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公开(公告)号：US11834189B2
公开(公告)日：2023-12-05
申请号：US17301239
申请日：2021-03-30
发明人： Donald Freund , Derek Muzychka
摘要： An exhaust nozzle assembly includes, but is not limited to, a nozzle body configured to be fluidly coupled with an engine and to receive a jet produced by the engine. An outer cover covers the nozzle body. A movable component is disposed and configured to have an effect on either the jet or an exhaust plume when the movable component moves. A linkage is coupled to the movable component and adapted for coupling to an actuator. The linkage transmits the force to the moveable component from the actuator. There is a gap between an inner surface of the outer cover and an outer surface of the nozzle body. The linkage is smaller than the actuator. The gap is smaller than a smallest dimension of the actuator and larger than the linkage. The linkage is partially disposed within the gap, and the exhaust nozzle assembly is free of the actuator.
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公开(公告)号：US09127623B2
公开(公告)日：2015-09-08
申请号：US14271626
申请日：2014-05-07
申请人： AIRCELLE
发明人： Vincent Peyron
CPC分类号： F02K1/763 , F02K1/32 , F02K1/54 , F02K1/56 , F02K1/70 , F02K1/72 , F05D2260/901 , F05D2270/66 , Y02T50/671
摘要： A thrust reverser device for a turbojet engine nacelle includes a cowl mounted translating between a closing position and an opening position in which the cowl opens a passage in the nacelle and uncovers deflecting cascades. The cowl is associated with a blocking flap pivotally mounted on the cowl between a retracted position and a pivoted blocking position in which the blocking flap closes partially an air flow path of the nacelle. The blocking flap is equipped with a driving mechanism including an assembly forming a lever pivotally mounted on the cowl and articulated at each of ends of the lever, by means of driving links, respectively on the blocking flap and on a fixed structure of the thrust reverser device. In particular, the assembly and the driving links are articulated in an articulation plane substantially perpendicular to the blocking flap and substantially radial to the thrust reverser device.
摘要翻译： 用于涡轮喷气发动机机舱的推力反向装置包括在关闭位置和打开位置之间平移的整流罩，其中整流罩在机舱中打开通道并且露出偏转级联。 整流罩与在缩回位置和枢转阻断位置之间枢转地安装在整流罩上的阻挡盖相关联，其中阻挡片部分地封闭机舱的空气流动路径。 挡板装有一个驱动机构，该驱动机构包括一个组件，该组件形成一个可枢转地安装在整流罩上的杠杆，并分别通过驱动连杆分别在挡板上和推力反向器的固定结构上铰接在杠杆的每个端部 设备。 特别地，组件和驱动连杆在基本上垂直于阻挡挡板的关节平面中铰接并且基本上径向铰接到推力反向器装置。
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公开(公告)号：US20150056070A1
公开(公告)日：2015-02-26
申请号：US13975038
申请日：2013-08-23
申请人： ROHR, INC.
发明人： ANTHONY LACKO
CPC分类号： F02K1/70 , F02K1/54 , F02K1/56 , F02K1/566 , F02K1/58 , F02K1/64 , F02K1/68 , F02K1/72 , F02K1/766
摘要： A multi-surface blocker door system for a thrust reverser of an aircraft is provided. The system may comprise one or more first blocker doors coupled to the inner fixed structure. The first blocker doors may be configured to obstruct a fan duct area adjacent the engine. The system may also comprise one or more second blocker doors coupled to a translating sleeve. The second blocker doors may be configured to obstruct a fan duct area adjacent to an inlet of the nacelle.
摘要翻译： 提供了一种用于飞机的推力反向器的多表面阻挡门系统。 该系统可以包括联接到内部固定结构的一个或多个第一阻止门。 第一阻塞门可以被配置成阻塞与发动机相邻的风扇管道区域。 系统还可以包括联接到平移套筒的一个或多个第二阻塞门。 第二阻塞门可以被配置成阻塞与机舱的入口相邻的风扇管道区域。
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公开(公告)号：US20150041059A1
公开(公告)日：2015-02-12
申请号：US14056695
申请日：2013-10-17
申请人： Rohr, Inc.
发明人： Timothy Olson , Jay Cobia , Thomas Sommer
CPC分类号： B21D53/92 , B23K1/0008 , B23K1/0018 , B32B37/0038 , B32B37/12 , F02K1/56 , F02K1/70 , F02K1/827 , F05D2250/283 , Y02T50/672 , Y10T29/4957 , Y10T156/10
摘要： A method is provided for providing, e.g. manufacturing, a thrust reverser inner fixed structure. The method includes (a) providing an acoustic inner barrel that includes a first honeycomb core and an annular inner skin radially inward of the first honeycomb core; (b) providing a bifurcation panel that includes a second honeycomb core; and (c) arranging a corner fitting between and attaching the corner fitting to the acoustic inner barrel and the bifurcation panel.
摘要翻译： 提供了一种方法， 制造，推力反向器内固定结构。 该方法包括（a）提供包括第一蜂窝芯和第一蜂窝芯径向向内的环形内皮的声音内筒; （b）提供包括第二蜂窝芯的分叉板; 以及（c）在所述声学内筒和所述分叉面板之间布置角配件并将所述角配件附接到所述声内筒和所述分叉面板。
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公开(公告)号：US3025667A
公开(公告)日：1962-03-20
申请号：US67325257
申请日：1957-07-22
申请人： BOEING CO
发明人： MOOREHEAD JAMES R
CPC分类号： F02K1/40 , F02K1/56 , Y02T50/671
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公开(公告)号：US3002343A
公开(公告)日：1961-10-03
申请号：US61902256
申请日：1956-10-29
申请人： AEROJET GENERAL CO
发明人： JOHN BAIRD
IPC分类号： F02K1/56
CPC分类号： F02K1/56
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公开(公告)号：US2997845A
公开(公告)日：1961-08-29
申请号：US72258058
申请日：1958-03-19
申请人： ROLLS ROYCE
发明人： GEORGE OULIANOFF
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公开(公告)号：US2944392A
公开(公告)日：1960-07-12
申请号：US57488456
申请日：1956-03-29
申请人： UNITED AIRCRAFT CORP
发明人： TYLER JOHN M
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10.发明授权Jet deflector for a jet propelled aircraft comprising a flexible canopy 失效一种用于喷气式飞机飞行器的喷射导流器，包括一个灵活的天篷
公开(公告)号：US2936582A
公开(公告)日：1960-05-17
申请号：US51467555
申请日：1955-06-10
IPC分类号： F02K1/56
CPC分类号： F02K1/56 , Y02T50/671
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