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    SOUND ATTENUATION PANEL FOR AN AIRCRAFT
    2.
    发明申请
    SOUND ATTENUATION PANEL FOR AN AIRCRAFT 审中-公开

    公开(公告)号：US20190161157A1

    公开(公告)日：2019-05-30

    申请号：US16201035

    申请日：2018-11-27

    Applicant: AIRBUS OPERATIONS SAS

    Inventor： Florian RAVISE ,  Wolfgang BROCHARD

    IPC: B64C1/40 ,  G10K11/168

    Abstract: An acoustic panel (1) includes a plate (2) made of an acoustic absorbing material (3), as well as a resistive skin (4) and a backing skin (6) arranged respectively on both sides of the plate (2), the acoustic panel (1) including acoustic elements (8) able to carry out an acoustic absorption, each of them being arranged in a housing (7) provided in the plate (2) with an opening (9) in front of the resistive skin (4). The combination of the plate (2) and the acoustic elements (8) allows to combine the sound attenuation properties of these two types of elements and to increase the frequency range of sounds that can be attenuated by the acoustic panel (1), without increasing the dimension.

    AFT ENGINE PYLON FAIRING OF AN AIRCRAFT WITH MULTILAYER HEAT SHIELD
    5.
    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.

    ENGINE ASSEMBLY FOR AN AIRCRAFT COMPRISING A FRONT ENGINE ATTACHMENT WHICH FACILITATES ITS ASSEMBLY
    6.
    发明申请
    ENGINE ASSEMBLY FOR AN AIRCRAFT COMPRISING A FRONT ENGINE ATTACHMENT WHICH FACILITATES ITS ASSEMBLY 审中-公开

    公开(公告)号：US20180186462A1

    公开(公告)日：2018-07-05

    申请号：US15850115

    申请日：2017-12-21

    Applicant: Airbus Operations SAS

    Inventor： Wolfgang BROCHARD

    IPC: B64D27/26 ,  F02C7/20

    Abstract: For fitting of a front engine attachment of an engine assembly for an aircraft, a shearing pin is oriented in a longitudinal direction and is integral with a front closure rib of the strut housing and projects forward, a main attachment body is arranged axially opposite the intermediate casing hub, at the rear of the latter, the main attachment body having an orifice for accommodation of the shearing pin, an arrangement for securing the main attachment body on the engine, and an arrangement for axial retention of the main attachment body relative to the rib, the axial retention arrangement comprising first screws, the heads of which cooperate with the rib, as well as barrel nuts which cooperate with the screws, and are accommodated in the main attachment body.

    ASSEMBLY FOR A NACELLE OF AN AIRCRAFT ENGINE, SAID ASSEMBLY COMPRISING A FIXED COWL AND A COWL MOUNTED SO AS TO BE ABLE TO MOVE ON THE FIXED COWL
    8.
    发明申请
    ASSEMBLY FOR A NACELLE OF AN AIRCRAFT ENGINE, SAID ASSEMBLY COMPRISING A FIXED COWL AND A COWL MOUNTED SO AS TO BE ABLE TO MOVE ON THE FIXED COWL 有权

    公开(公告)号：US20230040055A1

    公开(公告)日：2023-02-09

    申请号：US17878360

    申请日：2022-08-01

    Applicant: Airbus Operations SAS

    Inventor： Umberto GASTALDI ,  Wolfgang BROCHARD ,  Olivier PAUTIS

    IPC: B64D29/06

    Abstract: An assembly for a nacelle, which includes a fixed cowl, a movable cowl that is movable between a closed position and an open position, and including an upper edge and a lower edge and, between the two edges, a reinforcing rib. The fixed cowl includes, an upper reinforcing rib and a lower reinforcing rib, a hinge including a fixed part attached to the upper reinforcing rib of the fixed cowl, a movable part attached to the reinforcing rib of the movable cowl, and at least two locks, each one including a first part secured to the lower reinforcing rib and a second part secured to the reinforcing rib of the movable cowl. An assembly of this kind serves to provide access to the inside of the nacelle while ensuring that the cowls remain sufficiently rigid.

    TURBOFAN COMPRISING A SET OF ROTATABLE BLADES FOR BLOCKING OFF THE BYPASS FLOW DUCT
    9.
    发明申请
    TURBOFAN COMPRISING A SET OF ROTATABLE BLADES FOR BLOCKING OFF THE BYPASS FLOW DUCT 审中-公开

    公开(公告)号：US20200325848A1

    公开(公告)日：2020-10-15

    申请号：US16845224

    申请日：2020-04-10

    Applicant: Airbus Operations SAS

    Inventor： Pascal GARDES ,  Wolfgang BROCHARD

    IPC: F02K1/09 ,  F02C7/057 ,  F02C7/042

    Abstract: A turbofan having a nacelle including a slider translationally mobile to open a window between a duct and the exterior, a plurality of blades, each rotationally mobile on the slider, and a maneuvering system moving each blade and comprising for each blade, a shaft rotationally mobile on the slider and onto which the blade is fixed, an arm having a first end fixed to the shaft, an arc coaxial with the longitudinal axis, mounted rotationally mobile on the slider about the longitudinal axis, a rectilinear rod fixed by its base to the arc, the rectilinear rod inserted into a through-bore of a stock, wherein the stock is mounted translationally free relative to the rectilinear rod, and the stock is mounted rotationally free on the arm at its second end about a rocking axis parallel to the rotational axis, and an actuation system producing arc rotation in two opposite directions.

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