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公开(公告)号：US11255293B2
公开(公告)日：2022-02-22
申请号：US16832344
申请日：2020-03-27
Applicant: Airbus Operations SAS
Inventor： Pascal Gardes , Frédéric Ridray , Benoit Orteu , Pascal Gougeon , Frédéric Piard
IPC: F02K1/72
Abstract: A turbofan with a secondary duct and including a fixed structure and a mobile assembly including a frame with openwork regions. The mobile assembly is translatable between advanced and extended positions. The openwork regions are positioned across the window in the extended position. A plurality of blocking doors is provided, each being mobile between stowed and deployed positions. An array of rams move the mobile assembly. A cascade grille mounts on the frame across the openwork region. The grille slides on the frame parallel to the translational direction. For each grille, a rear stop limits rearward movement, and a compression spring pushes the grille to the rear for abutment against a rear stop. For each grille, the fixed structure comprises a stop element against which the grille abuts upon movement from the advanced position to the extended position.
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公开(公告)号：US11772781B2
公开(公告)日：2023-10-03
申请号：US17572254
申请日：2022-01-10
Applicant: Airbus Operations SAS
Inventor： Benoit Orteu , Damien Sire
Abstract: An aircraft including two main landing gears and also a main landing gear bay configured to house, on either side of a vertical median plane, the two main landing gears in a retracted position, the main landing gear bay including a rear transverse wall, a front transverse wall and also an end wall that is approximately perpendicular to the rear and front transverse walls. The main landing gear bay includes at least one strut connecting the rear or front transverse wall and the end wall, approximately positioned in the vertical median plane.
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公开(公告)号：US11319081B2
公开(公告)日：2022-05-03
申请号：US16437260
申请日：2019-06-11
Applicant: Airbus Operations SAS
Inventor： Thomas Deforet , Benoit Orteu , Olivier Gleize
Abstract: A mounting pylon comprising a structure that comprises two C-shaped semi-structures and comprising an upper spar, a lower spar and a lateral flank, an upper panel, a lower panel, a reacting attachment point, two bars attached between the reacting attachment point and a jet engine, and a front wing attachment point attached to a wing box. The lateral flank comprises joists that are aligned between the front wing attachment point and the reacting attachment point, and where the angles between two successive joists are equal.
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4.发明授权公开(公告)号：US11193450B2
公开(公告)日：2021-12-07
申请号：US16791372
申请日：2020-02-14
Applicant: Airbus Operations SAS
Inventor： Sreekanth Ganapathi Raju , Benoit Orteu , Laurent Cazeaux , Olivier Denoy
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.
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公开(公告)号：US10464686B2
公开(公告)日：2019-11-05
申请号：US15683976
申请日：2017-08-23
Applicant: Airbus Operations SAS
Inventor： Benoit Orteu
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.
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Patent Agency Ranking
公开(公告)号：US12187411B2
公开(公告)日：2025-01-07
申请号：US17985199
申请日：2022-11-11
Applicant: Airbus Operations SAS
Inventor： Benoit Orteu , Ludovic Mil , Lionel Laganier , Dominique Marty , Philippe Robert
Abstract: An aircraft floor including at least one hinge connecting movable and fixed floor parts, which has a pivot axis parallel to a longitudinal direction. The floor also includes at least two beams, each including first and second beam portions secured respectively to the fixed and movable floor parts and connected together by a pivot link, and at least one rail including at least one first rail portion secured to the movable floor part and at least one second rail portion secured to the fixed floor part of the floor, extending the first rail portion.
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公开(公告)号：US11565822B2
公开(公告)日：2023-01-31
申请号：US16708760
申请日：2019-12-10
Applicant: Airbus Operations SAS
Inventor： Philippe Auge , Benoit Orteu , Julien Bernat , Jean Geliot , Delphine Jalbert , Frédéric Ridray , Laurent Lafont , Pascal Gardes
Abstract: A propulsion assembly having a pylon, a turbomachine comprising an engine and a fan that is enclosed by a fan casing, a nacelle surrounding the engine and the fan casing and having a load support disposed in the top part of the nacelle, a front engine attachment between the pylon and a front part of the engine, a rear engine attachment between the pylon and a rear part of the engine, a front fan attachment between the fan casing and the load support, and a rear pylon attachment between the pylon and the load support. Such a propulsion assembly allows a reduction in bulk since the load of the turbojet engine is distributed between the load support and the pylon, and the pylon is attached to the engine.
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公开(公告)号：US11105297B2
公开(公告)日：2021-08-31
申请号：US16745606
申请日：2020-01-17
Applicant: Airbus Operations SAS
Inventor： Pascal Gardes , Guillaume Seguin , Laurent Tizac , Fabien Menou , Frédéric Ridray , Benoit Orteu , Romain Cusset
Abstract: A turbofan having a nacelle comprising a slider translatable between an advanced position and a retracted position to open a window between a duct and the exterior, a plurality of blades, each one rotatable on the slider between a stowed position and a deployed position, and a maneuvering system that moves each blade and comprises, for each blade, a shaft rotatable on the slider and on which the blade is fixed, and a toothed sector fixed to the shaft, and a toothed arc rotatable on the slider about a longitudinal axis, where the teeth of the toothed arc mesh with the teeth of each toothed sector, a cam, as one with the toothed arc, and a groove, as one with a fixed structure, which receives the cam and where, when the slider moves, the cam follows the groove and rotates the toothed arc.
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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.
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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
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.
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