公开(公告)号：US20250027452A1

公开(公告)日：2025-01-23

申请号：US18772636

申请日：2024-07-15

Applicant: Airbus Operations SAS

Inventor： Lionel CZAPLA ,  Rémi AMARGIER

IPC: F02C7/25 ,  B64D27/10 ,  B64D29/08 ,  B64D37/30 ,  B64D37/32 ,  F02C7/22

Abstract: A propulsion assembly having a combustion chamber and a turbine, a nacelle with a front cowl facing the turbine, with a window passing through it, and a rear cowl to the rear of the turbine, a fire barrier between the front cowl and the rear cowl, a dihydrogen supply pipe meandering from the inside of the rear cowl, then in a sealed manner through the fire barrier, then through the window as far as the combustion chamber, wherein the supply pipe has an intermediate section between the fire barrier and the window, and a plate fastened in a sealed manner to the intermediate section and fastened in a sealed manner to the front cowl around the window.

公开(公告)号：US20240417090A1

公开(公告)日：2024-12-19

申请号：US18742442

申请日：2024-06-13

Applicant: Airbus Operations SAS

Inventor： Lionel CZAPLA ,  Kotaro FUKASAKU ,  Rémi AMARGIER

IPC: B64D27/40

Abstract: A device for coupling a propulsion system to an engine pylon of an aircraft, the device comprising a baseplate comprising first and second parts of the baseplate placed against each other so as to form a base suitable for being fastened to the propulsion system, and a first wall extending substantially perpendicularly to the base. The first wall of the baseplate interacts with a sleeve, a pair of flanges and fasteners to the engine pylon.

公开(公告)号：US20240174368A1

公开(公告)日：2024-05-30

申请号：US18519467

申请日：2023-11-27

Applicant: Airbus Operations SAS

Inventor： Jérôme CASSAGNE ,  Frédéric VINCHES ,  Lionel CZAPLA ,  Kotaro FUKASAKU ,  Rémi AMARGIER

IPC: B64D27/24 ,  B60L50/70 ,  B64D27/26

CPC classification number: B64D27/24 ,  B60L50/70 ,  B64D27/26 ,  B60L2200/10 ,  B64D2027/262

Abstract: A propulsion assembly for an aircraft, having a T-shaped chassis with a horizontal structure and a vertical structure, a gearbox fastened to a front of the chassis, and a propulsion system having the following propulsion elements: an electric motor driving the components of the gearbox, a fuel cell, a tank and a cooling system, wherein the propulsion elements are fastened beneath the horizontal structure and against the vertical structure by fastening means.

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.