公开(公告)号：US20200291854A1

公开(公告)日：2020-09-17

申请号：US16814484

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

IPC: F02C6/18 ,  B64D15/04 ,  B64D13/08

Abstract: An aircraft propulsion system including a turbojet and a heat exchanger system including a main heat exchanger, a hot air supply pipe and a regulating valve, a first pipe bleeding high pressure stage hot air through a first valve, a second pipe bleeding intermediate pressure stage hot air through a second valve, a transfer pipe transferring the hot air to an air management system, a main supply pipe supplying cold fan duct air via a main regulating valve, an evacuation pipe expelling air to the outside, a sub heat exchanger, wherein the first pipe goes through the sub heat exchanger, a sub supply pipe supplying cold fan duct air and including a sub regulating valve, a sub evacuation pipe expelling air to the fan duct, a temperature sensor measuring a hot air temperature exiting the main heat exchanger, and a controller controlling the valves according to the measured temperature.

公开(公告)号：US20220024599A1

公开(公告)日：2022-01-27

申请号：US17383559

申请日：2021-07-23

Applicant: Airbus Operations SAS

Inventor： Julien CAYSSIALS ,  Adeline SOULIE ,  Arnaud GUICHOT ,  Nicolas BRACHET

IPC: B64D29/06 ,  B64D27/12 ,  B64D27/26

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.

公开(公告)号：US20200298986A1

公开(公告)日：2020-09-24

申请号：US16819941

申请日：2020-03-16

Applicant: Airbus Operations SAS

Inventor： Julien CAYSSIALS ,  Michael BERJOT

IPC: B64D27/26

Abstract: A rear engine fastener for an aircraft connecting a primary structure and an engine of an aircraft, the rear engine fastener comprising a support configured to be connected to the primary structure, at least one main shackle connected to the support by first and second support link pins, which are symmetrical relative to a vertical longitudinal plane, and to the engine by a first lateral engine link pin and by a central engine link pin, and at least one secondary shackle connected to the engine by a second lateral engine link pin and to the main shackle by a secondary link pin.

公开(公告)号：US20210101694A1

公开(公告)日：2021-04-08

申请号：US16940747

申请日：2020-07-28

Applicant: Airbus Operations SAS

Inventor： Julien CAYSSIALS ,  Jean GELIOT ,  Adeline SOULIE

IPC: B64D37/32 ,  B64D37/02

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.

公开(公告)号：US20200291869A1

公开(公告)日：2020-09-17

申请号：US16814494

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

IPC: F02C9/18 ,  F02C7/10

Abstract: 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.

公开(公告)号：US20200216185A1

公开(公告)日：2020-07-09

申请号：US16733783

申请日：2020-01-03

Applicant: Airbus Operations SAS

Inventor： Jacky PUECH ,  Thomas DEFORET ,  Julien CAYSSIALS

IPC: B64D27/26 ,  B64F5/10

Abstract: An aircraft engine attachment connecting an attachment body and a primary structure of an aircraft pylon, the engine attachment comprising a shear pin immobilized in translation by a first immobilization system that comprises a shoulder and a removable stop that are integral with the primary structure, between which a flange of the shear pin is immobilized, and a second immobilization system that comprises a stop plate, connected by at least one removable link to the primary structure, which closes the first hole, at least in part.

公开(公告)号：US20220246971A1

公开(公告)日：2022-08-04

申请号：US17584858

申请日：2022-01-26

Applicant: Airbus Operations SAS

Inventor： Janik FERNANDEZ GARCIA ,  Jordan COOK ,  Julien CAYSSIALS ,  Christophe LABARTHE

IPC: H01M8/2483 ,  H01M8/2404 ,  B64D27/24 ,  H01M8/2475

Abstract: A device for grouping together fuel cells, including at least two fuel cells, a support including a casing, at least one feeder configured to supply the fuel cells with fluid, at least one manifold configured to collect a fluid from the fuel cells, the feeder and the manifold being rigidly secured to the casing and positioned between the casing and the fuel cells.

公开(公告)号：US20210114741A1

公开(公告)日：2021-04-22

申请号：US17073688

申请日：2020-10-19

Applicant: Airbus Operations SAS

Inventor： Michael BERJOT ,  Julien CAYSSIALS

IPC: B64D27/26 ,  B64C3/32 ,  B64C3/18

Abstract: An aircraft including a rear wing attachment, connecting a primary structure of an aircraft pylon to its wing, and including at least one right-hand link connected to the wing by a first right-hand connecting element and to the primary structure by a second right-hand connecting element and configured to react loads oriented parallel to the vertical direction only, at least one left-hand link connected to the wing by a first left-hand connecting element and to the primary structure by a second left-hand connecting element and configured to react loads oriented parallel to the vertical direction only, a shear pin secured to the primary structure and housed in operation in a housing secured to the wing, the shear pin and the housing being configured to react loads oriented in a plane approximately perpendicular to the vertical direction.

公开(公告)号：US20230030602A1

公开(公告)日：2023-02-02

申请号：US17873368

申请日：2022-07-26

Applicant: Airbus Operations SAS

Inventor： Jordan COOK ,  Frédéric ROSSI ,  Julien CAYSSIALS

IPC: F16J15/02 ,  E04B1/68

Abstract: A bulkhead fitting device configured to sealingly link a conduit and a wall traversed by the conduit. This bulkhead fitting device includes a first ring sealingly linked to the conduit, a second ring having a flat, ring-shaped sealing face configured to be pressed against a contact face of the wall or of an intermediate part linked to the wall, an elastically deformable intermediate annular portion sealingly linking the first and second rings, a holding system configured to press the sealing face against the contact face. This bulkhead fitting device guarantees an optimum seal while enabling the absorption of forces and slight relative movements between the conduit and the wall. The device also helps to limit the propagation of vibration.

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

IPC: B64D37/32 ,  B64D37/02

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.