公开(公告)号：US20230045036A1

公开(公告)日：2023-02-09

申请号：US17878331

申请日：2022-08-01

Applicant: Airbus SAS ,  Airbus Operations SAS

Inventor： Lionel CZAPLA ,  Antoine ABELE ,  Benjamin THUBERT ,  Alexis PISSAVIN ,  Abhishek VERMA ,  Alistair FORBES ,  Jorge A. CARRETERO BENIGNOS ,  Benedikt BAMMER

IPC: F02C7/224 ,  F02C7/22 ,  B64D37/04 ,  B64D37/30

Abstract: An aircraft including a fuselage, a wing structure, at least one turbomachine running on hydrogen and generating thrust at a propulsion unit distant from the fuselage, at least one fuel tank positioned in the fuselage and configured to store hydrogen in the cryogenic state, at least one hydrogen supply device connecting the fuel tank and the turbomachine and including at least one pump positioned in the fuselage in the vicinity of the fuel tank, at least one hydrogen heating system positioned in the fuselage in the vicinity of the pump. This solution makes it possible to reduce a length of the complex double-walled pipes configured for carrying the hydrogen in the cryogenic state between the fuel tank and the hydrogen heating system.

公开(公告)号：US20220135236A1

公开(公告)日：2022-05-05

申请号：US17512188

申请日：2021-10-27

Applicant: Airbus Operations SAS

Inventor： Antoine ABELE ,  Maxime ZEBIAN

IPC: B64D13/08 ,  B64D37/32 ,  F25B13/00 ,  F25B31/02

Abstract: An aircraft having an engine, a cabin, an air conditioning system collecting the hot air from the engine, so as to treat the hot air, regulate a temperature of the hot air and send the hot air towards the cabin via a main line, an air line channeling the air leaving the cabin, and an arrangement for cooling the engine using the air thus drawn off by the air line. By drawing off the air at the outlet of the cabin, the performance of the engine is improved and the fuel consumption is reduced.

公开(公告)号：US20180170563A1

公开(公告)日：2018-06-21

申请号：US15845330

申请日：2017-12-18

Applicant: Airbus Operations SAS ,  Airbus Operations SL

Inventor： Eric BOUCHET ,  Esteban MARTINO-GONZALEZ ,  Jerome COLMAGRO ,  Fernando INIESTA LOZANO ,  Julien MOULIS ,  Antoine ABELE

IPC: B64D27/20 ,  B64C1/16 ,  B64D27/26

CPC classification number: B64D27/20 ,  B64C1/061 ,  B64C1/16 ,  B64D27/14 ,  B64D27/26 ,  B64D2027/268 ,  B64D2033/0286 ,  Y02T50/44

Abstract: In order to reduce the congestion of the attachment means for aircraft engines in a secondary vein, a first fuselage frame has two side portions for supporting the engine, each associated with one of the two partly buried side engines, these portions being curved inwards so as to surround and follow the profile of the outer shroud of an intermediate case. The side portion is attached on this shroud through first and second attachment arrangements spaced apart from each other circumferentially, these arrangements being configured in order to allow absorption of the forces related to the torque along a longitudinal direction of the engine.