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.

公开(公告)号：US20190161198A1

公开(公告)日：2019-05-30

申请号：US16195971

申请日：2018-11-20

Applicant: Airbus Operations SAS

Inventor： Stéphane COMBES ,  Jean GELIOT ,  Thomas DEFORET ,  Adeline SOULIE ,  Benoit ORTEU

IPC: B64D27/26

Abstract: A swivel axis for an aircraft engine attachment, comprising a tubular main axis which has, at a first end, a head and, at a second end, a threaded portion onto which is screwed a first nut. A fail-safe axis is configured to be mounted to swivel inside the main axis. The fail-safe axis has, at a first end, a head and, at a second end, a threaded portion onto which is screwed a second nut. The fail-safe axis is linked by an axial link to the first nut. Since the fail-safe axis is linked to the first nut, it is necessarily inserted into the main axis when the first nut is screwed onto the main axis.

公开(公告)号：US20190152615A1

公开(公告)日：2019-05-23

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: B64D27/26

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.

公开(公告)号：US20180127105A1

公开(公告)日：2018-05-10

申请号：US15683976

申请日：2017-08-23

Applicant: Airbus Operations SAS

Inventor： Benoit ORTEU

IPC: B64D27/26 ,  F02C7/20

Abstract: A rear engine mount for a turbomachine of an aircraft comprising a pylon. The rear engine mount comprises a beam attached to the pylon, a first and a second lateral connecting rod having an abutment and attached between the beam and the turbomachine, a three-point, V-shaped central connecting rod, of which the vertex is attached to the turbomachine, and of which the ends of the arms are attached to the beam. The rear engine mount has a plane of symmetry passing through the center of the ball joint of the vertex. The beam has, for each abutment, a buffer, wherein each abutment comes to bear against the buffer in the event of failure of the central connecting rod.