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公开(公告)号：US12054271B2
公开(公告)日：2024-08-06
申请号：US17391825
申请日：2021-08-02
Applicant: Airbus SAS , Airbus Operations SAS
Inventor： Sebastien Alby , Jean Geliot , Thomas Deforet , Olivier Dubois , Joël Dedieu , Xavier Bardey
Abstract: A method for assembling an aircraft pylon including a primary structure and at least one internal system positioned at least partially within the primary structure, wherein the assembly method includes a first step of assembling a part of the primary structure so that the interior of the primary structure remains accessible, a step of mounting an internal systems module including at least one support and at least one internal system connected to the support, a second step of assembling the internal systems module and the partially assembled primary structure, a third step of assembling any element of the primary structure not assembled in the first assembly step, and an aircraft pylon assembled by such a method.
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2.发明授权公开(公告)号：US11511873B2
公开(公告)日：2022-11-29
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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公开(公告)号：US11518532B2
公开(公告)日：2022-12-06
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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公开(公告)号：US11345479B2
公开(公告)日：2022-05-31
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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公开(公告)号：US11247781B2
公开(公告)日：2022-02-15
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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Patent Agency Ranking
公开(公告)号：US11066992B2
公开(公告)日：2021-07-20
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：US11021898B2
公开(公告)日：2021-06-01
申请号：US16293164
申请日：2019-03-05
Applicant: Airbus Operations SAS
Inventor： Jean Geliot , Adeline Soulie
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.
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公开(公告)号：US11807375B2
公开(公告)日：2023-11-07
申请号：US17709514
申请日：2022-03-31
Applicant: Airbus Operations SAS
Inventor： Laurent Sammito , Jean Geliot , Thierry Theron
IPC: B64D29/02
CPC classification number: B64D29/02
Abstract: A nacelle for an aircraft, including a structure, a cap attached to the structure and a seal system including an arch forming a channel which extends beneath a rear edge of the cap and which has a bottom, the arch being attached to the structure, a seal in the form of a solid block in the channel and beneath the rear edge of the cap, a spring system arranged to move the seal away from the bottom, and a retaining arrangement configured to prevent the seal from leaving the channel under the action of the spring system. With an arrangement of this kind, it is not necessary to oversize the bead, this being replaced with a solid seal mounted on a spring system.
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公开(公告)号：US20220315233A1
公开(公告)日：2022-10-06
申请号：US17709514
申请日：2022-03-31
Applicant: Airbus Operations SAS
Inventor： Laurent Sammito , Jean Geliot , Thierry Theron
IPC: B64D29/02
Abstract: A nacelle for an aircraft, including a structure, a cap attached to the structure and a seal system including an arch forming a channel which extends beneath a rear edge of the cap and which has a bottom, the arch being attached to the structure, a seal in the form of a solid block in the channel and beneath the rear edge of the cap, a spring system arranged to move the seal away from the bottom, and a retaining arrangement configured to prevent the seal from leaving the channel under the action of the spring system. With an arrangement of this kind, it is not necessary to oversize the bead, this being replaced with a solid seal mounted on a spring system.
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10.发明授权公开(公告)号：US11434020B2
公开(公告)日：2022-09-06
申请号：US16940747
申请日：2020-07-28
Applicant: Airbus Operations SAS
Inventor： Julien Cayssials , Jean Geliot , Adeline Soulie
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.
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