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    COMPACT HEAT EXCHANGE DEVICE INCORPORATED INTO AN AIRCRAFT PYLON
    4.
    发明申请
    COMPACT HEAT EXCHANGE DEVICE INCORPORATED INTO AN AIRCRAFT PYLON 审中-公开

    公开(公告)号：US20190085770A1

    公开(公告)日：2019-03-21

    申请号：US16129499

    申请日：2018-09-12

    Applicant: Airbus Operations (S.A.S.)

    Inventor： Stéphane Combes ,  Jean Geliot ,  Thomas Deforet ,  Adeline Soulie ,  Benoit Orteu

    IPC: F02C7/18 ,  B64D33/08 ,  B64D27/12 ,  F02C7/20

    Abstract: A heat exchange device to be positioned in an aircraft pylon and including a heat exchanger and an obturator to adopt a closed state where it prevents flow of air from flowing through the heat exchanger, and more- or less-permissive states where it allows flow of air to flow with a higher or lower flow rate. The obturator includes slats each including a pivot axis, the pivot axes of the various slats being mutually parallel and intersecting the direction of the flow of air, the slats being simultaneously mobile in rotation about their pivot axis between a closed position in which the slats are contiguous, which corresponds to the closed state of the obturator, and an open position in which the slats are spread apart, which corresponds to the permissive state of the obturator.

    Aircraft engine fastener
    6.
    发明授权
    Aircraft engine fastener 有权
    飞机发动机紧固件

    公开(公告)号：US09527599B2

    公开(公告)日：2016-12-27

    申请号：US14600921

    申请日：2015-01-20

    Applicant: Airbus Operations (S.A.S.)

    Inventor： Thomas Deforet ,  Arnold Wysocki

    IPC: B64D27/26

    CPC classification number: B64D27/26 ,  B64D2027/266 ,  B64D2027/268

    Abstract: An engine fastener includes a fixing assembly having a connection element provided with a shaft and holding two pins, which are configured to participate in the implementation of a fail-safe function, the fixing assembly including a shear pin surrounding the shaft of the connection element with a clearance , the shear pin being arranged between the two pins and being adjusted so as to be in contact with two joined fitting parts at a junction zone therebetween, the shaft of the connection element also being mounted with clearances relative to the two pins and the two fitting parts.

    Abstract translation: 发动机紧固件包括具有连接元件的固定组件，该连接元件设置有轴并且保持两个销，所述两个销构造成参与故障保护功能的实现，所述固定组件包括围绕连接元件的轴的剪切销， 间隙，剪切销布置在两个销之间并且被调节成与它们之间的接合部分处的两个连接的配合部分接触，连接元件的轴也相对于两个销安装有间隙，并且 两个配件。

    Compact heat exchange device incorporated into an aircraft pylon
    8.
    发明授权
    Compact heat exchange device incorporated into an aircraft pylon 有权

    公开(公告)号：US10746100B2

    公开(公告)日：2020-08-18

    申请号：US16129499

    申请日：2018-09-12

    Applicant: Airbus Operations (S.A.S.)

    Inventor： Stéphane Combes ,  Jean Geliot ,  Thomas Deforet ,  Adeline Soulie ,  Benoit Orteu

    IPC: F01N5/02 ,  F02C7/18 ,  B64D13/08 ,  B64D27/12 ,  B64D33/08 ,  F02C7/20

    Abstract: A heat exchange device to be positioned in an aircraft pylon and including a heat exchanger and an obturator to adopt a closed state where it prevents flow of air from flowing through the heat exchanger, and more- or less-permissive states where it allows flow of air to flow with a higher or lower flow rate. The obturator includes slats each including a pivot axis, the pivot axes of the various slats being mutually parallel and intersecting the direction of the flow of air, the slats being simultaneously mobile in rotation about their pivot axis between a closed position in which the slats are contiguous, which corresponds to the closed state of the obturator, and an open position in which the slats are spread apart, which corresponds to the permissive state of the obturator.

    Rear attachment of an aircraft engine comprising break detectors
    10.
    发明授权
    Rear attachment of an aircraft engine comprising break detectors 有权

    公开(公告)号：US10759542B2

    公开(公告)日：2020-09-01

    申请号：US15801278

    申请日：2017-11-01

    Applicant: Airbus Operations (S.A.S.)

    Inventor： Jean Pierre Couffignal ,  Jérôme Cassagne ,  Didier Rovatti ,  Thomas Deforet ,  Benoit Orteu ,  Michael Belin ,  Miren Egana-Abarrategui

    IPC: B64D27/26 ,  B64D45/00

    Abstract: A rear engine attachment includes a beam attached to the reactor strut, a rudder mounted by a pivot connection on the beam about a main rotational axis, and two thrust rods each exhibiting a first end attached to the rudder and a second end attached to a front section of an engine, the two thrust rods and the rudder attached to the beam together defining a primary thrust path between the engine and the reactor strut to bear the engine thrust. For each thrust rod, the rear engine attachment exhibits a waiting fail-safe system activated in the event of a failure of the primary thrust path. The rear engine attachment includes, for each thrust rod, a break detector integral with the rudder which is provided to come into contact with the beam in the event of a failure of the primary thrust path. The attachment allows a quick inspection to be made to determine whether there has been a failure of the primary thrust path.

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