专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US4884748A Fairing flap arrangement 失效
标题翻译：整流罩安排
公开(公告)号：US4884748A
公开(公告)日：1989-12-05
申请号：US239738
申请日：1988-09-02
申请人： Eric J. Ward , Kevin L. Worley , Kenneth M. Pesyna
发明人： Eric J. Ward , Kevin L. Worley , Kenneth M. Pesyna
IPC分类号： F02K1/12
CPC分类号： F02K1/1223 , F02K1/1269 , Y02T50/671
摘要： An external fairing flap (26) is provided with an hydraulic spring (42, 44) for causing the external flap (26) to follow the motion of an exhaust nozzle control flap (18). The external flap (26) is hinged (32) at the leading edge thereof, and contacts the control flap (18) via corresponding rubstrips (40, 36) at the flap trailing edges (28, 38).
摘要翻译：外部整流罩（26）设置有用于使外部挡板（26）跟随排气喷嘴控制挡板（18）的运动的液压弹簧（42,44）。外部翼片（26）在其前缘处铰接（32），并通过翼片后缘（28,38）处的对应的搓纸（40,36）与控制翼片（18）接触。

2. 发明授权

US08616850B2 Gas turbine engine blade mounting arrangement 有权
标题翻译：燃气轮机发动机叶片安装布置
公开(公告)号：US08616850B2
公开(公告)日：2013-12-31
申请号：US12814098
申请日：2010-06-11
申请人： Eric J. Ward , Brian K. Richardson
发明人： Eric J. Ward , Brian K. Richardson
IPC分类号： F01D5/02
CPC分类号： F01D5/3007 , F01D5/323 , F05D2300/501 , Y02T50/672
摘要： A mounting arrangement for a gas turbine engine blade having a root employs a lightweight, simple and economical leaf spring spacer which biases the blade root in a radially outward direction to minimize unwanted movement of the root within a conforming slot in a blade hub under conditions such as windmilling when centrifugal force alone is inadequate to tightly seal the root within the slot.
摘要翻译：具有根部的燃气涡轮发动机叶片的安装装置采用重量轻，简单且经济的叶片间隔件，其将叶片根部沿径向向外的方向偏置，以使根部在叶片毂内的适形狭槽内的不期望的运动最小化，作为单独离心力不足以将根部紧紧地密封在槽内的风车。

3. 发明授权

US5031836A Flexible fairing for airframe/nozzle interface 失效
标题翻译：柔性整流罩机身/喷嘴接口
公开(公告)号：US5031836A
公开(公告)日：1991-07-16
申请号：US550423
申请日：1990-07-10
申请人： Eric J. Ward
发明人： Eric J. Ward
IPC分类号： F02K1/12
CPC分类号： F02K1/1292 , F02K1/12
摘要： A flexible fairing 13 is provided which includes an aerodynamic surface 20 composed of a plurality of closely spaced, telescopic fairing members 14 and a moveable fairing panel 18. One end 15 of each fairing member 14 is pivotably secured to a divergent flap 11 of a thrust vectoring nozzle, and the other end 17 of the fairing member is pivotably secured to the fairing panel 18 which is slideably mounted to the static structure of a nozzle 19 of a gas turbine engine. The flexible fairing 13 adjusts to accommodate both translational and rotational movement of the divergent flap relative to an airframe fairing 10, thereby maintaining an aerodynamic surface 20 between the airframe fairing 10 and the divergent flap 11 of the nozzle.
摘要翻译：提供了一种柔性整流罩13，其包括由多个紧密间隔的可伸缩整流罩构件14和可移动的整流罩18组成的空气动力学表面20.每个整流罩构件14的一端15可枢转地固定到推力整流罩的另一端17可枢转地固定在可滑动地安装在燃气轮机的喷嘴19的静态结构上的整流罩18上。柔性整流罩13调整以适应发散翼片相对于机身整流罩10的平移和旋转运动，由此在机身整流罩10和喷嘴的发散翼片11之间保持空气动力学表面20。

4. 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。

5. 发明授权

US5797544A C/D nozzle with synchronizing ring link suspension 失效
标题翻译： C / D喷嘴具有同步环链接悬挂
公开(公告)号：US5797544A
公开(公告)日：1998-08-25
申请号：US721889
申请日：1996-09-27
申请人： Eric J. Ward
发明人： Eric J. Ward
IPC分类号： F02K1/00 , F02K1/12 , F02K1/15 , B64C15/08
CPC分类号： F02K1/004 , F02K1/1223 , F02K1/15 , F05D2260/15 , Y02T50/671
摘要： The flaps of the C/D exhaust nozzle for a gas turbine engine are arranged to obtain synchronous movement relative to each other and the interconnecting fulcrum links are attached to a coaxially mounted combined piston/sync ring by an H-shaped link. One link from one convergent flap is connected to one of the fulcrum links and the adjacent convergent flap is connected to the same fulcrum link. The redundant synchronization provided by the H-shaped links and flap connections provide damping of the flap train. The fulcrum links are judiciously mounted between adjacent convergent flaps.
摘要翻译：用于燃气涡轮发动机的C / D排气喷嘴的翼片被布置成获得相对于彼此的同步运动，并且互连支点链节通过H形连杆附接到同轴安装的组合活塞/同步环。来自一个会聚舌片的一个连接件连接到一个支点连杆，并且相邻的会聚舌片连接到相同的支点连杆。由H形连杆和襟翼连接提供的冗余同步提供了挡板系统的阻尼。支点链接明智地安装在相邻的收缩瓣之间。

6. 发明授权

US5102049A Vane control mechanism 失效
标题翻译：叶片控制机制
公开(公告)号：US5102049A
公开(公告)日：1992-04-07
申请号：US124631
申请日：1987-11-24
申请人： Eric J. Ward
发明人： Eric J. Ward
IPC分类号： F02K1/12 , F02K1/62
CPC分类号： F02K1/12 , F02K1/62
摘要： A thrust reverser in a two dimensional jet engine exhaust nozzle employs a plurality of reverser apparati that maintain a constant flow throat area, for example, in the reverse throat mode. A single reverser apparatus includes an actuator that operates through a lever upon linkage and a coupler to drive a set of parallel vanes and at least one independent vane. The parallel vanes are connected by a parallelogram of links to the coupler. The independent vanes move in a manner as defined by a cam having a preselected path therein that causes the independent vanes to move in a desired manner to provide the constant throat area.
摘要翻译：二维喷气发动机排气喷嘴中的推力反向器采用多个反向装置，其保持恒定的流动喉部区域，例如在反向喉部模式。单个反向器装置包括致动器，其通过连杆操作通过杆和联接器来驱动一组平行叶片和至少一个独立叶片。平行叶片通过连接器的平行四边形连接到耦合器。独立叶片以由其中具有预选路径的凸轮限定的方式移动，其使得独立叶片以期望的方式移动以提供恒定的喉部区域。

7. 发明授权

US09169849B2 Gas turbine engine compressor stator seal 有权
标题翻译：燃气涡轮发动机压缩机定子密封
公开(公告)号：US09169849B2
公开(公告)日：2015-10-27
申请号：US13466549
申请日：2012-05-08
申请人： Eric J. Ward
发明人： Eric J. Ward
IPC分类号： F01D11/02 , F04D29/10 , F04D29/16 , F04D29/32 , F01D5/06 , F01D11/00 , F04D19/02
CPC分类号： F04D29/164 , F01D5/06 , F01D11/001 , F01D11/02 , F04D19/02 , F04D29/102 , F04D29/321
摘要： A compressor section for use in a gas turbine engine has a plurality of compressor stages. Each compressor stage is provided with a rotor hub, and each rotor hub mounts a plurality of compressor blades. A rotor drum extends between adjacent rotor hubs. A plurality of stator stages have an outer ring and a radially inner ring. A plurality of vanes extend between the outer and inner rings. An inner surface of the inner ring is spaced by a gap from an outer surface of the rotor drum. The rotor drum is provided with a plurality of blades having a general airfoil shape to resist leakage across the gap.
摘要翻译：用于燃气涡轮发动机的压缩机部具有多个压缩机级。每个压缩机级设置有转子毂，并且每个转子毂安装多个压缩机叶片。转子鼓在相邻的转子毂之间延伸。多个定子级具有外环和径向内环。多个叶片在外圈和内圈之间延伸。内环的内表面与转子鼓的外表面间隔开间隙。转子鼓设置有多个具有一般翼型形状的叶片，以抵抗间隙的渗漏。

8. 发明授权

US08967952B2 Gas turbine engine duct blocker that includes a duct blocker rotor with a plurality of roller elements 有权
标题翻译：燃气涡轮发动机管道阻塞器，其包括具有多个滚子元件的管道阻塞转子
公开(公告)号：US08967952B2
公开(公告)日：2015-03-03
申请号：US13335577
申请日：2011-12-22
申请人： James Jones , John H. Maurer , Eric J. Ward , Roger W. Bursey, Jr.
发明人： James Jones , John H. Maurer , Eric J. Ward , Roger W. Bursey, Jr.
IPC分类号： F01B25/02
CPC分类号： F01D17/141 , F02C9/18 , F02K1/822 , F02K3/075 , F05D2240/50 , F05D2250/411 , Y02T50/675
摘要： A rotational duct blocker for a gas turbine engine includes a duct blocker rotor and a duct blocker stator. The duct blocker rotor includes a plurality of first flow apertures extending axially therethrough, and a plurality of roller elements connected to an inner rotor platform. The first flow apertures are arranged circumferentially around the inner rotor platform. The duct blocker stator includes a plurality of second flow apertures extending axially therethrough, and a roller element track located radially within the inner rotor platform and in rolling contact with the roller elements. The second flow apertures are arranged circumferentially around an inner stator platform that is located axially adjacent to the inner rotor platform. The duct blocker rotor rotates relative to the duct blocker stator to regulate fluid flowing between the first flow apertures and the second flow apertures.
摘要翻译：用于燃气涡轮发动机的旋转管道阻塞器包括管道阻塞转子和管道阻塞器定子。导管阻塞转子包括多个沿轴向延伸穿过的第一流动孔，以及连接到内转子平台的多个滚子元件。第一流动孔围绕内转子平台周向地布置。导管阻塞器定子包括沿轴向延伸穿过其中的多个第二流动孔径以及径向位于内部转子平台内并与滚子元件滚动接触的滚子元件轨道。第二流动孔围绕位于轴向邻近内转子平台的内定子平台周向地布置。管道阻塞器转子相对于管道阻塞器定子旋转以调节在第一流动孔和第二流动孔之间流动的流体。

9. 发明申请

US20130164118A1 GAS TURBINE ENGINE DUCT BLOCKER THAT INCLUDES A DUCT BLOCKER ROTOR WITH A PLURALITY OF ROLLER ELEMENTS 有权
标题翻译：气体涡轮发动机阻塞器，其包括具有多个滚子元件的导管阻塞器转子
公开(公告)号：US20130164118A1
公开(公告)日：2013-06-27
申请号：US13335577
申请日：2011-12-22
申请人： James Jones , John H. Maurer , Eric J. Ward , Roger W. Bursey, JR.
发明人： James Jones , John H. Maurer , Eric J. Ward , Roger W. Bursey, JR.
IPC分类号： F01D17/00 , F01D9/02
CPC分类号： F01D17/141 , F02C9/18 , F02K1/822 , F02K3/075 , F05D2240/50 , F05D2250/411 , Y02T50/675
摘要： A rotational duct blocker for a gas turbine engine includes a duct blocker rotor and a duct blocker stator. The duct blocker rotor includes a plurality of first flow apertures extending axially therethrough, and a plurality of roller elements connected to an inner rotor platform. The first flow apertures are arranged circumferentially around the inner rotor platform. The duct blocker stator includes a plurality of second flow apertures that extending axially therethrough, and a roller element track located radially within the inner rotor platform and in rolling contact with the roller elements. The second flow apertures are arranged circumferentially around an inner stator platform that is located axially adjacent to the inner rotor platform. The duct blocker rotor rotates relative to the duct blocker stator to regulate fluid flowing between the first flow apertures and the second flow apertures.
摘要翻译：用于燃气涡轮发动机的旋转管道阻塞器包括管道阻塞转子和管道阻塞器定子。导管阻塞转子包括多个沿轴向延伸穿过的第一流动孔，以及连接到内转子平台的多个滚子元件。第一流动孔围绕内转子平台周向地布置。导管阻塞器定子包括多个第二流动孔，其轴向延伸穿过其中，以及滚子元件轨道，径向地位于内转子平台内并与滚子元件滚动接触。第二流动孔围绕位于轴向邻近内转子平台的内定子平台周向地布置。管道阻塞器转子相对于管道阻塞器定子旋转以调节在第一流动孔和第二流动孔之间流动的流体。

10. 发明授权

US06694723B2 Valve assembly for gas turbine engine 有权
标题翻译：燃气轮机发动机用阀组件
公开(公告)号：US06694723B2
公开(公告)日：2004-02-24
申请号：US10109109
申请日：2002-03-27
申请人： Eric J. Ward
发明人： Eric J. Ward
IPC分类号： F02K100
CPC分类号： F02C7/12 , F01D17/141 , F05D2250/411 , Y02T50/671 , Y02T50/675
摘要： A valve assembly for supplying cooling air to a nozzle of a gas turbine engine. The nozzle can move between a first configuration and a second configuration. The valve assembly includes a first member having openings that receive cooling air. The valve assembly also includes a second member having openings. The second member resides adjacent the first member to receive the cooling air from the first member. Finally, the valve assembly includes actuator for moving the first member from a first position, which allows a first flow rate of cooling air to pass through the openings, to a second position, which allows a second flow rate of cooling air to pass through the openings. The second flow rate is less than the first flow rate.
摘要翻译：一种用于向燃气涡轮发动机的喷嘴供给冷却空气的阀组件。喷嘴可以在第一配置和第二配置之间移动。阀组件包括具有容纳冷却空气的开口的第一构件。阀组件还包括具有开口的第二构件。第二构件邻近第一构件驻留以从第一构件接收冷却空气。最后，阀门组件包括用于使第一构件从第一位置移动的致动器，该第一位置允许冷却空气的第一流量通过开口至第二位置，该第二位置允许冷却空气的第二流量通过开口第二流量小于第一流量。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式