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公开(公告)号：US20200369397A1
公开(公告)日：2020-11-26
申请号：US16880171
申请日：2020-05-21
Applicant: Airbus Operations SAS
Inventor： Jean GELIOT , Christophe LABARTHE
Abstract: A propulsion assembly for an aircraft, the propulsion assembly having a pylon configured to be fastened beneath a wing of the aircraft, a turbomachine having a longitudinal direction, a median plane and a transverse plane, and a nacelle surrounding the turbomachine and having a load support disposed in the top part of the nacelle. The load support has a structural part fastened to the pylon and an aerodynamic part capping the structural part. The aerodynamic part has, at the front, a front part fastened to the structural part and, at the rear, a rear part fastened to the pylon. Separating the load support into two parts makes it possible to reduce the movements of the aerodynamic part capping the structural part of the load support.
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12.发明申请公开(公告)号：US20190338704A1
公开(公告)日：2019-11-07
申请号：US16394339
申请日：2019-04-25
Applicant: Airbus Operations SAS
Inventor： Jean GELIOT , Adeline SOULIE
Abstract: A propulsion assembly for an aircraft comprising a pylon and a bypass turbomachine having a fan duct in which an air flow flows. The turbomachine further comprises an air intake system with a cold bleed air device for bleeding some of the air flow from the fan duct, the device comprising a sliding scoop comprising an upstream face that is open to allow the air to pass and a lower side that has an air outlet opening connected to an exchanger. The scoop is able to slide between an open position in which the scoop extends at least in part into the fan duct and in which part of the air flow in the fan duct rushes into the scoop via the upstream face thereof, and a closed position in which the scoop does not extend into the fan duct and has its upper side closing off the cutout.
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公开(公告)号：US20190315477A1
公开(公告)日：2019-10-17
申请号：US16363513
申请日：2019-03-25
Applicant: Airbus Operations SAS
Inventor： Jean GELIOT , Thomas DEFORET , Adeline SOULIE , Olivier DUBOIS
IPC: B64D27/26
Abstract: An engine attachment configured to link an engine and an aircraft pylon comprising a first end fitting having two mutually parallel wings, a joining piece positioned between the first end fitting wings and linked to the first end fitting by a link system, fixing elements, linking the first end fitting and the pylon, including first and second fixing elements positioned between the first end fitting wings which are inclined by an angle of between 10 and 45° to be able to be put in place and removed in the presence of the joining piece linked to the first end fitting by the link system. The inclined fixing elements absorb lateral loads. The joining piece and the first end fitting are linked by the link system before the engine is fixed to the pylon. The engine is fixed to the pylon by putting the fixing elements in place.
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14.发明公开公开(公告)号：US20240082611A1
公开(公告)日：2024-03-14
申请号：US18461808
申请日：2023-09-06
Applicant: Airbus Operations SAS
Inventor： Jean GELIOT , Adeline SOULIE
Abstract: An aircraft pylon comprising a box-section primary structure and at least one tank positioned inside the primary structure. To facilitate mounting or demounting the tank, the pylon is equipped with a guide system configured to move the tank from its mounted position toward a through-hole, including a guide rail fastened to the primary structure and positioned above the tank and a guide pin fastened to the tank cooperating with the guide rail so that the tank is supported by the guide rail and is able to slide along the latter. This guide system contributes to simplifying manipulation of the tank when mounting or demounting the tank by at least partly compensating its weight and guiding the tank.
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15.发明公开公开(公告)号：US20230233892A1
公开(公告)日：2023-07-27
申请号：US18158099
申请日：2023-01-23
Applicant: Airbus Operations SAS
Inventor： Jean GELIOT , Adeline SOULIE
Abstract: An assembly of at least one extinguishing agent tank in the interior of an aircraft strut. The strut has an elongate chamber form extending in a longitudinal direction and includes a plurality of ribs which are spaced apart and arranged in parallel along the strut, each extending orthogonally to the longitudinal direction. The ribs are covered by lateral walls, at least one of the walls comprising a window opening into a space between two consecutive ribs, and via which a spherical extinguishing agent tank is installed in the interior of the strut. The assembly of the tank on the strut includes a frame arranged in the interior of the strut, facing the window and secured on each of the two consecutive ribs. The frame forms a support area on which the tank is supported. A system locks the extinguishing agent tank on the frame.
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Patent Agency Ranking
16.发明申请公开(公告)号：US20210188457A1
公开(公告)日：2021-06-24
申请号：US17123444
申请日：2020-12-16
Applicant: Airbus Operations SAS
Inventor： Julien CAYSSIALS , Jean GELIOT , Adeline SOULIE
Abstract: An assembly for an aircraft, the assembly including a pylon with a lateral wall pierced by a window, a tank with a neck blocked by a film and carrying a first anchoring arrangement, and a fixing arrangement for fixing at least a part of the tank bearing the neck inside the pylon, a discharge pipe, and a discharge head. The head includes an explosive cartridge and a hole with a second anchoring arrangement in which discharges the discharge pipe. The discharge head is fixed inside the pylon facing the window. The explosive cartridge is designed to generate in the hole a shockwave sufficient to rupture the film An assembly of this kind enables simple and rapid removal of the tank from and installation thereof inside the pylon.
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17.发明申请公开(公告)号：US20200307816A1
公开(公告)日：2020-10-01
申请号：US16827008
申请日：2020-03-23
Applicant: Airbus Operations SAS
Inventor： Michael BERJOT , Jean GELIOT
Abstract: An aircraft rear engine attachment connecting a primary structure of a pylon and an engine of an aircraft. The rear engine attachment includes first and second rods, each of them including at least two parts, a first part including at least one support orifice, accommodating a support link bar, configured to connect the rod directly or indirectly to the primary structure, at least one second part including at least one engine orifice, accommodating an engine link bar, configured to connect the rod directly or indirectly to the engine, and also detachable link elements for connecting the first and second parts oriented parallel to the direction of the rod.
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18.发明申请公开(公告)号：US20190285000A1
公开(公告)日：2019-09-19
申请号：US16271300
申请日：2019-02-08
Applicant: Airbus Operations SAS
Inventor： Jean GELIOT , Adeline SOULIE
Abstract: A propulsion system for an aircraft comprising an air system, the propulsion system comprising a fairing having an openwork grating, a dual-flow jet engine with a compression stage and a secondary jet, and an air-drawing system comprising a heat exchanger. A hot pipeline connects between the compression stage and the air system, and passing through the heat exchanger. A cold pipeline connects between the secondary jet and the openwork grating and passes through the heat exchanger. The air-drawing system comprises a shutter arranged at the openwork grating and displaced by a motor between an open position in which the shutter does not block the holes of the openwork grating and a closed position in which the shutter blocks the openwork grating holes. The incorporation of the discharge and regulation function at the openwork grating allows for a space saving facilitating incorporation of the air-drawing system in the propulsion system.
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公开(公告)号：US20200164994A1
公开(公告)日：2020-05-28
申请号：US16689188
申请日：2019-11-20
Applicant: Airbus Operations SAS
Inventor： Jean GELIOT , Christophe LABARTHE
Abstract: An aircraft nacelle which comprises a structure, an upstream cowl, an upper cowl arranged to the rear of the upstream cowl and having a starboard-side door and a port-side door, each being articulated between a closed position and an open position, each having a front edge, a rear edge, an inner edge and an outer edge. The nacelle comprises, for each door, an articulation and a locking system. Each door is articulated at the level of its outer edge and, in the closed position, the inner edge of one door is contiguous with the inner edge of the other door. Such a nacelle makes the technicians' work easier because the two articulated doors can be opened wide and give easy access under the cowl.
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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
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.
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