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公开(公告)号：US11319084B2
公开(公告)日：2022-05-03
申请号：US16720848
申请日：2019-12-19
Applicant: Airbus Operations SAS
Inventor： Jean Geliot , Christophe Labarthe
Abstract: A propulsive assembly of an aircraft comprises a junction fairing, ensuring a continuity between a nacelle and a pylon, which comprises a fixed frame, linked to the nacelle and/or to the pylon by a link system configured to absorb any deformations and/or misalignments between the nacelle and the pylon in operation, which has an outer wall comprising an opening, a cowl, mobile between a closed position in which the cowl blocks the opening, and an open position in which the cowl at least partially frees the opening, which has a panel, the outer wall of the fixed frame and the panel of the cowl having outer surfaces which form the aerodynamic surface of the junction fairing. An aircraft is also provided which comprises at least one such propulsive assembly.
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公开(公告)号：US11242159B2
公开(公告)日：2022-02-08
申请号：US16418555
申请日：2019-05-21
Applicant: Airbus Operations SAS
Inventor： Jean Geliot
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.
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公开(公告)号：US11111027B2
公开(公告)日：2021-09-07
申请号：US16415356
申请日：2019-05-17
Applicant: Airbus Operations SAS
Inventor： Jean Geliot , Adeline Soulie
Abstract: An aircraft has at least one cowling, a fixed structure, and a hinge system connecting the cowling to the fixed structure. The hinge system includes at least two hinges and at least two stops, including a first stop integral with the fixed structure and a second stop integral with the cowling, the first and second stops being configured to be in contact one against the other when the cowling is in the closed position and to ensure an absorption of a part of the loads between the cowling and the fixed structure at least along a direction perpendicular to the pivot axis of the hinge system.
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公开(公告)号：US10738705B2
公开(公告)日：2020-08-11
申请号：US15921870
申请日：2018-03-15
Applicant: Airbus Operations SAS
Inventor： Jérôme Cassagne , Jean Geliot
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.
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公开(公告)号：US10577114B2
公开(公告)日：2020-03-03
申请号：US16253040
申请日：2019-01-21
Applicant: Airbus Operations SAS
Inventor： Jean Geliot , Thomas Deforet , Adeline Soulie
Abstract: An assembly for an aircraft engine mounting comprising an articulation axis supported by two plain bearings and a blocking device blocking the translation of the articulation axis in a direction which comprises a blocking screw that is screwed, in operation, into a first, tapped internal portion of a tubular extension secured to one of the two plain bearings, a first blocking system comprising an internal elastic stop ring housed in a groove formed in the tubular extension, and a second blocking system comprising a blocking screw which passes through first orifices passing through the second section of the blocking screw and second orifices passing through the tubular extension.
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Patent Agency Ranking
公开(公告)号：US11987370B2
公开(公告)日：2024-05-21
申请号：US17849882
申请日：2022-06-27
Applicant: Airbus Operations SAS
Inventor： Jean Geliot
CPC classification number: B64D27/40 , B64D27/02 , F02C7/20 , B64D27/402
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.
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公开(公告)号：US11702217B2
公开(公告)日：2023-07-18
申请号：US17342118
申请日：2021-06-08
Applicant: Airbus Operations SAS
Inventor： Jean Geliot , Thierry Theron
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.
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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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19.发明授权公开(公告)号：US11547884B2
公开(公告)日：2023-01-10
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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公开(公告)号：US11319083B2
公开(公告)日：2022-05-03
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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