AIR INLET STRUCTURE FOR A TURBOJET ENGINE NACELLE OF LAMINAR TYPE
    1.
    发明申请
    AIR INLET STRUCTURE FOR A TURBOJET ENGINE NACELLE OF LAMINAR TYPE 有权
    涡轮发动机空气入口结构LAMINAR型涡轮发动机

    公开(公告)号:US20150007896A1

    公开(公告)日:2015-01-08

    申请号:US14496518

    申请日:2014-09-25

    Applicant: AIRCELLE

    Abstract: An air intake structure for a turbojet engine nacelle includes an inner panel to be attached to a fan casing, and an external panel capable of a translational movement in a longitudinal direction of the nacelle. The external panel incorporates a portion of an air inlet lip able to provide a junction between the inner panel and the external panel, and each of the air inlet lip portion and the inner panel is equipped, at least in the region of a joining end, with an acoustic attenuation structure. In particular, at least one of the joining ends is equipped with a radial buffer able to come into contact with a corresponding joining flange exhibited by the other joining end when the external panel is in a closed position.

    Abstract translation: 用于涡轮喷气发动机机舱的进气结构包括附接到风扇壳体的内板和能够在机舱的纵向方向上的平移运动的外板。 外部面板包括能够在内部面板和外部面板之间提供接合部的空气入口唇缘的一部分,并且至少在接合端的区域中配备每个空气入口唇部和内部面板, 具有声衰减结构。 特别地,当外部面板处于关闭位置时,连接端中的至少一个配备有径向缓冲器,该径向缓冲器能够与另一接合端所示的相应的接合凸缘接触。

    CELLULAR ACOUSTIC STRUCTURE FOR A TURBOJET ENGINE AND TURBOJET ENGINE INCORPORATING AT LEAST ONE SUCH STRUCTURE
    2.
    发明申请
    CELLULAR ACOUSTIC STRUCTURE FOR A TURBOJET ENGINE AND TURBOJET ENGINE INCORPORATING AT LEAST ONE SUCH STRUCTURE 有权
    涡轮发动机和涡轮发动机的细节声学结构至少一个这样的结构

    公开(公告)号:US20140341744A1

    公开(公告)日:2014-11-20

    申请号:US14322601

    申请日:2014-07-02

    Applicant: AIRCELLE

    Abstract: A cellular acoustic structure for a turbojet engine includes a closed wall. The closed wall includes at least two faces having acoustically transparent areas and acoustic reflective areas. The closed wall is filled with a plurality of cells, and the acoustic reflective areas are disposed within the closed wall so that an acoustic path of aerial sound vibrations travels through the acoustically transparent areas, penetrates inside the cells and reflects on the acoustic reflective areas. In particular, the acoustic path in some of the cells has a depth greater than a half of the thickness of the cellular acoustic structure.

    Abstract translation: 用于涡轮喷气发动机的蜂窝声学结构包括封闭壁。 闭合的壁包括具有声学透明区域和声反射区域的至少两个面。 封闭的墙壁上填充有多个单元,并且声反射区域设置在闭合的壁内,使得空中声音振动的声路径穿过声透明区域,穿透在单元内并在声反射区域上反射。 特别地,一些单元中的声学路径具有大于蜂窝声学结构的厚度的一半的深度。

    CONTROL DEVICE FOR A TURBOJET ENGINE THRUST REVERSER, BLOCKING THE REVERSER
    3.
    发明申请
    CONTROL DEVICE FOR A TURBOJET ENGINE THRUST REVERSER, BLOCKING THE REVERSER 有权
    涡轮发动机的控制装置扭转逆转器,阻塞逆变器

    公开(公告)号:US20160102633A1

    公开(公告)日:2016-04-14

    申请号:US14975326

    申请日:2015-12-18

    Applicant: AIRCELLE

    Abstract: A control device for a thrust reverser of a turbojet engine nacelle, which includes movable portions actuated by actuators, includes: a first blocking control acting on a motor-actuated system; and a second blocking control acting, mechanically, on the movable portions. The second blocking control may inhibit, when activated, a deployment of the movable portions. The control device further includes a device inhibiting disengagement of the first blocking control when a mechanical control is activated.

    Abstract translation: 用于涡轮喷气发动机机舱的推力反向器的控制装置,其包括由致动器致动的可动部分,包括:作用在电动机致动系统上的第一阻塞控制; 以及机械地作用在可动部分上的第二阻挡控制。 第二阻塞控制可以在被激活时抑制可移动部分的展开。 控制装置还包括当机械控制被激活时禁止第一阻塞控制分离的装置。

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