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    THRUST REVERSER ASSEMBLY FOR A TURBOJET ENGINE
    2.
    发明公开
    THRUST REVERSER ASSEMBLY FOR A TURBOJET ENGINE 审中-公开

    公开(公告)号：US20240254946A1

    公开(公告)日：2024-08-01

    申请号：US18565461

    申请日：2022-05-30

    Applicant: SAFRAN NACELLES

    Inventor： Pierre Charles CARUEL

    IPC: F02K1/76 ,  F02K1/72

    CPC classification number: F02K1/763 ,  F02K1/72 ,  F02K1/766 ,  F05D2240/11

    Abstract: The invention relates to a thrust reverser assembly for a turbojet engine, comprising a stationary structure having a main axis; a shroud, movable and capable of translational movement along the main axis between an attached position in which the shroud is attached to the stationary structure, and a spaced position in which the shroud is spaced from the stationary structure; at least one latch capable of holding the stationary structure and the shroud in the attached position; at least one actuator mounted between the stationary structure and the shroud and configured to move the shroud along the main axis between the attached position and the spaced position; and a seal configured to provide a seal between the stationary structure and the shroud in the attached position, wherein the seal has a tapered cross section.

    NACELLE FOR AN AIRCRAFT PROPULSION UNIT COMPRISING AN ACCESS SPACE CLOSED BY A TANGENTIALLY CLAMPED COWL
    4.
    发明申请
    NACELLE FOR AN AIRCRAFT PROPULSION UNIT COMPRISING AN ACCESS SPACE CLOSED BY A TANGENTIALLY CLAMPED COWL 有权

    公开(公告)号：US20250002167A1

    公开(公告)日：2025-01-02

    申请号：US18689195

    申请日：2022-09-12

    Applicant: SAFRAN NACELLES

    Inventor： Pierre Charles CARUEL

    IPC: B64D29/06 ,  B64D29/08

    Abstract: A nacelle for an aircraft propulsion unit includes an air intake cowl, and an intermediate section including fixed and removable hoods defining an access space between front ends of the hoods and an outer rear end of the air intake cowl. The intermediate section includes an annular row of mutually spaced connecting parts which rigidly connect the outer rear end of the air intake cowl to the front ends of the hoods so as to transmit longitudinal forces, and an intermediate cowl extending between the air intake cowl and the hoods, around the connecting parts, thereby closing the access space and creating aerodynamic continuity with the air intake cowl and the hoods. The intermediate cowl is formed from at least one strip which is held in place by tangential clamping of the circumferential ends of the strip.

    THRUST REVERSER COMPRISING PRIMARY LATCHES OFFSET WITH RESPECT TO A PLANE OF SYMMETRY OF THE MOVABLE HOOD
    5.
    发明申请
    THRUST REVERSER COMPRISING PRIMARY LATCHES OFFSET WITH RESPECT TO A PLANE OF SYMMETRY OF THE MOVABLE HOOD 有权

    公开(公告)号：US20220307446A1

    公开(公告)日：2022-09-29

    申请号：US17640112

    申请日：2020-09-02

    Applicant: SAFRAN NACELLES

    Inventor： Pierre Charles CARUEL ,  Fabien CHARLIAC ,  Fabien BRAVIN ,  Loïc CHAPELAIN

    IPC: F02K1/76

    Abstract: A thrust reverser for an aircraft propulsion assembly, this reverser including an outer structure movable between a closed position and an open position of two primary latches configured to lock the movable outer structure in the closed position. The movable outer structure includes an output end that is oblique with respect to the longitudinal central axis so as to orient the thrust laterally. In order to compensate the tilting moment of the movable outer structure, which results from this lateral orientation of the thrust, the primary latches are offset with respect to a median longitudinal plane passing through the longitudinal central axis of the reverser.

    THRUST REVERSER FOR TURBOJET ENGINE
    6.
    发明公开
    THRUST REVERSER FOR TURBOJET ENGINE 审中-公开

    公开(公告)号：US20240209812A1

    公开(公告)日：2024-06-27

    申请号：US17907743

    申请日：2021-03-31

    Applicant: SAFRAN NACELLES

    Inventor： Pierre Charles CARUEL ,  Loïc CHAPELAIN

    IPC: F02K1/56

    CPC classification number: F02K1/566

    Abstract: This summary relates to a thrust reverser (20) for a turbojet engine mounted on an engine nacelle pylon (40), comprising a fixed part (29), a movable part (39), coaxial and mounted in translation with respect to the fixed part (29) and sealingly inserted against the fixed part (29) by blocking an air outlet passage in a closed state whereas the air outlet passage is freed up in the extended state, and a single actuating device (38) including a beam (31), a slider (30), and a driving device, configured to drive the movable part (39) in translation with respect to the fixed part (29), wherein the beam (31) comprises a stop (32) taking the form of a protuberance protruding on a radially outer surface (31a) of the beam (31) and configured to have a clearance (j) with respect to said engine nacelle pylon (40).

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