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.

公开(公告)号：US20180283280A1

公开(公告)日：2018-10-04

申请号：US15921870

申请日：2018-03-15

Applicant: Airbus Operations SAS

Inventor： Jérôme CASSAGNE ,  Jean GELIOT

IPC: F02C7/25 ,  B64D27/26 ,  B64D45/00 ,  F02C7/20

Abstract: A fire seals system positioned in a corner of a region of attachment between a rear engine mount and a pylon and comprising a metal shoe comprising a fitting comprising two first vanes forming an L fixed in the corner and a lower second vane between the lower edges of the two first vanes and an upper second vane between the upper edges of the two first vanes, and a flexible tongue having a fixed upstream end and a free downstream end in which an intermediate part of the tongue is arranged between the lower second vane and the upper second vane, and a longilinear seal attached to a thrust reverser cowl with one end of the longilinear seal bearing against the tongue. Such a fire seals system makes it possible to limit the spread of flames and to absorb movements of the nacelle.

公开(公告)号：US20240351704A1

公开(公告)日：2024-10-24

申请号：US18627739

申请日：2024-04-05

Applicant: Airbus Operations SAS

Inventor： Jérôme BADERSPACH ,  Jean GELIOT ,  Dimitri GARAY

IPC: B64D45/00 ,  A62C3/08

CPC classification number: B64D45/00 ,  A62C3/08 ,  B64D2045/009

Abstract: An assembly having a pylon with two side walls provided with apertures, a reservoir for extinguishing agent, a support which has two support elements, wherein each support element has an upwardly facing first bearing face to which the reservoir is fastened, a distal end, and a proximal end fastened by a first removable fastener, wherein the distal end is rotatable about a horizontal axis, and wherein each support element is movable between a use position, in which the first bearing face is horizontal, and a fitted position, in which the first bearing face is tilted downwards.

公开(公告)号：US20220411086A1

公开(公告)日：2022-12-29

申请号：US17849882

申请日：2022-06-27

Applicant: Airbus Operations SAS

Inventor： Jean GELIOT

IPC: B64D27/26 ,  B64D27/02

Abstract: An aircraft propulsion assembly including a front engine mount including a transverse beam which is connected to the engine via first and second convergent connection rods. This transverse beam includes an upper extension which is at least partially positioned opposite a front transverse reinforcement of the primary structure and which is connected thereto via at least one first connection element and right and left lateral extensions which are positioned at one side and another of the upper extension, each of them being connected via a least one second fixing element to a first wing of a right or left bracket, a second wing of the right or left bracket being connected via at least one third connection element to the primary structure.

公开(公告)号：US20210101694A1

公开(公告)日：2021-04-08

申请号：US16940747

申请日：2020-07-28

Applicant: Airbus Operations SAS

Inventor： Julien CAYSSIALS ,  Jean GELIOT ,  Adeline SOULIE

IPC: B64D37/32 ,  B64D37/02

Abstract: An assembly for an aircraft including a pylon having a lateral wall with a window passing through it, at least one reservoir, each reservoir being in the shape of an elongate ellipsoid with three semi-axes. The dimension of the reservoir along a first semi-axis differs from the dimension of the reservoir along at least one other semi-axis. The reservoir extends parallel to the semi-major axis, between a first end and a second end. The reservoir is equipped with a discharge head at the second end. The reservoir is equipped with a fastening arrangement disposed on the side of the second end and fastening the reservoir to the pylon. The reservoir is positioned through the window with the first end housed in the pylon and the second end outside the pylon.

公开(公告)号：US20200025088A1

公开(公告)日：2020-01-23

申请号：US16418555

申请日：2019-05-21

Applicant: Airbus Operations SAS

Inventor： Jean GELIOT

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

Abstract: A turbomachine assembly for an aircraft comprising a nacelle with a nacelle structure, cowls attached to the structure to create an aerodynamic surface, an articulated cowl, comprising four edges, in the upper portion of the nacelle, an articulation at a first edge of the articulated cowl attached between the articulated cowl and the nacelle structure allowing the articulated cowl to move between a closed and an open position, a locking system at a second edge of the articulated cowl, opposite the first edge. The locking system comprises a handle actuable from the exterior of the nacelle, between a first position and a second position, a locking device movable between a locking position and an unlocking position, and a transmission system that moves the locking device from the locking position to the unlocking position when the handle passes from the first position to the second position, and vice versa.

公开(公告)号：US20190284856A1

公开(公告)日：2019-09-19

申请号：US16293164

申请日：2019-03-05

Applicant: Airbus Operations SAS

Inventor： Jean GELIOT ,  Adeline SOULIE

IPC: E05D7/10 ,  B64D29/06 ,  B64C1/14 ,  B64D29/08

Abstract: A bypass turbojet engine comprising a fixed structure, a central core and a cowl comprising a fixed part and a mobile cowl mounted with the ability to rotate on the fixed structure between a closed position and an open position via hinges with gooseneck fitting. At least one hinge with gooseneck fitting comprises a gooseneck fitting having one end mounted in articulated manner on the mobile cowl and one end mounted in an articulated manner on the fixed structure, the bypass turbojet engine comprises anti-vibration means which are configured to exert pressure against the gooseneck fitting when the mobile cowl is in the closed position.

公开(公告)号：US20220363400A1

公开(公告)日：2022-11-17

申请号：US17701781

申请日：2022-03-23

Applicant: Airbus Operations SAS

Inventor： Jean GELIOT ,  Thierry THERON

IPC: B64D29/06

Abstract: An aircraft fairing comprising at least one joint connecting a fixed panel to a movable panel, the joint comprising at least one first flange that is connected to the fixed panel, at least one second flange that is connected to the movable panel, and an elastically deformable junction region connecting the first and second flanges, the first and second flanges and the junction region forming a single part.

公开(公告)号：US20210387740A1

公开(公告)日：2021-12-16

申请号：US17342118

申请日：2021-06-08

Applicant: Airbus Operations SAS

Inventor： Jean GELIOT ,  Thierry THERON

IPC: B64D29/08 ,  B64D29/02 ,  B64F5/45

Abstract: An aircraft pylon comprising a structure covered by a fairing. The structure includes at least one void bounded by a peripheral edge. The fairing includes at least one removable panel connected to the structure around the void and having an inner face oriented towards the structure. The structure includes at least one seal connected to the structure so as to be slightly compressed against the inner face of the removable panel. The seal extends over at least a lower portion of the peripheral edge so as to retain a fluid located below a sealing horizontal plane while ensuring ventilation beneath the fairing.