公开(公告)号：US20200072128A1

公开(公告)日：2020-03-05

申请号：US16513990

申请日：2019-07-17

Applicant: Airbus Operations SAS

Inventor： Stéphane COMBES ,  Jean GELIOT

IPC: F02C7/20 ,  B64D27/10 ,  B64D29/06

Abstract: An aircraft turbine engine assembly including a nacelle structure with a strut attachment zone, a first cover forming an air intake lip, a hinged cover arranged on the nacelle upper portion, between the first cover and the attachment zone, a hinge system of the cover comprising, on either side of a mid-plane of the nacelle, a front rod and a rear rod that are one in front of the other. The two ends of each rod are co-planar, parallel to the mid-plane. A first end of each rod is hinged on the cover. A second end of each rod is hinged on the structure. A locking system is actuatable from the outside of the nacelle between a locked and an unlocked positon. The nacelle comprises at least one cylinder with a first end mounted hinged on the structure and the other end mounted hinged on the cover.

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：US20200207481A1

公开(公告)日：2020-07-02

申请号：US16615924

申请日：2017-12-12

Applicant: Airbus Operations SAS

Inventor： Stéphane COMBES ,  Adeline SOULIE ,  Olivier PAUTIS

IPC: B64D27/26

Abstract: A propulsion assembly for an aircraft, comprising a pylon to be secured below a wing of the aircraft and having a front face and a lower face, and a turbomachine comprising, from upstream to downstream in a direction of a flow of air passing through the turbomachine during operation, a fan and an engine driving the fan. The fan is faired by a fan casing and the engine is faired, from upstream to downstream, by an intermediate casing and an engine casing, the intermediate casing having a hub and an outer ring extending the fan casing, the ring being spaced apart radially from the hub and secured to the latter by arms extending in an air duct. The propulsion assembly comprises a front engine attachment secured between the pylon front face and the hub and a rear engine attachment secured between the pylon lower face and the engine casing.

公开(公告)号：US20190135445A1

公开(公告)日：2019-05-09

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：US20190106221A1

公开(公告)日：2019-04-11

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.