公开(公告)号：US11142327B2

公开(公告)日：2021-10-12

申请号：US16658936

申请日：2019-10-21

Applicant: Airbus Operations SAS

Inventor： Christophe Labarthe ,  Jean Geliot

IPC: B64D29/08 ,  B64D29/06 ,  B64D29/02 ,  B64D27/26

Abstract: A turbomachine assembly comprising a nacelle having an air inlet and comprising a structure. A forward hood is fixed to the structure and extends backwards from the air inlet. An articulated hood is arranged in the upper part of the nacelle and at the rear of the forward hood and comprises a front edge arranged at the front of the articulated hood. A rear edge is arranged at the rear of the articulated hood. A joint is disposed at the front edge between the articulated hood and the structure and ensures a displacement of the articulated hood between a closed position and an open position. A locking system is arranged at the rear edge, and is mobile between a locked position and an unlocked position, where in the closed position, the front edge is under the forward hood.

公开(公告)号：US10934009B2

公开(公告)日：2021-03-02

申请号：US16180129

申请日：2018-11-05

Applicant: Airbus Operations SAS

Inventor： Stéphane Combes ,  Jean Geliot ,  Thomas Deforet ,  Adeline Soulie ,  Benoit Orteu

IPC: B64D27/26

Abstract: An engine attachment system comprising an engine pylon with a top wall, a bottom wall and two lateral walls, and a front engine attachment with a beam which bears two connecting rods for fixing the engine. The engine attachment system also comprises an intermediate piece with a bottom wall and four lateral walls, wherein the beam is fixed against an outer face of the bottom wall, wherein the intermediate piece is fitted at a front-end face of the engine pylon in such a way that an inner face of the bottom wall comes against the front-end face of the engine pylon, and in such a way that the lateral walls of the intermediate piece are superposed with the walls of the engine pylon. In such an engine attachment system, the front engine attachment is thus located on the front-end face of the engine pylon, allowing a space saving.

公开(公告)号：US10882630B2

公开(公告)日：2021-01-05

申请号：US16138242

申请日：2018-09-21

Applicant: Airbus Operations SAS

Inventor： Stéphane Combes ,  Jean Geliot ,  Thomas Deforet ,  Adeline Soulie ,  Benoit Orteu

IPC: B64D29/08 ,  B64C7/02 ,  F01D25/24

Abstract: A dual-flow jet engine comprising a fixed structure, a central core, and a cowl comprising a fixed part and a mobile cowl mounted to be rotationally mobile on the fixed structure via hinges with swan neck fitting. The fixed part has a first edge and the mobile cowl has a second edge, in which, when the mobile cowl is in a closed position, the second edge extends against the first edge. For each hinge with swan neck fitting, the fixed part is hollowed at the first edge, so as to delimit a recess opposite the swan neck fitting and allow the passage of the swan neck fitting when the mobile cowl switches from the closed position to the open position. The recess for each hinge with swan neck fitting allows for a reduction of the dimensions of the swan neck during the movement of the mobile cowl.

公开(公告)号：US10647441B2

公开(公告)日：2020-05-12

申请号：US16192950

申请日：2018-11-16

Applicant: Airbus Operations SAS

Inventor： Stéphane Combes ,  Jean Geliot ,  Thomas Deforet ,  Adeline Soulie ,  Benoit Orteu

IPC: F16M13/00 ,  B64D27/26 ,  F02C7/20

Abstract: A rear engine attachment for an engine of an aircraft which comprises a pylon having a bottom face, the rear engine attachment comprising a first fitting configured to be fixed against the bottom face and having a wall, a second fitting configured to be secured to a structural casing of the engine, two front links and two rear links, which are fixed by one and the same main link point to the wall and by two link points on either side of the second fitting. Such a motorization assembly allows for a reduction of the bulk, in particular at the rear engine attachment, which helps in improving the overall performance of the motorization assembly.