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    ENGINE BACKBONE BENDING REDUCTION
    3.
    发明公开
    ENGINE BACKBONE BENDING REDUCTION 审中-公开

    公开(公告)号：US20240150027A1

    公开(公告)日：2024-05-09

    申请号：US18450071

    申请日：2023-08-15

    Applicant: General Electric Company

    Inventor： Jonathan E. Coleman ,  Timothy L. Schelfaut ,  Anthony M. Metz ,  Thomas P. Joseph ,  Mahesh Khandeparker ,  Kudum Shinde ,  Donald L. Gardner

    IPC: B64D27/40 ,  F02K3/06

    CPC classification number: B64D27/40 ,  F02K3/06 ,  F02C7/20

    Abstract: Methods, apparatus, systems and articles of manufacture are disclosed. An apparatus for mounting a gas turbine engine to a pylon includes: a thrust link coupled to the gas turbine engine and an aft mount, the gas turbine engine coupled to the pylon via a forward mount and the aft mount, a bending restraint having a first end and a second end, the bending restraint including an actuator positioned at the first end to apply a force to a fan section of the gas turbine engine, a first joint positioned at the first end of the bending restraint, the first joint coupled to the first end of the bending restraint and the fan section, and a second joint positioned at the second end of the bending restraint, the second joint coupled to the second end of the bending restraint.

    Front engine attachment system for an aircraft engine, which has a compact structure
    4.
    发明授权
    Front engine attachment system for an aircraft engine, which has a compact structure 有权

    公开(公告)号：US11975857B2

    公开(公告)日：2024-05-07

    申请号：US17899673

    申请日：2022-08-31

    Applicant: Airbus Operations SAS

    Inventor： Michael Berjot ,  Thomas Robiglio

    IPC: B64D27/40 ,  F02C7/20

    CPC classification number: B64D27/40 ,  F02C7/20

    Abstract: A front engine attachment system having an engine pylon having a frontal rib fastened against a front face, a front engine attachment having a beam fastened to the frontal rib, two rods articulated to the beam respectively via two connection points and one connection point, and a front casing of an engine, wherein the first rod is articulated to the front casing via a connection point and wherein the second rod is articulated to the front casing via a connection point, wherein each point of connection of a rod to the beam is positioned inside a volume that extends the front face of the engine pylon towards the front. Such a front engine attachment system has reduced bulk and therefore less drag.

    SUPPORT STRUCTURE FOR ATTACHING A GAS TURBINE ENGINE TO AN AIRCRAFT PYLON
    10.
    发明公开
    SUPPORT STRUCTURE FOR ATTACHING A GAS TURBINE ENGINE TO AN AIRCRAFT PYLON 审中-公开

    公开(公告)号：US20230182911A1

    公开(公告)日：2023-06-15

    申请号：US18061330

    申请日：2022-12-02

    Applicant: ROLLS-ROYCE plc

    Inventor： Richard G STRETTON

    IPC: B64D27/26 ,  B64D27/10 ,  B64D33/08 ,  F02C7/20

    CPC classification number: B64D27/26 ,  B64D27/10 ,  B64D33/08 ,  F02C7/20 ,  B64D2027/268 ,  F05D2220/323 ,  F05D2240/90

    Abstract: A gas turbine engine includes a support structure for attaching the engine to an aircraft pylon. The support structure includes: an engine-side interface member, a pylon-side interface member interfacing to the engine-side interface member, and a top V-shaped connection formation above the engine core and pair of side V-shaped connection formations on opposite lateral sides of the engine core, each V-shaped connection formation being formed by a pair of connection members meeting at a vertex, the vertex of the top V-shaped connection formation joining to the top of the engine-side interface member, the vertices of the side V-shaped connection formations respectively joining to the bottom ends of the engine-side interface member, and the connection members extending forwardly from their respective vertices to join to front fixation points at the core casing.

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