公开(公告)号：US20240025553A1

公开(公告)日：2024-01-25

申请号：US18355779

申请日：2023-07-20

Applicant: Airbus Operations SAS

Inventor： Mathieu MAHE ,  Christophe LABARTHE ,  Frederic JOURNADE ,  Frédéric VINCHES ,  Franck ALVAREZ ,  Lionel CZAPLA ,  Emmanuel VARDELLE ,  Rémi AMARGIER ,  Kotaro FUKASAKU

IPC: B64D27/24 ,  H01M8/2465

CPC classification number: B64D27/24 ,  H01M8/2465 ,  B64D2027/264

Abstract: A propulsion unit, for an aircraft, comprising a hollow chassis with an opening at the bottom, a propulsion system comprising an electric motor with a propeller, a fuel cell, a tank and a cooling system, and one platform fastened to the chassis through said opening using fasteners and in which at least one element of the propulsion system is fastened to the platform. An aircraft with such a propulsion unit.

公开(公告)号：US20230132103A1

公开(公告)日：2023-04-27

申请号：US17971680

申请日：2022-10-24

Applicant: Airbus Operations SAS

Inventor： Lionel CZAPLA ,  Frédéric PIARD

IPC: B64D29/00

Abstract: An aircraft nacelle comprising first and second ducts, each including, in a radial direction, at least one first or second acoustically resistive layer, at least one first or second alveolar structure, as well as a first or second reflective layer. The first and second ducts include first and second flanges which are positioned on transverse planes, oriented towards the interior, and are connected respectively to the first and second reflective layers and are maintained placed against one another by connection elements accessible from the interior of the first and second ducts. The first and second ducts are configured to form at least one receptacle in which there are positioned the first and second flanges as well as the connection elements, the receptacle being closed by at least one cap.

公开(公告)号：US20230044493A1

公开(公告)日：2023-02-09

申请号：US17879869

申请日：2022-08-03

Applicant: Airbus SAS ,  Airbus Operations SAS

Inventor： Lionel CZAPLA ,  Jorge A. CARRETERO BENIGNOS

IPC: F28D9/00

Abstract: A heat exchanger including a sealed housing and a body positioned inside the housing, the body including a stack of least one first assembly of first and second plates pressed against each other, between which flows a first fluid, and at least one second assembly of third and fourth plates pressed against each other, between which flows a second fluid, the first and second assemblies being arranged so that they transfer heat between the first and second fluids. This configuration limits the risk of leaks and mixing of the two fluids.

公开(公告)号：US20230022291A1

公开(公告)日：2023-01-26

申请号：US17870052

申请日：2022-07-21

Applicant: Airbus SAS ,  Airbus Operations SAS

Inventor： Jorge A. CARRETERO BENIGNOS ,  Lionel CZAPLA

IPC: B64D27/26 ,  B64D29/06 ,  B64D37/02 ,  B64D33/02 ,  B64D33/04

Abstract: A propulsion assembly for an aircraft, comprising a nacelle, a propulsion system housed in the nacelle and comprising a fairing, a rotary assembly that has a combustion chamber and is housed in the fairing, an exhaust nozzle delimited by a nozzle wall of the fairing, a fuel tank, a supply duct which connects the tank and the combustion chamber, and a heat exchanger system ensuring, during operation of the propulsion system, an exchange of heat energy between the hot combustion gases circulating in the nozzle and the colder fuel circulating in the supply duct by thermal radiation through the nozzle wall.

公开(公告)号：US20200164998A1

公开(公告)日：2020-05-28

申请号：US16695375

申请日：2019-11-26

Applicant: Airbus Operations SAS

Inventor： Claire MAFFRE ,  Jérôme GAILLARDO ,  Lionel CZAPLA ,  Florian RAVISE ,  Laurent CALIMAN ,  Laurent CAZEAUX ,  Antoine COUSIN ,  Denis BROSSARD

IPC: F02K1/34 ,  F02C7/24 ,  G10K11/172 ,  G10K11/162

Abstract: An acoustic absorption structure comprising a plurality of resonators. Each resonator comprises a first chamber which has a first mouthpiece delimited by an edge pressed against an inner surface of a porous zone of a skin so that the first chamber and the skin delimit a first cavity, a second chamber, in which is positioned the first chamber, which delimits, with the first chamber, a second cavity, at least one acoustic orifice passing through the first chamber, at least one drainage orifice passing through the first chamber and at least one drainage hole passing the second chamber, each drainage orifice and each drainage hole being configured to limit an accumulation of fluid in the resonator. Also, an aircraft propulsive assembly or an aircraft comprising the acoustic absorption structure are provided.

公开(公告)号：US20250026481A1

公开(公告)日：2025-01-23

申请号：US18774119

申请日：2024-07-16

Applicant: Airbus Operations SAS

Inventor： Lionel CZAPLA ,  Christophe LABARTHE ,  Kotaro FUKASAKU

IPC: B64D29/06 ,  B64D37/34

Abstract: A nacelle comprising a cowl which has a window, a box structure around the window and containing a conditioning device for conditioning dihydrogen, a door mounted pivotably on the cowl between a closed position and an open position, a maneuvering system for moving the door from the closed position to the open position, a detector for detecting the presence of dihydrogen in the box structure, and a control unit designed to make the maneuvering system open on the basis of information supplied by the detector.

公开(公告)号：US20240359811A1

公开(公告)日：2024-10-31

申请号：US18644785

申请日：2024-04-24

Applicant: Airbus Operations SAS

Inventor： Jérôme MILLIERE ,  Lionel CZAPLA ,  Romain JOUBERT

IPC: B64D37/30 ,  B64D37/00 ,  F17C7/00

CPC classification number: B64D37/30 ,  B64D37/005 ,  F17C7/00 ,  F17C2205/0332 ,  F17C2205/0335 ,  F17C2205/0355 ,  F17C2221/012 ,  F17C2227/0135 ,  F17C2227/0302 ,  F17C2265/066 ,  F17C2270/0189

Abstract: An aircraft comprising at least one secondary structure which separates an inner zone from an outer zone and at least one hydrogen supplying device connecting a hydrogen tank and a motor, and having at least one portion fitted with shut-off valves for isolating it in the event of a leak. The portion has at least one outer enclosure, at least one inner element that is located in the outer enclosure and carries the hydrogen, and at least one interior zone located between the inner element and the outer enclosure, the hydrogen supplying device comprising at least one ventilation system configured to vent gases present in the interior zone toward the outer zone of the secondary structure.

公开(公告)号：US20240278922A1

公开(公告)日：2024-08-22

申请号：US18581718

申请日：2024-02-20

Applicant: Airbus SAS ,  Airbus Operations SAS

Inventor： Lionel CZAPLA ,  Alexis PISSAVIN

IPC: B64D29/06 ,  B64C1/14 ,  B64C1/00

CPC classification number: B64D29/06 ,  B64C1/1407 ,  B64C2001/009

Abstract: An aircraft propulsion unit comprising a motor, a system for supplying fuel to the motor, a fairing inside which the motor and at least part of the fuel supplying system are positioned, and at least one pressure relief device configured to establish communication between the inner and outer zones of the fairing when the pressure in the inner zone is greater than or equal to a given threshold or when a leak is detected. Also an aircraft comprising at least one such propulsion unit.

公开(公告)号：US20240271573A1

公开(公告)日：2024-08-15

申请号：US18438887

申请日：2024-02-12

Applicant: Airbus Operations SAS

Inventor： Lionel CZAPLA ,  Emmanuel VARDELLE

IPC: F02C7/32 ,  B64D27/12 ,  B64D29/08 ,  B64D37/30 ,  F02C7/22 ,  F02K3/02

CPC classification number: F02C7/32 ,  B64D27/12 ,  B64D37/30 ,  F02C7/22 ,  F02K3/02 ,  B64D29/08

Abstract: A propulsion assembly for an aircraft having a chassis in the form of a cage with bars, a turbine, a dihydrogen supply pipe winding inside a nacelle as far as the rear of the turbine, with a radial step towards the outside of the nacelle, a rail with a radial step towards the outside of the nacelle, a bypass pipe connected between the two radial steps outside the nacelle, and a protection plate fastened to the bars, and an absorber between the protection plate and the related bar.

公开(公告)号：US20240109667A1

公开(公告)日：2024-04-04

申请号：US18476579

申请日：2023-09-28

Applicant: Airbus SAS ,  Airbus Operations SAS

Inventor： Lionel CZAPLA ,  Alexis PISSAVIN

IPC: B64D37/30 ,  B64D27/12 ,  F02C7/22

CPC classification number: B64D37/30 ,  B64D27/12 ,  F02C7/22

Abstract: A propulsion assembly for an aircraft, which has a propulsion system with a combustion chamber surrounded by a casing, a supply pipe that conveys dihydrogen to the combustion chamber through the casing via injectors, and a housing fastened to the casing in a sealed manner around the latter, wherein the supply pipe has a downstream part housed inside the housing and wherein the injectors are also housed inside the housing.