the divergent and ejector flaps. When the nozzle is vectored, the size of the opening is increased in the region of the nozzle experiencing higher static pressure.
摘要翻译：排气喷嘴具有可变的会聚翼片，喷射器翼片和从喷射器翼片向内间隔的短发散翼片，冷却空气通过发散板和喷射器翼片之间的开口引入。当喷嘴被向导时，在喷嘴经受更高静压的区域中开口的尺寸增大。

6. 发明授权

US5161752A In-flight reverser 失效
公开(公告)号：US5161752A
公开(公告)日：1992-11-10
申请号：US806502
申请日：1991-12-13
申请人： Jefre H. Cockerham , Edward B. Thayer
发明人： Jefre H. Cockerham , Edward B. Thayer
IPC分类号： B64C15/02 , F02K1/00 , F02K1/12 , F02K1/60
CPC分类号： F02K1/60 , B64C15/02 , F02K1/008 , F02K1/1223 , F05D2250/31
摘要： Increased aircraft control is achieved by combining reverse thruster operation with splay capability. Each of the four door sets has a pair of vanes controllable to various parallel positions. Maximum opening at 26.degree. from the vertical decreases in each direction from the maximum position. The vanes may be controlled to effect yaw and pitch control while maintaining a constant total effective flow area. Back pressure on the turbine is thereby unaffected.

7. 发明授权

US4382551A Flap-type nozzle with built-in reverser 失效
标题翻译：带内置反向器的翻盖式喷嘴
公开(公告)号：US4382551A
公开(公告)日：1983-05-10
申请号：US264726
申请日：1981-05-18
申请人： Edward B. Thayer
发明人： Edward B. Thayer
IPC分类号： F02K1/58 , F02K1/12 , F02K1/62
CPC分类号： F02K1/62 , F02K1/12 , F02K1/123 , Y02T50/671
摘要： A lightweight exhaust nozzle/thrust reverser for a gas turbine engine comprises a flap-type exhaust nozzle with a thrust reverser door built into a cutout within each flap. The flaps may be hinged at their forward edges to the engine exhaust duct and may either be actuated or may float freely. Preferably, when the reverser doors are stowed they blend smoothly with the internal and external surfaces of the flaps. Actuation means deploys the doors such that they extend into the gas flow path and coact with each other to form a wall which blocks the axial flow of gas, and they simultaneously open the cutout within which they are disposed and redirect the exhaust gas through the cutouts in an upstream direction. In a preferred embodiment the flaps define the divergent portion of a convergent/divergent exhaust nozzle.
摘要翻译：用于燃气涡轮发动机的轻质排气喷嘴/推力反向器包括翼形排气喷嘴，其具有内置在每个翼片内的切口中的推力反向器门。襟翼可以在它们的前边缘处铰接到发动机排气管道，并且可以被致动或者可以自由地浮动。优选地，当反向门被收起时，它们与襟翼的内表面和外表面平滑地混合。致动装置部署门，使得它们延伸到气体流动路径中并且彼此协作以形成阻挡气体的轴向流动的壁，并且它们同时打开它们所设置的切口，并且通过切口重新排列废气在上游方向。在优选实施例中，翼片限定了收敛/发散的排气喷嘴的发散部分。

8. 发明授权

US5261605A Axisymmetric nozzle with gimbled unison ring 失效
标题翻译：带对称螺纹的轴对称喷嘴
公开(公告)号：US5261605A
公开(公告)日：1993-11-16
申请号：US873485
申请日：1992-04-22
申请人： George H. McLafferty , Edward B. Thayer , Jim D. Stewart
发明人： George H. McLafferty , Edward B. Thayer , Jim D. Stewart
IPC分类号： F02K1/00 , F02K1/12 , B64C15/02
CPC分类号： F02K1/1223 , F02K1/008
摘要： A thrust vectoring exhaust nozzle (10) includes a plurality of flaps (16-22) and seals (24-28) positioned by a unison ring (52) and flap links (54-60).
摘要翻译：推力矢量排气喷嘴（10）包括多个翼片（16-22）和由协调环（52）和翼片连杆（54-60）定位的密封件（24-28）。

9. 发明授权

US4819876A Divergent flap actuation system for a two-dimensional exhaust nozzle 失效
标题翻译：用于二维排气喷嘴的不同翼片致动系统
公开(公告)号：US4819876A
公开(公告)日：1989-04-11
申请号：US66365
申请日：1987-06-25
申请人： Edward B. Thayer
发明人： Edward B. Thayer
IPC分类号： B64D33/04 , F02K1/00 , F02K1/12 , F02K1/15 , F02K1/62 , F16H21/40
CPC分类号： F02K1/006 , F02K1/1223 , F02K1/1284 , F02K1/15 , F02K1/625 , F05D2250/324 , Y02T50/671
摘要： A divergent flap actuation system for a two-dimensional exhaust nozzle for a gas turbine engine powered aircraft includes stationary sidewalls (2) and (3) with oppositely disposed movable divergent flaps (10) and (39) located therebetween, and flush mounted rotatable divergent disks (22) and (49) with drive pins (21) and (48) attached thereto for engaging the flaps. Each divergent disk utilizes an individual actuator to provide independent movement of the rearward edges of the flaps in response to disk rotation. Utilizing flush mounted disks for controlling the position of the rearward edges of the opposed flaps minimizes sidewall thickness and allows use of full length, tapered sidewalls to minimize drag and nozzle weight while maximizing flexibility in thrust control.

10. 发明授权

US4714197A 2-D propulsive lift nozzle 失效
标题翻译： 2-D推进式提升喷嘴
公开(公告)号：US4714197A
公开(公告)日：1987-12-22
申请号：US881375
申请日：1986-07-02
申请人： Edward B. Thayer , Eric J. Ward
发明人： Edward B. Thayer , Eric J. Ward
IPC分类号： F02K1/00 , F02K1/12 , B64C15/00
CPC分类号： F02K1/1223 , F02K1/006
摘要： A two-dimensional nozzle for directing the exhaust of a gas turbine engine includes two spaced apart vertical sidewalls (16), an upper flap assembly (18) and a lower flap assembly (20). The upper flap assembly (20) includes at least a dorsal flap (22) pivotable about a first fixed axis (24). The lower flap assembly (20) includes a ventral flap (28) centrally pivotable about a second fixed axis (30) for creating a dual throat exhaust flow path.
摘要翻译：用于引导燃气涡轮发动机的排气的二维喷嘴包括两个间隔开的垂直侧壁（16），上部翼片组件（18）和下部翼片组件（20）。上部翼片组件（20）包括至少一个绕第一固定轴线（24）枢转的背部翼片（22）。下翼片组件（20）包括腹侧翼片（28），其围绕第二固定轴线（30）居中枢转，用于产生双喉排气流动路径。

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