公开(公告)号：US20220411074A1

公开(公告)日：2022-12-29

申请号：US17849915

申请日：2022-06-27

Applicant: Airbus Operations SAS ,  Airbus Operations GmbH

Inventor： Florent HUET ,  Thomas JOSSET ,  Holger BAMMANN ,  Marion GOURGUES

IPC: B64D13/06 ,  B64D27/24

Abstract: An air supply system for a pneumatic de-icing assembly for de-icing surfaces of an aircraft, the aircraft comprising an air-conditioning system supplied by at least one first air compressor connected to a device for drawing in air outside the aircraft, the pneumatic de-icing assembly comprising an air supply inlet connected to an outlet of the first air compressor or to an outlet of the air-conditioning system. Thus, it is possible to supply air to a pneumatic de-icing system of an airplane equipped with electric motors or of what is referred to as “bleedless” type.

公开(公告)号：US20250002168A1

公开(公告)日：2025-01-02

申请号：US18742140

申请日：2024-06-13

Applicant: Airbus Operations SAS

Inventor： Florent CREBASSOL ,  Grégoire SMITH ,  Florent HUET ,  François PONS

IPC: B64D33/02 ,  B64D45/02

Abstract: An acoustic attenuation panel comprising, from a first face to an opposite second face, an acoustically resistive structure, at least one cellular structure and a reflective layer. This acoustic attenuation panel comprises an induction-based frost treatment system which comprises at least one electromagnetic field generator positioned at the reflective layer and at least one electrically conductive element situated at the first face of the acoustic attenuation panel and configured to generate a heating through an induction phenomenon. Also an aircraft and an air intake of an aircraft nacelle comprising at least one such panel.

公开(公告)号：US20210024221A1

公开(公告)日：2021-01-28

申请号：US16938227

申请日：2020-07-24

Applicant: Airbus Operations SAS ,  Airbus Operations GmbH

Inventor： Florent HUET ,  Stefan BENSMANN ,  Marcus ERBAN ,  Andreas GELLERT ,  Martin FEES

IPC: B64D15/04 ,  B64C3/28 ,  B64C3/18 ,  B64D13/06

Abstract: A leading edge member, an airfoil and an aircraft using the leading edge member to improve de-icing capacity by recirculating hot bleed air in a spanwise direction and to increase the mass and heat flow within the leading edge member. The hot bleed air is injected via an inlet arrangement into a forward hot air chamber defined by the outer skin of the leading edge member and the front spar. Subsequently, the hot air flow travels through a connecting passage opening from the forward hot air chamber through the front spar into the aft hot air chamber. Subsequently, the hot air flows along the entire spanwise length within the aft hot air chamber and splits into an exhaust flow and a recirculation flow. The recirculation flow passes through a recirculation opening and mixes with new hot bleed air, to take another round trip within the leading edge member.