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    Assembly of a pylon with an engine of an aircraft
    1.
    发明授权
    Assembly of a pylon with an engine of an aircraft 有权

    公开(公告)号：US12054272B2

    公开(公告)日：2024-08-06

    申请号：US17964083

    申请日：2022-10-12

    申请人： Airbus Operations SAS

    发明人： Franck Rumiel ,  Thomas Robiglio ,  Paolo Messina

    IPC分类号： B64D27/40

    CPC分类号： B64D27/40 ,  B64D27/402 ,  B64D27/404

    摘要： An assembly of a pylon and of an engine with a rear engine attachment having two fittings, wherein each one has a shoe fastened to a lower spar of the pylon, two transverse arms, one front and one rear, which are as one with the shoe and offset such that the front transverse arm, respectively rear transverse arm, of one fitting bears in planar fashion against the front transverse arm, respectively rear transverse arm, of the other fitting, wherein each transverse arm is pierced with a bore, wherein the two front transverse arms and the two rear transverse arms are spaced apart parallel to the longitudinal direction and thus form a female clevis, and wherein the assembly also has a lower rod mounted articulated in the female clevis and on the engine. With such an assembly, the number of components is reduced.

    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

    申请人： General Electric Company

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

    IPC分类号： B64D27/40 ,  F02K3/06

    CPC分类号： B64D27/40 ,  F02K3/06 ,  F02C7/20

    摘要： 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

    申请人： Airbus Operations SAS

    发明人： Michael Berjot ,  Thomas Robiglio

    IPC分类号： B64D27/40 ,  F02C7/20

    CPC分类号： B64D27/40 ,  F02C7/20

    摘要： 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.