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公开(公告)号：US20210101694A1
公开(公告)日：2021-04-08
申请号：US16940747
申请日：2020-07-28
发明人： Julien CAYSSIALS , Jean GELIOT , Adeline SOULIE
摘要： 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：US20200291869A1
公开(公告)日：2020-09-17
申请号：US16814494
申请日：2020-03-10
发明人： Bruno MEDDA , Esteban MARTINO-GONZALEZ , Thomas STEVENS , Julien CAYSSIALS , Juan Tomas PRIETO PADILLA , Adeline SOULIE , Didier POIRIER , Pierre-Alain PINAULT , Diego BARRON VEGA
摘要： An aircraft propulsion system, including a turbojet and a heat exchanger system which includes a main heat exchanger, a hot air supply pipe, a transfer pipe transferring hot air to an air management system, a main supply pipe supplying cold air from the fan duct, an evacuation pipe expelling air to the outside, a sub heat exchanger with a high pressure pipe going therethrough, a sub supply pipe supplying cold air and including a sub regulating valve, a sub evacuation pipe expelling air, a temperature sensor, and a controller controlling the system according to the temperature measured The sub regulating valve comprises a door articulated between closed and open positions, a return spring constraining the door in the open position, and a realizing system, controlled by the controller, mobile between a blocking position and a realizing position in which the door is released to move to the open position.
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3.发明申请公开(公告)号：US20190284856A1
公开(公告)日：2019-09-19
申请号：US16293164
申请日：2019-03-05
发明人： Jean GELIOT , Adeline SOULIE
摘要： 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：US20230127600A1
公开(公告)日：2023-04-27
申请号：US17972616
申请日：2022-10-25
发明人： Adeline SOULIE
IPC分类号： F16K17/04 , F16K17/10 , F16K7/17 , H01M8/04746
摘要： 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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5.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
发明人： Jean GELIOT , Adeline SOULIE
摘要： 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
发明人： Jean GELIOT , Thomas DEFORET , Adeline SOULIE , Olivier DUBOIS
IPC分类号： B64D27/26
摘要： 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：US20220024599A1
公开(公告)日：2022-01-27
申请号：US17383559
申请日：2021-07-23
摘要： 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：US20200207481A1
公开(公告)日：2020-07-02
申请号：US16615924
申请日：2017-12-12
发明人： Stéphane COMBES , Adeline SOULIE , Olivier PAUTIS
IPC分类号： B64D27/26
摘要： 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：US20190135445A1
公开(公告)日：2019-05-09
申请号：US16180129
申请日：2018-11-05
发明人： Stéphane COMBES , Jean GELIOT , Thomas DEFORET , Adeline SOULIE , Benoit ORTEU
IPC分类号： B64D27/26
摘要： 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：US20190106221A1
公开(公告)日：2019-04-11
申请号：US16138242
申请日：2018-09-21
发明人： Stéphane COMBES , Jean GELIOT , Thomas DEFORET , Adeline SOULIE , Benoit ORTEU
摘要： 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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