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    Aerodynamic element for an aircraft nacelle
    2.
    发明授权
    Aerodynamic element for an aircraft nacelle 有权
    飞机机舱的气动元件

    公开(公告)号：US08939713B2

    公开(公告)日：2015-01-27

    申请号：US13681219

    申请日：2012-11-19

    Applicant: Aircelle

    Inventor： Céline Blin ,  Guillaume Strub ,  Vincent Peyron

    IPC: F01D5/00 ,  F04D29/66 ,  F01D25/24 ,  B64D29/00 ,  B64D33/02

    CPC classification number: F01D25/24 ,  B64D29/00 ,  B64D33/02

    Abstract: An aerodynamic element for an aircraft nacelle is provided that includes a fixed shroud and an intake lip axially movable relative to the shroud. The aerodynamic element is flexible and has a substantially cylindrical general shape and defines an upstream portion attached to the inner wall of the intake lip of the nacelle, and a downstream portion bearing radially against an inner face of the shroud. The downstream portion of the element includes a ring shaped bead protruding towards an outside of the aerodynamic element and an end blade which, at rest, is tilted towards the outside of the aerodynamic element in a direction of its free end.

    Abstract translation: 提供了一种用于飞机机舱的空气动力学元件，其包括固定护罩和相对于护罩可轴向移动的进气口。 空气动力学元件是柔性的并且具有大致圆柱形的总体形状并且限定附接到机舱的进气口的内壁的上游部分和径向抵靠护罩的内表面的下游部分。 元件的下游部分包括朝向空气动力学元件的外侧突出的环形凸缘和在其自由端的方向上朝向空气动力学元件的外侧倾斜的端部叶片。

    Turbojet engine nacelle with downstream section
    3.
    发明授权
    Turbojet engine nacelle with downstream section 有权
    涡轮喷气发动机舱与下游段

    公开(公告)号：US09341083B2

    公开(公告)日：2016-05-17

    申请号：US14524099

    申请日：2014-10-27

    Applicant: AIRCELLE

    Inventor： Hazem Kioua ,  Vincent Peyron ,  Laurent Georges Valleroy

    IPC: B64D29/06 ,  F01D25/24 ,  F02K1/72 ,  B64D33/04

    CPC classification number: F01D25/24 ,  B64D29/06 ,  B64D33/04 ,  F02K1/72 ,  F05D2220/30

    Abstract: A turbofan engine nacelle has a downstream section which includes at least one front frame. The front frame is attached to a stationary portion of the nacelle, and the downstream section is provided with at least one rail or slide which extends in a longitudinal direction of the nacelle and is capable of engaging with at least one corresponding slide or rail of an attachment pylon of the turbofan engine. The front frame is connected to the rail or slide of the downstream section by means of at least one swiveled connecting rod.

    Abstract translation: 涡轮风扇发动机舱具有包括至少一个前框架的下游部分。 前框架连接到机舱的静止部分，并且下游部分设置有至少一个轨道或滑块，其沿着机舱的纵向方向延伸并且能够与至少一个相应的滑轨或轨道接合 涡扇发动机的附件塔。 前框架通过至少一个可旋转的连接杆连接到下游部分的导轨或滑块。

    Thrust reverser device
    4.
    发明授权
    Thrust reverser device 有权
    推力反向装置

    公开(公告)号：US09127623B2

    公开(公告)日：2015-09-08

    申请号：US14271626

    申请日：2014-05-07

    Applicant: AIRCELLE

    Inventor： Vincent Peyron

    IPC: F02K1/76 ,  F02K1/72 ,  F02K1/56 ,  F02K1/54 ,  F02K1/32 ,  F02K1/70

    CPC classification number: F02K1/763 ,  F02K1/32 ,  F02K1/54 ,  F02K1/56 ,  F02K1/70 ,  F02K1/72 ,  F05D2260/901 ,  F05D2270/66 ,  Y02T50/671

    Abstract: 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.

    Abstract translation: 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。

    Cascade thrust reverser for an aircraft turbojet engine
    5.
    发明授权
    Cascade thrust reverser for an aircraft turbojet engine 有权

    公开(公告)号：US09617955B2

    公开(公告)日：2017-04-11

    申请号：US14620543

    申请日：2015-02-12

    Applicant: AIRCELLE

    Inventor： Vincent Peyron ,  Laurent Georges Valleroy ,  Franck Depoortere

    IPC: F02K1/62 ,  F02K1/72 ,  F02K1/76

    CPC classification number: F02K1/625 ,  F02K1/72 ,  F02K1/763 ,  F02K1/766

    Abstract: The present disclosure relates to a cascade thrust reverser providing that when a sliding cowl and a flap are in a direct jet position, a hook is held in engagement with another hook and the flap is immobilized inside of a housing of the sliding cowl by a stem of a telescopic connecting rod subjected to pre-stress generated by a compressed spring located in the body of the connecting rod. When the sliding cowl starts to slide from the direct jet position toward the reverse jet position, the hooks disengage each other and the stem engages with an extension in the body of the connecting rod, so that the flap is rotated from the direct jet position toward the reverse jet position due to the tensile force exerted by the stem.

    DEVICE FOR CONNECTING A THRUST REVERSER FRONT FRAME TO A FAN CASING AND NACELLE INCORPORATING SUCH A DEVICE
    6.
    发明申请
    DEVICE FOR CONNECTING A THRUST REVERSER FRONT FRAME TO A FAN CASING AND NACELLE INCORPORATING SUCH A DEVICE 有权
    用于连接逆向前框架的风扇装置和装置的装置

    公开(公告)号：US20130227962A1

    公开(公告)日：2013-09-05

    申请号：US13860726

    申请日：2013-04-11

    Applicant: AIRCELLE

    Inventor： Serge Bunel ,  Vincent Peyron ,  Hazem Kioua ,  Jerome Lescure

    IPC: F01D25/28

    CPC classification number: F01D25/28 ,  F01D25/243 ,  F02K1/56 ,  F02K1/766 ,  F02K1/80 ,  F05B2240/911 ,  F05D2230/60 ,  F05D2250/411 ,  F05D2260/30 ,  F05D2260/50 ,  F16B2/14 ,  F16L23/036 ,  F16L37/101 ,  Y02T50/671

    Abstract: A device for connecting a thrust reverser front frame to a fan casing includes a crenulated flange secured to the front frame, an annular component to accept this flange secured to the fan casing, and a crenulated annulus of a shape that complements the flange and pivot-mounted on the annular component. The crenulated flange, the annular component and the crenulated annulus are designed in such a way that a rotation of the annulus with respect to the annular component has the effect of locking this flange against this annular component through the collaboration between the respective crenulations of the flange and of the annulus.

    Abstract translation: 用于将推力反向器前框架连接到风扇壳体的装置包括固定到前框架的螺旋形凸缘，用于接收固定到风扇壳体上的该凸缘的环形部件，以及与凸缘和枢轴连接部分互补的形状的圆环， 安装在环形部件上。 齿形凸缘，环形部件和棘轮环形空间被设计成使得环形件相对于环形部件的旋转具有通过凸缘的相应齿形部之间的协作将该凸缘锁定在该环形部件上的作用 和环带。

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