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    Variable area nozzle assembly and method for operating same
    1.
    发明授权
    Variable area nozzle assembly and method for operating same 有权

    公开(公告)号：US11867136B2

    公开(公告)日：2024-01-09

    申请号：US17554874

    申请日：2021-12-17

    Applicant: Rohr, Inc.

    Inventor： Timothy Gormley

    IPC: F02K1/12 ,  F02K1/36 ,  F02K1/62

    CPC classification number: F02K1/1215 ,  F02K1/36 ,  F02K1/62 ,  F05D2240/128 ,  F05D2260/50 ,  F05D2260/601

    Abstract: A variable area nozzle assembly for a gas turbine engine includes a fixed structure including a first fixed ring and a second fixed ring. The second fixed ring is spaced axially aft from the first fixed ring to define a first portion of an ejector passage therebetween. A nozzle defines an inner radial exhaust flow path surface. The nozzle includes a forward ejector door and an aft ejector door. The forward ejector door and the aft ejector door define a first surface portion of the inner radial exhaust flow path surface. Each of the forward ejector door and the aft ejector door are pivotable between respective closed positions and respective open positions. A translating ejector sleeve is mounted within the fixed structure and configured to axially translate within the fixed structure between a first axial position and a second axial position.

    Propelling nozzle
    3.
    发明授权
    Propelling nozzle 失效
    螺旋喷嘴

    公开(公告)号：US5186390A

    公开(公告)日：1993-02-16

    申请号：US721641

    申请日：1991-09-19

    Applicant: Heinrich Enderle ,  Jorg Heyse ,  Helmut-Arnd Geidel

    Inventor： Heinrich Enderle ,  Jorg Heyse ,  Helmut-Arnd Geidel

    IPC: F02K1/12

    CPC classification number: F02K1/1223 ,  F02K1/1215 ,  F02K1/1269

    Abstract: A propelling nozzle has upper and lower primary and secondary flaps which are disposed opposite one another at a mutual distance and which are sealingly movably guided between lateral wall portions of a four-cornered nozzle housing. The primary flaps are arranged pivotally about a fixed axis of rotation on the nozzle housing. The secondary flaps, in each case upstream of levers non-rotatably connected with the primary flaps, are pivotally linked to pivots situated on the side facing away from the nozzle flow. The secondary flaps change into the primary flaps with a surface section which is bent concentrically with respect to the pivots. The primary and secondary flaps are arranged in a four-cornered nozzle housing which is itself closed in. In each case the secondary flaps are arranged on the nozzle housing in an axially movable and angularly adjustable manner at the downstream end. The levers are formed on interior sections which are bent away from the primary flaps in a toggle-lever-type manner. At the rearward ends of the levers, pivots are located. The levers have cutouts which are concentric with respect to the pivots. The surface sections of the secondary flaps can be moved into the cutouts. The upper and the lower primary and secondary flaps can be swivelled by means of their respective separate adjusting system. Each adjusting system is arranged between an upper or a lower wall portion of the nozzle housing and the flaps and, in the process, acts upon a primary or a secondary flap.

    Abstract translation: PCT No.PCT / DE90 / 00020 Sec。 371日期1991年9月19日 102（e）1991年9月19日PCT PCT 1990年1月16日PCT公布。 出版物WO90 / 08254 日期：1990年7月26日。推进喷嘴具有彼此相对设置的彼此相对设置并且在四角喷嘴壳体的侧壁部分之间被密封地可移动地引导的上部和下部主要和次要折翼。 主翼片围绕喷嘴壳体上的固定旋转轴线枢转布置。 次级翼片（在每种情况下都不与主翼片不可旋转地连接的杆的上游）枢转地连接到位于远离喷嘴流动的一侧的枢轴。 次级翼片变成主翼片，其中相对于枢轴同心弯曲的表面部分。 主瓣和副翼被布置在四角喷嘴壳体中，其四周封闭。在每种情况下，次级翼片在下游端以可轴向移动和角度可调节的方式布置在喷嘴壳体上。 杠杆形成在以肘杆式方式从主瓣折回的内部部分上。 在杠杆的后端，枢轴位于。 杆具有相对于枢轴同心的切口。 次级襟翼的表面部分可以移动到切口中。 上，下主瓣可以通过各自的单独的调节系统进行旋转。 每个调节系统布置在喷嘴壳体的上壁部分或下壁部分与翼片之间，并且在该过程中，其作用在主瓣或副皮瓣上。

    Gas turbine engine nozzle apparatus including a nozzle flap slot seal
    6.
    发明授权
    Gas turbine engine nozzle apparatus including a nozzle flap slot seal 失效
    燃气涡轮发动机喷嘴装置，包括喷嘴盖槽口密封件

    公开(公告)号：US4073441A

    公开(公告)日：1978-02-14

    申请号：US729594

    申请日：1976-10-04

    Applicant: Dudley O. Nash ,  Thomas S. Clayton

    Inventor： Dudley O. Nash ,  Thomas S. Clayton

    IPC: F02K1/10 ,  F02K1/12 ,  B64C15/06

    CPC classification number: F02K1/1215

    Abstract: Apparatus for modulating the area of a gas turbine engine nozzle which provides for positive sealing between overlapping articulated flaps when the overlapped flap is axially slotted to receive a portion of the overlapping flap. An arcuate seal is attached to the overlapping flap by means of a floating connection, the overlapping flap dragging the seal therewith in the axial direction. A seat is mounted on either side of the slot to slidingly receive a pair of shoulders laterally extending from the seal. A portion of the seal is received within the slot and is so contoured as to partially define the nozzle flow path. A sleeve captures and supports the seal shoulders during their axial travel.

    Abstract translation: 用于调节燃气涡轮发动机喷嘴的区域的装置，当重叠的翼片轴向地开槽以接收重叠翼片的一部分时，该区域提供重叠的铰接翼片之间的正密封。 弓形密封件通过浮动连接附接到重叠翼片，重叠的翼片沿着轴向方向将其密封件拖动。 一个座位安装在槽的任一侧，以滑动地接收从密封件侧向延伸的一对肩部。 密封件的一部分被容纳在槽内，并且具有如此轮廓以局部地限定喷嘴流动路径。 套筒在其轴向移动期间捕获并支撑密封肩。

    Propelling nozzle for a hypersonic jet plane
    9.
    发明授权
    Propelling nozzle for a hypersonic jet plane 失效
    喷气喷嘴用于高性能喷气飞机

    公开(公告)号：US5094070A

    公开(公告)日：1992-03-10

    申请号：US505044

    申请日：1990-04-05

    Applicant: Heinrich Enderle

    Inventor： Heinrich Enderle

    IPC: B64D27/02 ,  F02K1/12 ,  F02K1/60 ,  F02K1/62 ,  F02K7/16

    CPC classification number: F02K7/16 ,  F02K1/1215 ,  F02K1/1223 ,  F02K1/60

    Abstract: A propelling nozzle for a hypersonic jet plane having movable upper and lower primary and secondary flaps assigned to the gas turbojet engine as well as to the ramjet engine, both engines being arranged axially above one another, their outlet ducts being separated by means of a partition extending in the downstream direction to the narrowest cross-section of the propelling nozzle. The nozzle flaps can place themselves against the end edge of the partition on both sides in a manner advantageous with respect to the flow in the transition area from the primary flaps to the secondary flaps. As a result, each of the two outlet ducts can advantageously, either alternatively or simultaneously, be closed or opened, while, at the same time, a narrow cross-section and a divergence of the propelling nozzle can be adjusted which are optimal for the respective flying Mach number.

    Abstract translation: 用于超音速喷射平面的推进喷嘴，其具有分配给气体涡轮喷气发动机以及冲压喷气发动机的可移动的上部和下部主要和次级翼片，两个发动机彼此轴向地布置，它们的出口管道通过分隔件 沿下游方向延伸到推进喷嘴的最窄横截面。 喷嘴襟翼可以以相对于从主襟翼到次襟翼的过渡区域中的流动有利的方式将自身置于两侧的隔板的端边缘上。 结果，两个出口管道中的每一个可以有选择性地或同时地被闭合或打开，同时，可以调节窄的横截面和推进喷嘴的发散，这对于 各自飞行马赫数。

    Actuating means for a thrust vectoring gas turbine engine exhaust nozzle
    10.
    发明授权
    Actuating means for a thrust vectoring gas turbine engine exhaust nozzle 失效
    用于推力矢量燃气涡轮发动机排气喷嘴的致动装置

    公开(公告)号：US3979067A

    公开(公告)日：1976-09-07

    申请号：US572341

    申请日：1975-04-28

    Applicant: Dudley O. Nash

    Inventor： Dudley O. Nash

    IPC: F02K1/06 ,  B64C15/02 ,  B64D33/00 ,  F02K1/00 ,  F02K1/11 ,  F02K1/12 ,  F02K1/78 ,  F02K1/20

    CPC classification number: F02K1/006 ,  F02K1/1215 ,  Y02T50/671

    Abstract: A thrust vectoring gas turbine exhaust nozzle is provided with cooperating variable internal coverging-diverging flaps to provide nozzle flow path area control. A vertical take-off and landing capability is obtained by deployment of a rotating bonnet-type deflector which diverts the exhaust stream downward around one side of the exhaust nozzle. Actuating means are provided to rotate the nozzle throat simultaneously with deflector rotation to produce efficient turning of the exhaust stream in the lift mode. The actuation means also simultaneously controls the nozzle flow path area and external exhaust expansion in the cruise mode.

    Abstract translation: 推力矢量式燃气轮机排气喷嘴配有可配合的可变内部覆盖 - 发散翼片，以提供喷嘴流路面积控制。 通过部署旋转阀盖型偏转器获得垂直起降能力，该导流器将废气流向下排放到排气喷嘴的一侧。 提供致动装置以同时具有偏转器旋转来旋转喷嘴喉部，以在提升模式下有效地转动废气流。 致动装置还同时控制巡航模式下的喷嘴流路面积和外部排气膨胀。

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