公开(公告)号：US5197694A

公开(公告)日：1993-03-30

申请号：US516015

申请日：1990-04-27

申请人： Dudley O. Nash ,  Donald F. Keck

发明人： Dudley O. Nash ,  Donald F. Keck

IPC分类号： B64C25/42 ,  B64D33/04

CPC分类号： B64D33/04 ,  B64C25/423

摘要： A thrust reverser assembly is disclosed for a wing mounted gas turbine engine exhaust nozzle having an outlet for discharging exhaust gases over a surface of the wing. The assembly in accordance with a preferred embodiment includes a deflector having forward and aft ends, and first and second sides joined together by a base. The deflector is positionable in a stowed position around the exhaust nozzle so that the aft end is aligned generally with the nozzle outlet for allowing substantially unobstructed discharge of exhaust gases therefrom, and in a deployed position for changing direction of exhaust gases for thrust reversal. A pair of bellcranks are positioned adjacent to respective ones of the deflector sides and actuators are povided for rotating the bellcranks for moving the deflector between the stowed and deployed positions. A pair of elongate tracks having rollers slidably positioned therein and being pivotally connected to the deflector are also provided for controlling the angular orienation of the deflector so that the deflector aft end is disposed against the wing surface and the base extends outwardly from the wing surface for deflecting exhaust gases upwardly and out the deflector forward end when the deflector is in the deployed position.

摘要翻译： 公开了一种用于机翼安装的燃气涡轮发动机排气喷嘴的推力反向器组件，其具有用于在机翼的表面上排放废气的出口。 根据优选实施例的组件包括具有前端和后端的偏转器，以及由底座连接在一起的第一和第二侧。 偏转器可定位在排气喷嘴周围的收纳位置，使得后端大体上与喷嘴出口对齐，用于允许基本上不受阻碍地从其排出废气，并且在用于改变排气反转方向的展开位置中用于推力反转。 一对曲拐与相应的偏转器侧相邻定位，致动器用于旋转曲拐，用于在收起位置和展开位置之间移动偏转器。 还提供一对具有可滑动地定位在其中并且可枢转地连接到偏转器的辊的细长轨道，用于控制偏转器的角度偏移，使得偏转器后端靠近机翼表面设置，并且基座从机翼表面向外延伸，以便 当偏转器处于展开位置时，将排气向上偏转并偏离偏转器前端。

公开(公告)号：US5307623A

公开(公告)日：1994-05-03

申请号：US129874

申请日：1993-09-29

申请人： Eugene J. Antuna ,  Donald F. Keck

发明人： Eugene J. Antuna ,  Donald F. Keck

IPC分类号： B64D27/18 ,  F02K3/02

CPC分类号： B64D27/18

摘要： An apparatus and method for the disassembly of an ultra high bypass turbine engine having an outer engine portion and an inner engine portion. A plurality of fan blades and acoustic panels are removed from the inner portion of the engine. The outer portion of the engine which includes a plurality of fan outlet guide vanes and fan casing are disconnected from the engine and axially removed. Certain outer portions of the engine including a hinged thrust reverser and hinged fan cowling may be coupled to an aircraft pylon and used interchangeably with replacement engines.

摘要翻译： 一种用于拆卸具有外发动机部分和内部发动机部分的超高旁路涡轮发动机的装置和方法。 多个风扇叶片和隔音板从发动机的内部部分移除。 包括多个风扇出口导向叶片和风扇壳体的发动机外部部分与发动机断开并被轴向移除。 发动机的包括铰接推力反向器和铰接风扇罩的发动机的某些外部部分可以联接到飞机塔架并且与替换发动机可互换使用。

公开(公告)号：US5222360A

公开(公告)日：1993-06-29

申请号：US785365

申请日：1991-10-30

申请人： Eugene J. Antuna ,  Donald F. Keck ,  Robert H. Roth ,  James W. Brantley ,  Thomas G. Wakeman ,  Jeffrey B. Fravel ,  Alan B. Corbeil ,  William J. Strock

发明人： Eugene J. Antuna ,  Donald F. Keck ,  Robert H. Roth ,  James W. Brantley ,  Thomas G. Wakeman ,  Jeffrey B. Fravel ,  Alan B. Corbeil ,  William J. Strock

IPC分类号： B64D27/18 ,  B64D27/26 ,  F02C7/20

CPC分类号： B64D27/18 ,  B64D27/26 ,  F02C7/20 ,  Y02T50/672

摘要： A gas turbine engine has a core frame separable from a vane frame for removably attaching the vane frame to a core structure through a mid ring. The mid ring includes an annular forward panel and an annular aft panel, each of which has a radially outer flange and a radially inner flange. The inner flanges are welded to the core frame and the outer flanges are bolted to the vane frame. A plurality of circumferentially spaced stiffeners extend between the forward and aft panels, with each of the stiffeners including a pair of stringers extending diagonally across the stiffeners. Panels may be incorporated with the stringers between the triangular shaped areas adjacent the forward and aft panels of the stiffener. The bolted connection between the mid ring and the vane frame includes a plurality of tongue and groove joints formed in the flanges of the mid ring and vane frame. The tongue and groove joints provide additional radial support for the core engine within the vane frame. Preferably, the tongue and groove joints are formed with angular sides so that conformance between the joints can be achieved by simply tightening the bolts attaching the joints. In one embodiment, the tongue and groove joints may only be used at preselected circumferential positions with the remainder of the flange connections using overlapping lap joints.

摘要翻译： 燃气涡轮发动机具有与叶片框架分离的芯框架，用于通过中环将叶片框架可拆卸地附接到芯结构。 中环包括环形前板和环形后板，每个板具有径向外凸缘和径向内凸缘。 内部凸缘焊接到芯框架，外部凸缘螺栓连接到叶片框架。 多个周向隔开的加强件在前板和后板之间延伸，其中每个加强件包括一对沿着加强件对角延伸的纵梁。 面板可以与邻近加强筋的前板和后板的三角形形状区域之间的桁条结合。 中间环和叶片框架之间的螺栓连接包括形成在中环和叶片框架的凸缘中的多个榫舌和凹槽接头。 舌和槽接头为叶片框架内的核心发动机提供额外的径向支撑。 优选地，舌和沟槽接头形成有角侧，使得可以通过简单地紧固附接接头的螺栓来实现接头之间的一致性。 在一个实施例中，舌和槽接头可以仅在预选的圆周位置处使用，其余的凸缘连接使用重叠搭接接头。