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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：US20220333495A1
公开(公告)日：2022-10-20
申请号：US17753045
申请日：2020-08-26
摘要： The invention relates to a bypass turbomachine (2) for an aircraft, comprising a gas generator (5) and a ducted fan (4) comprising variable pitch blades (18) configured to take a reverse thrust position driving a reverse flow (24) of air within a secondary duct (16), the gas generator (5) being connected to a fan casing (3) by a stator blade assembly (40) that passes through the secondary duct, first openings (28) for letting in air from the reverse flow being located on an outer casing (17) at least partially internally delimiting the outer duct, and second openings (29) for letting said air out being located on an inner casing (14) at least partially externally delimiting an inner duct (12). The first openings are located within a plane that is perpendicular to a longitudinal axis (C) of the turbomachine and passes substantially through the middle of the blade assembly.
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3.发明申请公开(公告)号：US20210239047A1
公开(公告)日：2021-08-05
申请号：US17238602
申请日：2021-04-23
申请人： Safran Nacelles
发明人： Patrick BOILEAU
摘要： A nacelle for use in an aircraft having a turbojet engine (the turbojet engine including a fan casing and a suspension pylon) includes a D-shaped structure downstream section embedding a thrust reverser device. The D-shaped structure downstream section includes a movable cascades vane. The D-shaped structure downstream section also includes two D-shaped half-structures each having an outer half-cowl movable in translation along a longitudinal axis, a connector between the cascades vane and the outer half-cowl, a twelve o'clock half-bifurcation, an inner half-structure defining an inner portion of the annular flow path, and a twelve o'clock half-beam mounted on the twelve o'clock half-bifurcation articulated on the pylon. The nacelle further includes an axial retention device of the downstream section of the nacelle, relative to the turbojet engine, configured to provide a connection defining an axial retention between the twelve o'clock half-beam and a fixed element of the fan casing.
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公开(公告)号：US20210088001A1
公开(公告)日：2021-03-25
申请号：US16407438
申请日：2019-05-09
申请人： ROHR, INC.
摘要： A thrust reverser for a nacelle may comprise a composite track beam and a composite lug. The composite lug may be inserted through a through-hole in the composite track beam. Continuous fibers in the composite lug may provide strength in the in-plane direction.
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公开(公告)号：US10830176B2
公开(公告)日：2020-11-10
申请号：US14836712
申请日：2015-08-26
申请人： Rohr, Inc.
IPC分类号： B29C64/118 , B29L31/30 , F02K1/56 , B33Y80/00 , F02K1/70 , B33Y10/00 , B29K101/12 , B29K105/08
摘要： Manufacturing processes is provided for forming a thrust reverser cascade an aircraft propulsion system. The thrust reverser cascade may include an array of vanes connected to and extending laterally between longitudinally extending first and second strongback rails. In one of the processes, the forming of the thrust reverser cascade includes additive manufacturing the first strongback rail and/or at least one of the vanes. This first strongback rail may include a length of fiber which extends more than eighty-five percent of a longitudinal length of the first strongback rail.
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公开(公告)号：US10161356B2
公开(公告)日：2018-12-25
申请号：US14293605
申请日：2014-06-02
摘要： A turbofan engine having a turbine engine, a nacelle surrounding a portion of the turbine engine, and a thrust reverser. The thrust reverser comprises a movable control surface movable to and from a reversing position and a thrust reverser actuation system having at least one actuator operably coupled to the movable control surface to move the movable control surface into and out of the reversing position. A guide comprising a rail and a bogie having at least one rotatable bearing surface coupled to the rail for relative translational movement between the rail and bogie connects the turbine engine to the movable control surface such that operation of the at least one actuator moves the movable control surface by translation movement between the rail and the bogie.
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公开(公告)号：US09784216B2
公开(公告)日：2017-10-10
申请号：US14939638
申请日：2015-11-12
申请人： Rohr, Inc.
发明人： Michael Ray Aten , Sara Crawford
CPC分类号： F02K1/82 , B64D29/02 , B64D33/04 , F02K1/54 , F02K1/566 , F02K1/72 , F05B2220/33 , F05D2220/36 , Y02T70/56
摘要： A nacelle is configured to be coupled to an underside of a wing and forms a clearance space between the nacelle and a leading edge slat of the wing. A portion of an outlet cowling moves longitudinally aft when a reverse thrust configuration is activated and the leading edge slat is deployed toward the nacelle. The outlet cowling also includes another portion located adjacent to the leading edge slat that does not move when the reverse thrust configuration is activated and thus maintains its clearance space from the leading edge slat.
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8.发明授权Method of fabricating a bonded cascade assembly for an aircraft thrust reverser 有权制造用于飞机推力反向器的粘合级联组件的方法公开(公告)号：US09587582B1
公开(公告)日：2017-03-07
申请号：US14305444
申请日：2014-06-16
IPC分类号： F02K1/56
CPC分类号： F02K1/72 , F05D2230/23 , F05D2230/60 , F05D2240/129 , F05D2300/603 , Y02T50/672
摘要： A method of fabricating a bonded cascade assembly of a thrust reverser for an aircraft nacelle. The method may include inserting individual turning vanes between spaced apart elongated stiffeners at an aft end thereof and sliding the turning vanes toward a front frame piece attached to or integrally formed with forward ends of the elongated stiffeners. The elongated stiffeners may have inner and outer flanges for trapping and limiting radial movement of the turning vanes. The method may further include bonding the turning vanes to the structural frame with a structural adhesive and attaching a closeout cap to the aft ends of each of the elongated stiffeners.
摘要翻译： 一种用于制造用于飞机机舱的推力反向器的接合级联组件的方法。 该方法可以包括将单独的转动叶片插入在其后端处的间隔开的细长加强件之间，并将转向叶片朝向附接到细长加强件的前端或与其整体形成的前框架件滑动。 细长的加强件可以具有用于捕获和限制转动叶片的径向运动的内和外凸缘。 该方法还可以包括用结构粘合剂将转向叶片结合到结构框架上，并将闭合帽附接到每个细长加强筋的后端。
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公开(公告)号：US20160369743A1
公开(公告)日：2016-12-22
申请号：US14746380
申请日：2015-06-22
申请人： Rohr, Inc.
发明人： Johann S. Schrell
IPC分类号： F02K1/56
摘要： An assembly is provided for an aircraft propulsion system. This assembly includes a thrust reverser cascade, a fan ramp fairing and a blocker door. The thrust reverser cascade extends along an axial centerline from a forward cascade end to an aft cascade end. The fan ramp fairing is disposed at the forward cascade end. The fan ramp fairing is configured with a fairing surface that provides a forward boundary for bypass air flowing into the thrust reverser cascade during a first mode of operation. The blocker door is configured to completely axially overlap the fairing surface during a second mode of operation.
摘要翻译： 为飞机推进系统提供组件。 该组件包括推力反向器级联，风扇斜坡整流罩和阻塞门。 推力反向器级联沿着轴向中心线从前级联端延伸到后级联端。 风扇斜坡整流罩设置在前级联端。 风扇斜坡整流罩配置有整流表面，其在第一操作模式期间提供流入推力反向器级联的旁路空气的前方边界。 阻挡门构造成在第二操作模式期间完全轴向地重叠整流罩表面。
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公开(公告)号：US20160258386A1
公开(公告)日：2016-09-08
申请号：US15066606
申请日：2016-03-10
申请人： Woodward HRT, Inc.
发明人： Galen Ko , Yehuda M. Shapira
CPC分类号： F02K1/763 , F02K1/563 , F02K1/566 , F02K1/766 , F02K3/06 , F05D2220/36 , F05D2260/406
摘要： A thrust reverser actuation system for a jet engine having a turbine engine surrounded by a nacelle to define an annular air flow path between the turbine engine and the nacelle, with a thrust reverser having a movable element to reverse the direction of at least a portion of the air flow along the air flow path, where the thrust reverser actuation system includes a hydraulic actuator configured to be operably coupled to the movable element, and a remote actuator that controls the inhibit function of the hydraulic system.
摘要翻译： 一种用于喷气发动机的推力反向器致动系统，其具有被机舱包围以在涡轮发动机和机舱之间限定环形空气流动路径的涡轮发动机，其中推力反向器具有可移动元件以使至少一部分 沿着空气流动路径的空气流，其中推力反向器致动系统包括构造成可操作地联接到可移动元件的液压致动器以及控制液压系统的禁止功能的远程致动器。
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