公开(公告)号：EP1961944B1

公开(公告)日：2013-07-31

申请号：EP08250312.9

申请日：2008-01-25

Applicant: United Technologies Corporation

Inventor： Kehret, Debora F. ,  Farah, Jorge I.

IPC: F02K1/82 ,  F02K1/12

CPC classification number: F02K1/1223 ,  F02K1/822 ,  Y02T50/675

公开(公告)号：EP1378651B1

公开(公告)日：2012-05-30

申请号：EP03254239.1

申请日：2003-07-03

Applicant: United Technologies Corporation

Inventor： Allore, James P. ,  Paul, Stephen A. ,  Stoner, Charles D.

IPC: F02K1/12 ,  F02K1/82

CPC classification number: F02K1/1223 ,  F02K1/06 ,  F02K1/822 ,  Y02T50/671 ,  Y02T50/675

公开(公告)号：EP2096291A1

公开(公告)日：2009-09-02

申请号：EP09250446.3

申请日：2009-02-20

Applicant: General Electric Company

Inventor： Senile, Darrell Glenn ,  Boehm, Valentine Robert, Jr. ,  Renggli, Bernarnd James

IPC: F02K1/12 ,  F02K1/80

CPC classification number: F02K1/1223 ,  F02K1/80

Abstract: An aircraft gas turbine engine exhaust nozzle basesheet (52) includes longitudinally extending plurality of basesheet segments (100). Each of the basesheet segments (100) includes a panel body (106) between segment leading and trailing edges (108, 109) and slidable sealing joints (134) with slidingly un-restrained center surfaces (135) between adjacent segment leading and trailing edges (108, 109). Segmented first and second basesheet side edges (60, 62) first and second segment side edges (104, 105) of the basesheet segments (100) respectively. Slidably sealingly engaged overlapping flanges (119) at the segment leading and trailing edges (108, 109) include tacked together transversely spaced apart first and second distal ends (153, 155) of the overlapping flanges (119). Leading and trailing edge ribs (94, 95, 96, 97) supporting the overlapping flanges (119) are clipped together with longitudinally spaced apart and transversely extending forward and aft slits (282, 284) in retainers (180). A spine (67) includes transverse stiffeners (220) with first and second stiffener distal ends (221, 223) attached to longitudinally spaced apart sets of transversely extending first and second spine tabs (224, 226) of the spine (67).

Abstract translation: 飞机燃气涡轮发动机排气喷嘴底片（52）包括纵向延伸的多个基片段（100）。 每个基片段（100）包括在区段前缘和后缘（108,109）之间的面板主体（106）和可滑动的密封接头（134），在相邻的区段前缘和后缘之间具有滑动地不受约束的中心表面（135） （108,109）。 分段的第一和第二基片侧边缘（60,62）分别是基片段（100）的第一和第二分段侧边缘（104,105）。 在所述段前缘和所述后缘（108,109）处的可滑动地密封地接合的重叠凸缘（119）包括在所述重叠凸缘（119）的横向间隔开的第一和第二远端（153,155）上。 支撑重叠凸缘（119）的前缘和后缘肋（94,95,96,97）与保持器（180）中的纵向间隔开的和横向延伸的前后狭缝（282,284）夹在一起。 脊（67）包括横向加强件（220），其中第一和第二加强件远端（221,223）连接到脊（67）的横向延伸的横向延伸的第一和第二脊突片（224,226）的组。

公开(公告)号：EP1764498B1

公开(公告)日：2009-05-06

申请号：EP06253792.3

申请日：2006-07-20

Applicant: United Technologies Corporation

Inventor： Peters, Donald William

IPC: F02K1/12

CPC classification number: F02K1/1223

公开(公告)号：EP1978232A2

公开(公告)日：2008-10-08

申请号：EP08250849.0

申请日：2008-03-12

Applicant: United Technologies Corporation

Inventor： Pero, Edward B. ,  Aceto, Leonard D.

IPC: F02K1/70

CPC classification number: F02K1/70 ,  F02K1/1223

Abstract: A nozzle (40) for use in a gas turbine engine (10) includes a nozzle door (54) having a first end (54a), a second end (54b) opposed from the first end (54a), and a pivot (56) between the first end (54a) and the second end (54b). A linkage (64) connects to the nozzle door (54) and to an actuator (42). The actuator (42) is selectively operative to move the linkage (64) to in turn move the nozzle door (54) about the pivot (56) between a plurality of positions, such as a stowed position, an intermediate position, and a thrust reverse position, to influence a bypass airflow through a fan bypass passage (30).

Abstract translation: 一种用于燃气涡轮发动机（10）的喷嘴（40）包括具有第一端（54a）的喷嘴门（54a），与第一端（54a）相对的第二端（54b）和枢轴 ）在第一端（54a）和第二端（54b）之间。 连杆（64）连接到喷嘴门（54）和致动器（42）。 致动器42选择性地操作以使连杆机构64移动，从而使喷嘴门54围绕枢轴56在诸如收起位置，中间位置和推力之间的多个位置之间移动 反向位置，以影响通过风扇旁路通道（30）的旁路气流。

公开(公告)号：EP1820954A1

公开(公告)日：2007-08-22

申请号：EP07250521.7

申请日：2007-02-08

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Peters, Donald W.

IPC: F02K1/12

CPC classification number: F02K1/1223 ,  F02K1/12 ,  F02K1/805

Abstract: A nozzle system (10) includes a multitude of circumferentially distributed divergent seals (21) that circumscribe an engine centerline. Each divergent seal (21) includes an interface between a forward seal bridge bracket (80) and an aft seal bridge bracket (82) with a forward bridge support (76) and an aft bridge support (78) which provides axial and radial support for the divergent seals (21) between adjacent divergent flaps (18). A divergent-convergent seal joint structure (42) includes a horn (86) and a fork (88). By having the forward bridge bracket (80) retain the divergent seal (21) in the axial direction, there is no need for axial sliding of the divergent seal (21) relative to the divergent flap (18). The joint structure provides circumferential support as the axial and radial support are provided by the bridge-bracket interface. The joint interface permits the forward end section (48) of the divergent seal (21) and the forward end section of the divergent flap to include a radiused surface which provides a smooth interior interface between the convergent section and the divergent sections.

Abstract translation: 喷嘴系统（10）包括围绕发动机中心线的多个周向分布的发散密封件（21）。 每个发散密封件（21）包括前部密封桥架（80）和后部密封桥架（82）之间的界面，前桥和后桥支架（82）具有前桥支撑件（76）和后桥支撑件（78） 相邻发散片（18）之间的发散密封件（21）。 发散会聚密封接头结构（42）包括喇叭（86）和叉（88）。 通过使前桥支架（80）沿轴向保持发散密封件（21），不需要相对于发散片（18）的发散密封件（21）的轴向滑动。 当轴向和径向支撑由桥架支架接口提供时，接头结构提供周向支撑。 接合界面允许发散密封件（21）的前端部分（48）和发散片的前端部分包括在收敛部分和发散部分之间提供平滑的内部界面的圆角表面。

公开(公告)号：EP1767768A2

公开(公告)日：2007-03-28

申请号：EP06253846.7

申请日：2006-07-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Kehret, Debora F.

IPC: F02K1/12

CPC classification number: F02K1/1223 ,  F02K1/1292 ,  F02K1/38 ,  Y02T50/671

Abstract: A turbine engine nozzle assembly has an upstream flap assembly having a main flap (226) and a liner (228), a cooling passageway formed between the main flap (226) and liner (228). A downstream flap (26) is pivotally coupled to the upstream flap assembly for relative rotation about a hinge axis (H). The liner (228) has a trailing end (234) spaced upstream from a trailing end of the main flap (226) by at least 40% of a length (L F ) of the main flap (226).

Abstract translation: 涡轮发动机喷嘴组件具有上游翼片组件，其具有主瓣（226）和衬套（228），形成在主翼片（226）和衬套（228）之间的冷却通道。 下游翼片（26）枢转地联接到上游翼片组件，用于围绕铰链轴线（H）的相对旋转。 衬套（228）具有与主瓣（226）的尾端上游相距主瓣（226）的长度（L F）的至少40％的后端（234）。

公开(公告)号：EP1304472A1

公开(公告)日：2003-04-23

申请号：EP01500252.0

申请日：2001-10-19

Applicant: Industria de Turbo Propulsores S.A.

Inventor： Elorriaga Vicario, Javier ,  Gutierrez Ozamiz, Asier

IPC: F02K1/00 ,  F02K1/12 ,  F02K1/56 ,  F02K1/62

CPC classification number: F02K1/56 ,  F02K1/006 ,  F02K1/1207 ,  F02K1/1223 ,  F02K1/62 ,  Y02T50/671

Abstract: A gas turbine engine exhaust nozzle mechanism, including two side walls (7), two convergent flaps (10, 46), an upper and a lower reverse flow duct (15, 58) and at least one actuator mechanism. The convergent flaps (10, 46) are arranged to be displaceable between a forward thrust operation mode position and a reverse thrust operation mode position by the at least one convergent flap actuator (19), whereby the convergent flaps are arranged to block the reverse flow ducts (15, 58) when the convergent flaps are in the forward thrust operation mode position. Each of the convergent flaps (10, 46) is provided with a pair of front sliding guides (16, 50), each front sliding guide being housed in a respective first cam track (34, 54) in a respective side wall (7). Further, each of the convergent flaps (10, 46) is provided with a pair of rear sliding guides (17, 52), each rear sliding guide being housed in a respective second cam track (33, 55) in a respective side wall (7).

Abstract translation: 一种燃气涡轮发动机排气喷嘴机构，包括两个侧壁（7），两个会聚翼片（10,46），上部和下部反向流动管道（15,58）和至少一个致动器机构。 会聚翼片（10,46）被布置成由所述至少一个会聚舌片致动器（19）在正推力操作模式位置和反向推力操作模式位置之间移动，由此所述会聚翼片被布置成阻挡所述反向流动 当收敛翼片处于向前推力操作模式位置时，管道（15,58）。 每个收敛翼片（10,46）设置有一对前部滑动导向件（16,50），每个前部滑动导轨容纳在相应的侧壁（7）中的相应的第一凸轮轨道（34,54）中， 。 此外，每个收敛翼片（10,46）设置有一对后滑动导轨（17,52），每个后滑动引导件容纳在相应的侧壁中的相应的第二凸轮轨道（33,55）中 7）。

公开(公告)号：EP1052395A1

公开(公告)日：2000-11-15

申请号：EP99500079.1

申请日：1999-05-13

Applicant: Industria de Turbo Propulsores S.A.

Inventor： Elorriaga Vicario, Javier

IPC: F02K1/12 ,  F02K1/15 ,  F02K1/00

CPC classification number: F02K1/15 ,  F02K1/008 ,  F02K1/1223 ,  F05D2250/323 ,  F05D2250/324

Abstract: The invention consists of a nozzle structure (2), on which a synchronising ring (1) is allowed to rotate and to move in the axial direction. Angled lever arms (3) with pivoting capability (4) on the nozzle structure (2), are connected on one side to the synchronising ring (1) and on the other to compression struts (8), joined to the divergent petals (10). The rotation of the synchronising ring (1) around the nozzle structure (2) is converted by the angled lever arms (3) in a predominant axial displacement of one side of the compression struts (8), resulting in the opening or closure of the divergent petals (10).

Abstract translation: 本发明由一个喷嘴结构（2）组成，允许同步环（1）旋转并沿轴向移动。 在喷嘴结构（2）上具有枢转能力（4）的有角度的杠杆臂（3）在一侧连接到同步环（1），另一侧连接到压缩支柱（8），其连接到发散花瓣（10 ）。 喷嘴结构（2）周围的同步环（1）的旋转由成角度的杠杆臂（3）以压缩支柱（8）的一侧的主要轴向位移转换，导致打开或关闭 发瓣（10）。

公开(公告)号：EP0851110A2

公开(公告)日：1998-07-01

申请号：EP97500118.1

申请日：1997-07-04

Applicant: SENER, INGENIERIA Y SISTEMAS, S.A.

Inventor： Aldecoa-Otalora Garate, Kepa M. ,  Rivacoba, Urruela, José

IPC: F02K1/00

CPC classification number: F02K1/008 ,  F02K1/1223

Abstract: Improvements in Patent No. 9,401,114, filed on May 20, 1994, covering improvement in axisymmetric nozzles of variable geometry and orientation of the flow which are intended for gas turbine engines. The nozzle comprises control means for adjusting the throat area A 8 and vectoring the push, which means are formed by three rings concentric to the longitudinal axis (14) of the engine, one inside (8), one intermediate (7), and one outside (6), and by a plurality of linear actuators (9); the outer ring (6) including two ring segments (6a, 6b) biarticulated to each other, which limits the ability to swing to a single plane and, therefore, can vector the thrust only in the plane of pitch of the airplane.
Use: On engines of twin-jet airplanes.

Abstract translation: 1994年5月20日提交的专利号9,401,114的改进，涵盖旨在用于燃气涡轮发动机的可变几何形状和取向的轴对称喷嘴的改进。 喷嘴包括用于调节喉部区域A8并且对推动进行向心的控制装置，该装置由与发动机的纵向轴线（14）同心的三个环形成，一个内部（8），一个中间件（7）和一个外部 （6）和多个线性致动器（9）; 所述外环（6）包括彼此重合的两个环形段（6a，6b），这限制了摆动到单个平面的能力，并且因此仅能够在飞机的俯仰平面中对推力进行矢量。 用途：双喷气发动机。