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    TURBOJET COMPRISING A THRUST REVERSER DRIVE MECHANISM
    3.
    发明申请
    TURBOJET COMPRISING A THRUST REVERSER DRIVE MECHANISM 审中-公开

    公开(公告)号：US20200256282A1

    公开(公告)日：2020-08-13

    申请号：US16736474

    申请日：2020-01-07

    Applicant: Airbus Operations SAS

    Inventor： Fabien MENOU ,  Laurent CAZEAUX ,  Benoit ORTEU

    IPC: F02K1/70 ,  F02K1/76

    Abstract: A turbojet comprising a nacelle with a fixed cowl, a fan duct and a thrust reverser comprising a cowl movable between a stowed and a deployed position where the movable cowl is remote from the fixed cowl, at least one blocking flap movable between the closed position and a fixed position where the flap at least partially blocks the fan duct, and also a drive mechanism for moving the movable cowl and the blocking flap. The drive mechanism comprises a roller slide comprising a rail and a roller rotatable in the rail, a connecting rod with a first end movable on the roller and a second end movable on the blocking flap. The rail comprises a bearing surface extending parallel to a turbojet longitudinal axis to support the connecting rod during movement of the movable cowl from the stowed position to an intermediate position between the stowed and deployed positions.

    AIRCRAFT TURBOFAN HAVING A COWL ARTICULATED IN ROTATION AND A SYSTEM FOR DEPLOYING SAID COWL
    4.
    发明申请
    AIRCRAFT TURBOFAN HAVING A COWL ARTICULATED IN ROTATION AND A SYSTEM FOR DEPLOYING SAID COWL 有权

    公开(公告)号：US20220106927A1

    公开(公告)日：2022-04-07

    申请号：US17488725

    申请日：2021-09-29

    Applicant: Airbus Operations SAS

    Inventor： Corentin VILHES ,  Simon VANDERBAUWEDE ,  Thierry GACHES ,  Laurent CAZEAUX ,  Pascal GARDES ,  Guillaume SEGUIN

    IPC: F02K7/08 ,  F04D29/52

    Abstract: A turbofan having a fixed structure, a fan, a fan casing surrounding the fan, an outer cowl disposed around the fan casing and mounted so as to be articulated on the fixed structure, and a deployment system that moves the outer cowl from a closed position to an open position. The deployment system has a guide rail fastened around the fan casing, a slider that is able to move along the guide rail and has a shoe. An activation system of the deployment system moves the slider and the shoe alternately in one direction or the other along the guide rail. One end of an arm of the deployment system is mounted to be articulated on the shoe and another end is mounted to be articulated on the outer cowl. Such a motorized deployment system makes it possible to save space and mass in the turbofan.

    LOW-FREQUENCY-SOUND-ABSORBING STRUCTURE FOR A PRIMARY NOZZLE OF A TURBOMACHINE OF AN AIRCRAFT
    5.
    发明申请
    LOW-FREQUENCY-SOUND-ABSORBING STRUCTURE FOR A PRIMARY NOZZLE OF A TURBOMACHINE OF AN AIRCRAFT 审中-公开

    公开(公告)号：US20200072161A1

    公开(公告)日：2020-03-05

    申请号：US16552079

    申请日：2019-08-27

    Applicant: Airbus Operations SAS

    Inventor： Eric BOUCHET ,  Laurent CAZEAUX ,  Thierry GACHES ,  Morad KASSEM ,  Claire MAFFRE

    IPC: F02K1/82 ,  F02C7/24

    Abstract: A structure which absorbs low-frequency sound comprising a perforated skin, a box having two lateral walls in the shape of a strip, that delimit between them an opening, and a bottom opposite the opening connecting the two lateral walls, the lateral walls becoming closer together with increasing distance from the opening to the bottom. The box is attached to the skin at the opening. Each lateral wall extends width-wise between the opening and the bottom. Each box has two tongues, each tongue being strip shaped, extending lengthwise over an entire box length, and width-wise between the opening and the bottom of the box. Each tongue has a first end attached along an edge of the opening and a second, free end which extends towards the bottom, becoming closer to the second end of the other tongue, where each tongue has an arcuate shape along its length.

    NACELLE OF A TURBOJET COMPRISING A BLOCKING DOOR AND A SYSTEM FOR DEPLOYMENT OF THE BLOCKING DOOR
    7.
    发明申请
    NACELLE OF A TURBOJET COMPRISING A BLOCKING DOOR AND A SYSTEM FOR DEPLOYMENT OF THE BLOCKING DOOR 审中-公开

    公开(公告)号：US20200263632A1

    公开(公告)日：2020-08-20

    申请号：US16791372

    申请日：2020-02-14

    Applicant: Airbus Operations SAS

    Inventor： Sreekanth GANAPATHI RAJU ,  Benoit ORTEU ,  Laurent CAZEAUX ,  Olivier DENOY

    IPC: F02K1/72 ,  F02K1/60

    Abstract: A nacelle comprising a fixed structure with a fixed cowling and a cowling movable in translation between closed and open positions, to open an opening between a duct and the exterior. A blocking door is rotatably movable on the movable cowling between a stowed position and a deployed position. A deployment system comprises an arm with a first end articulated on the blocking door and a second end that bears a stop, a slider fixed to the arm, a linear guide system is fixed on the fixed structure and guides the slide, and a cam. The stop is configured to lie against the cam when the movable cowling reaches an intermediate position from the closed position and to be guided by the cam to drive the rotation of the arm about the slider when the movable cowling moves from the intermediate position to an open position.

    INTERNAL FIXED STRUCTURE FOR AN AIRCRAFT NACELLE
    8.
    发明公开
    INTERNAL FIXED STRUCTURE FOR AN AIRCRAFT NACELLE 审中-公开

    公开(公告)号：US20240351697A1

    公开(公告)日：2024-10-24

    申请号：US18643483

    申请日：2024-04-23

    Applicant: Airbus Operations SAS

    Inventor： Laurent CAZEAUX ,  Laurent CALIMAN ,  Nicolas CHARTON

    IPC: B64D29/02

    CPC classification number: B64D29/02

    Abstract: An internal fixed structure for a nacelle, comprising end panels, an intermediate panel in the form of a half-cylinder between the end panels, splice plates between the intermediate panel and each end panel, wherein each splice plate is made up of a skin with an inner face fastened to the panels and at least one indentation protruding with respect to an outer face, and a pad fastened to each fastening surface of an indentation, wherein each pad of the upper splice plate bears against a surface of an engine pylon, and wherein each pad of the lower splice plate bears against a pad of a lower splice plate of another internal fixed structure.

    TURBOFAN ENGINE COMPRISING A SET OF ROTATABLE BLADES FOR BLOCKING OFF THE BYPASS FLOW DUCT
    10.
    发明申请
    TURBOFAN ENGINE COMPRISING A SET OF ROTATABLE BLADES FOR BLOCKING OFF THE BYPASS FLOW DUCT 有权

    公开(公告)号：US20220136459A1

    公开(公告)日：2022-05-05

    申请号：US17516251

    申请日：2021-11-01

    Applicant: Airbus Operations SAS

    Inventor： Fabien MENOU ,  Laurent CAZEAUX ,  Thierry GACHES

    IPC: F02K3/02

    Abstract: A turbofan engine having a duct for a bypass flow and blades. Each blade is mobile between a stowed position and a deployed position. Each blade includes a rigid core a second, free end, and a sheath into which the core and the second end slide. Each sheath includes a first part which surrounds at least one part of the core and the second end, and an aileron which extends beyond the core facing the first part of the adjacent blade. The sheath is made of a flexible material such that the bypass flow causes the sheath to come into contact with the first part of the adjacent blade. A turbofan engine of this kind makes it possible to create blades whose production costs are low but whose aerodynamic behavior is effective.

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