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公开(公告)号：US11408338B2
公开(公告)日：2022-08-09
申请号：US16814506
申请日：2020-03-10
Applicant: Airbus SAS , Airbus Operations SAS , Airbus Operations, S.L.
Inventor： Bruno Medda , Esteban Martino-Gonzalez , Thomas Stevens , Julien Cayssials , Juan Tomas Prieto Padilla , Adeline Soulie , Didier Poirier , Pierre-Alain Pinault , Diego Barron Vega
Abstract: An aircraft propulsion system, including a turbojet and a heat exchanger system including a main heat exchanger, a hot air supply pipe and regulating valve, a high pressure pipe bleeding high pressure stage hot air through a first valve, an intermediate pressure pipe bleeding intermediate pressure stage hot air through a second valve, a pipe transferring hot air to an air management system, a main supply pipe supplying fan duct cold air including a main regulating valve, an evacuation pipe expelling air to the outside, a sub heat exchanger, wherein the supply pipe from the regulating valve goes through the sub heat exchanger, a sub supply pipe supplying cold air from the main supply pipe, a sub evacuation pipe expelling air to the fan duct, a temperature sensor measuring hot air temperature exiting the main heat exchanger, and a controller controlling the valves according to the measured temperature.
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公开(公告)号：US11975859B2
公开(公告)日：2024-05-07
申请号：US17383559
申请日：2021-07-23
Applicant: Airbus Operations SAS
Inventor： Julien Cayssials , Adeline Soulie , Arnaud Guichot , Nicolas Brachet
CPC classification number: B64D29/06 , B64D27/12 , B64D27/40 , F02C7/20 , B64D27/402 , B64D2045/009
Abstract: A propulsive assembly for aircraft comprising an engine, a nacelle arranged around the engine and a pylon supporting the engine, the nacelle including two engine cowls and reversing cowls, each cowl having an internal skin, characterized in that at least one of the cowls of the nacelle comprises at least one box arranged in a space situated between the internal skin of the cowl and the engine, the box delimiting a volume of inert material, the inert material being flame retardant foam. This box partially blocks a zone of the engine where a fire is likely to begin, which makes it possible to limit the volume of a fire zone of the engine, and thus reduce the quantity of extinguishing agent which is necessary to extinguish a fire in the zone of the engine concerned.
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公开(公告)号：US11542022B2
公开(公告)日：2023-01-03
申请号：US16615924
申请日：2017-12-12
Applicant: Airbus Operations SAS
Inventor： Stéphane Combes , Adeline Soulie , Olivier Pautis
IPC: B64D27/26
Abstract: A propulsion assembly for an aircraft, comprising a pylon to be secured below a wing of the aircraft and having a front face and a lower face, and a turbomachine comprising, from upstream to downstream in a direction of a flow of air passing through the turbomachine during operation, a fan and an engine driving the fan. The fan is faired by a fan casing and the engine is faired, from upstream to downstream, by an intermediate casing and an engine casing, the intermediate casing having a hub and an outer ring extending the fan casing, the ring being spaced apart radially from the hub and secured to the latter by arms extending in an air duct. The propulsion assembly comprises a front engine attachment secured between the pylon front face and the hub and a rear engine attachment secured between the pylon lower face and the engine casing.
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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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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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Patent Agency Ranking
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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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：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：US12129931B2
公开(公告)日：2024-10-29
申请号：US17972616
申请日：2022-10-25
Applicant: Airbus Operations SAS
Inventor： Adeline Soulie
IPC: F16K17/04 , F16K7/17 , F16K17/10 , H01M8/04746 , A62C99/00
CPC classification number: F16K17/0453 , F16K7/17 , F16K17/10 , H01M8/04746 , A62C99/0018
Abstract: An enclosure containing an inerting gas and at least one liquid to be discharged. This enclosure comprises at least one orifice positioned in its lower part and a liquid discharging system positioned at the orifice. This liquid discharging system is configured to take up a closed state and an open state in which the system allows the liquid to flow towards the outside of the enclosure and includes at least one element that is elastically deformable depending on the pressure inside the enclosure and, depending on its deformation, controls the open or closed state of the liquid discharging system. This solution makes it possible to achieve simple and automatic regulation of the volume of the liquid in the enclosure, without a sensor. An aircraft including at least one such enclosure is also provided.
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