公开(公告)号：US20230102097A1

公开(公告)日：2023-03-30

申请号：US17952411

申请日：2022-09-26

Applicant: Airbus Operations SAS

Inventor： Adeline SOULIE

IPC: B64D37/30 ,  F16L39/00 ,  B64D37/00

Abstract: A pipeline including at least first and second portions, each comprising outer and inner pipes, at least one coupling system connecting the first and second portions and including at least a downstream flange ring connected to at least one of the outer and inner pipes of the first portion, at least an upstream flange ring connected to at least one of the outer and inner pipes of the second portion, connecting elements connecting the upstream and downstream flange rings, first and second annular seals interposed between the upstream and downstream flange rings and configured to delimit, with the upstream and downstream flange rings, a buffer space containing an atmosphere, the pipeline comprising at least one leak detection system configured to determine at least one characteristic of the atmosphere of the buffer space.

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：US20190241272A1

公开(公告)日：2019-08-08

申请号：US16253040

申请日：2019-01-21

Applicant: Airbus Operations SAS

Inventor： Jean GELIOT ,  Thomas DEFORET ,  Adeline SOULIE

IPC: B64D27/26 ,  F16M1/04 ,  F16B21/20

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.

公开(公告)号：US20190161198A1

公开(公告)日：2019-05-30

申请号：US16195971

申请日：2018-11-20

Applicant: Airbus Operations SAS

Inventor： Stéphane COMBES ,  Jean GELIOT ,  Thomas DEFORET ,  Adeline SOULIE ,  Benoit ORTEU

IPC: B64D27/26

Abstract: A swivel axis for an aircraft engine attachment, comprising a tubular main axis which has, at a first end, a head and, at a second end, a threaded portion onto which is screwed a first nut. A fail-safe axis is configured to be mounted to swivel inside the main axis. The fail-safe axis has, at a first end, a head and, at a second end, a threaded portion onto which is screwed a second nut. The fail-safe axis is linked by an axial link to the first nut. Since the fail-safe axis is linked to the first nut, it is necessarily inserted into the main axis when the first nut is screwed onto the main axis.

公开(公告)号：US20190152615A1

公开(公告)日：2019-05-23

申请号：US16192950

申请日：2018-11-16

Applicant: Airbus Operations SAS

Inventor： Stéphane COMBES ,  Jean GELIOT ,  Thomas DEFORET ,  Adeline SOULIE ,  Benoit ORTEU

IPC: B64D27/26

Abstract: A rear engine attachment for an engine of an aircraft which comprises a pylon having a bottom face, the rear engine attachment comprising a first fitting configured to be fixed against the bottom face and having a wall, a second fitting configured to be secured to a structural casing of the engine, two front links and two rear links, which are fixed by one and the same main link point to the wall and by two link points on either side of the second fitting. Such a motorization assembly allows for a reduction of the bulk, in particular at the rear engine attachment, which helps in improving the overall performance of the motorization assembly.

公开(公告)号：US20240082611A1

公开(公告)日：2024-03-14

申请号：US18461808

申请日：2023-09-06

Applicant: Airbus Operations SAS

Inventor： Jean GELIOT ,  Adeline SOULIE

IPC: A62C3/08 ,  A62C35/02

CPC classification number: A62C3/08 ,  A62C35/02

Abstract: An aircraft pylon comprising a box-section primary structure and at least one tank positioned inside the primary structure. To facilitate mounting or demounting the tank, the pylon is equipped with a guide system configured to move the tank from its mounted position toward a through-hole, including a guide rail fastened to the primary structure and positioned above the tank and a guide pin fastened to the tank cooperating with the guide rail so that the tank is supported by the guide rail and is able to slide along the latter. This guide system contributes to simplifying manipulation of the tank when mounting or demounting the tank by at least partly compensating its weight and guiding the tank.

公开(公告)号：US20230233892A1

公开(公告)日：2023-07-27

申请号：US18158099

申请日：2023-01-23

Applicant: Airbus Operations SAS

Inventor： Jean GELIOT ,  Adeline SOULIE

IPC: A62C3/08 ,  A62C35/02 ,  B64D27/26

CPC classification number: A62C3/08 ,  A62C35/02 ,  B64D27/26

Abstract: An assembly of at least one extinguishing agent tank in the interior of an aircraft strut. The strut has an elongate chamber form extending in a longitudinal direction and includes a plurality of ribs which are spaced apart and arranged in parallel along the strut, each extending orthogonally to the longitudinal direction. The ribs are covered by lateral walls, at least one of the walls comprising a window opening into a space between two consecutive ribs, and via which a spherical extinguishing agent tank is installed in the interior of the strut. The assembly of the tank on the strut includes a frame arranged in the interior of the strut, facing the window and secured on each of the two consecutive ribs. The frame forms a support area on which the tank is supported. A system locks the extinguishing agent tank on the frame.

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.

公开(公告)号：US20200347782A1

公开(公告)日：2020-11-05

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

IPC: F02C6/08 ,  F02C7/047 ,  F02C7/10 ,  B64D15/04

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.

公开(公告)号：US20190285000A1

公开(公告)日：2019-09-19

申请号：US16271300

申请日：2019-02-08

Applicant: Airbus Operations SAS

Inventor： Jean GELIOT ,  Adeline SOULIE

IPC: F02C7/18 ,  F02K3/02 ,  B64D33/08 ,  B64D27/18

Abstract: A propulsion system for an aircraft comprising an air system, the propulsion system comprising a fairing having an openwork grating, a dual-flow jet engine with a compression stage and a secondary jet, and an air-drawing system comprising a heat exchanger. A hot pipeline connects between the compression stage and the air system, and passing through the heat exchanger. A cold pipeline connects between the secondary jet and the openwork grating and passes through the heat exchanger. The air-drawing system comprises a shutter arranged at the openwork grating and displaced by a motor between an open position in which the shutter does not block the holes of the openwork grating and a closed position in which the shutter blocks the openwork grating holes. The incorporation of the discharge and regulation function at the openwork grating allows for a space saving facilitating incorporation of the air-drawing system in the propulsion system.