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    ENGINE PYLON FOR COUPLING A JET ENGINE TO A WING OF AN AIRCRAFT
    3.
    发明公开
    ENGINE PYLON FOR COUPLING A JET ENGINE TO A WING OF AN AIRCRAFT 审中-公开

    公开(公告)号：US20230159179A1

    公开(公告)日：2023-05-25

    申请号：US17988862

    申请日：2022-11-17

    Applicant: Airbus Operations SAS

    Inventor： Olivier PAUTIS ,  Jonathan BLANC

    IPC: B64D27/26 ,  F01D25/28

    CPC classification number: B64D27/26 ,  F01D25/28 ,  B64D2027/262 ,  B64D27/16

    Abstract: An engine pylon for an aircraft and comprising an inverted U-shaped upper spar with two lateral walls, a U-shaped lower spar with two lateral walls, where the free ends of the lateral walls of the spars are adjacent, an arrangement to the free end of a lateral wall of one spar to the free end of the lateral wall of the other spar, and ribs between the spars where each has a top end fixed to the lateral walls of the upper spar and a bottom end fixed to the lower spar. Such an engine pylon thus offers a reduced number of component parts and a single row of fixings per side, enabling a saving in weight and in assembly time.

    AIRCRAFT HAVING AN ENGINE PYLON WITH A MOBILE COWL
    4.
    发明公开
    AIRCRAFT HAVING AN ENGINE PYLON WITH A MOBILE COWL 审中-公开

    公开(公告)号：US20240199218A1

    公开(公告)日：2024-06-20

    申请号：US18541513

    申请日：2023-12-15

    Applicant: Airbus Operations SAS

    Inventor： Olivier PAUTIS ,  Paolo MESSINA ,  Jonathan BLANC ,  Thomas ROBIGLIO ,  Thomas FIRMIGNAC

    IPC: B64D29/06 ,  B64D29/02

    CPC classification number: B64D29/06 ,  B64D29/02

    Abstract: An aircraft having a fixed structure, an engine pylon, and a cowling system, a slider bearing a rear cowl and able to move in translation from an advanced position to a retracted position, a displacement system having, on either side of a median plane of the engine pylon, a guide as one with the fixed structure, a sliding element as one with the slider and sliding along each guide disposed on the same side, and a support as one with the fixed structure and having a blade parallel to the translation direction and on which a surface parallel to the translation direction of the slider rests. The presence of the mobile cowl ensures, inter alia, easy access to the inside of the engine pylon and to the systems that are housed therein.

    SHACKLE FOR FASTENING AN AIRCRAFT ENGINE COMPRISING A PAIR OF ENCAPSULATED ANTI-FRICTION COATINGS, AND AIRCRAFT COMPRISING SUCH A SHACKLE
    5.
    发明申请
    SHACKLE FOR FASTENING AN AIRCRAFT ENGINE COMPRISING A PAIR OF ENCAPSULATED ANTI-FRICTION COATINGS, AND AIRCRAFT COMPRISING SUCH A SHACKLE 有权

    公开(公告)号：US20230002067A1

    公开(公告)日：2023-01-05

    申请号：US17851407

    申请日：2022-06-28

    Applicant: Airbus Operations SAS

    Inventor： Cédric POUPON ,  Olivier PAUTIS ,  Jonathan BLANC

    IPC: B64D27/26 ,  F16C11/06

    Abstract: A shackle for fastening an aircraft engine including a ball joint with a pin including a ring including a first bore and a sleeve assembled in the first bore and having a second bore configured to receive the pin and the diameter of which progressively increases to have a flared inner surface at each of its ends, the fastening shackle being arranged such that a spherical outer surface of the ring bears an anti-friction coating produced on a region extending beyond the contact region with the body of the shackle, this first region being bordered by rims forming a projection around the coating, and/or the second bore bears an anti-friction coating on a region extending beyond its contact region with the pin, this region being bordered by rims forming a projection around this anti-friction coating, at the ends of the flared inner surface.

    AIRCRAFT ENGINE PYLON HAVING A MOBILE COWL
    6.
    发明申请
    AIRCRAFT ENGINE PYLON HAVING A MOBILE COWL 有权

    公开(公告)号：US20220297845A1

    公开(公告)日：2022-09-22

    申请号：US17694747

    申请日：2022-03-15

    Applicant: Airbus Operations SAS

    Inventor： Olivier PAUTIS ,  Jonathan BLANC

    IPC: B64D29/02 ,  B64D29/08 ,  B64D27/26

    Abstract: An engine pylon has a primary structure fastened between an engine and an aircraft wing and a cowling system having a front set of fixed cowls, a rear cowl, a displacement system having a first structure as one with the rear cowl and having a first slide mechanism, and a second structure fastened to a fixed structure of the wing and having second slide mechanism. The slide mechanisms cooperate so as to realize a sliding connection and to move the rear cowl in translation from an advanced position to a retracted position. An immobilizing system locks the rear cowl in the advanced position.

    AFT ENGINE PYLON FAIRING OF AN AIRCRAFT WITH MULTILAYER HEAT SHIELD
    7.
    发明申请
    AFT ENGINE PYLON FAIRING OF AN AIRCRAFT WITH MULTILAYER HEAT SHIELD 有权

    公开(公告)号：US20210163143A1

    公开(公告)日：2021-06-03

    申请号：US17109021

    申请日：2020-12-01

    Applicant: Airbus Operations SAS

    Inventor： Florent MERCAT ,  Jonathan BLANC ,  Wolfgang BROCHARD

    IPC: B64D29/00 ,  B64D27/26 ,  F02C7/24 ,  B32B3/26 ,  B32B5/18 ,  B32B5/24 ,  B32B3/12 ,  B32B9/00 ,  B32B9/04 ,  B32B15/04

    Abstract: An aft engine pylon fairing including a framework including lateral panels, transverse reinforcing ribs, and a heat shield linked to the framework. The heat shield has a multilayer structure comprising an insulating core configured both to constitute a thermal barrier and to damp acoustic waves, an outer skin configured to guide an aerodynamic flow and contribute to the acoustic damping, and an inner skin configured to ensure the mechanical strength of the shield. The shield multilayer structure allows the aft engine pylon fairing to contribute to the attenuation of the noise nuisances of the engine, and, also, to improve the thermal insulation conferred by the shield by allowing the use, for the insulating core of the shield, of materials having a better thermal resistance but a low mechanical rigidity, the mechanical strength being essentially ensured by the inner skin of the multilayer structure.

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