公开(公告)号：US11518526B2

公开(公告)日：2022-12-06

申请号：US16655387

申请日：2019-10-17

Applicant: Airbus Operations SAS

Inventor： Alain Porte ,  Jacques Lalane ,  Gregory Albet ,  Maxime Zebian ,  Arnaud Bourhis

IPC: B64D15/04 ,  B64D29/00 ,  B64D33/02

Abstract: An anti-icing protection system for an aircraft engine nacelle, the nacelle comprising an inner shroud provided with at least one acoustic panel, an air intake lip forming a leading edge of the nacelle, the protection system comprising a heat exchanger device including at least one heat pipe configured to transfer heat emitted by a heat source to the acoustic panel or panels.

公开(公告)号：US11643967B2

公开(公告)日：2023-05-09

申请号：US17684667

申请日：2022-03-02

Applicant: Airbus Operations SAS

Inventor： Arnaud Bourhis ,  Gregory Albet ,  Alain Porte

IPC: F02C7/047 ,  F02C7/24

CPC classification number: F02C7/047 ,  F02C7/24 ,  F05D2260/96

Abstract: An optimized protection against ice on the inner and outer faces of an aircraft engine nacelle air intake with the air intake including an outer face and an inner face meeting at a line at the longitudinally extreme, called extremum line, an acoustic panel being installed on the inner surface of a part of the inner face. An elimination system based on vibration of the ice formed is put in place on at least a part of the outer face and an ice formation prevention system using a hot fluid is put in place on at least a part of the inner face and either an ice elimination system or an ice formation prevention system using a hot fluid is installed on the inner face and on the outer face, a marking line marking the boundary between the two systems.

公开(公告)号：US11407522B2

公开(公告)日：2022-08-09

申请号：US17017482

申请日：2020-09-10

Applicant: Airbus Operations SAS

Inventor： Arnaud Bourhis ,  Gregory Albet ,  François Pons

IPC: B64D33/02 ,  B64D15/04 ,  F02C7/045 ,  F02C7/047

Abstract: An air inlet for an aircraft nacelle, including a lip and a front frame, which together form a duct with D-shaped section receiving hot air. The front frame is arranged in an advanced position inside the lip. The lip has de-icing grooves, which communicate with the duct and extend essentially downstream of the front frame. Downstream of the front frame, outside of the de-icing grooves, the lip has perforated zones provided with sound absorption holes. The air inlet includes a foil, which hermetically seals the de-icing grooves and is provided with sound absorption holes facing the perforated zones. The air inlet comprises acoustic panels inside the lip downstream of the front frame. The advanced position of the front frame, due to the de-icing grooves which ensure the de-icing of the lip downstream of the front frame, allows the acoustic treatment surface of the air inlet to be increased.

公开(公告)号：US12163469B2

公开(公告)日：2024-12-10

申请号：US17979023

申请日：2022-11-02

Applicant: Airbus Operations SAS

Inventor： Arnaud Bourhis ,  Florian Ravise ,  Maxime Zebian

IPC: F02C7/045 ,  F02C7/24 ,  B32B3/12 ,  B64D33/02

Abstract: A module ensuring an acoustic attenuation of a flow of a first fluid and a heat exchange between the first fluid and a second fluid. The module comprises a perforated first wall with a cutout, a second wall, a cellular structure extending from the second wall to the first wall, a recess provided in the cellular structure between a perforated bottom and a perforated top, and a heat exchanger which is fixed inside the recess between the bottom and the top and in which the second fluid circulates. Such a module ensures an attenuation of sound waves and a heat exchange without limiting the attenuation surface.