公开(公告)号：US12030659B2

公开(公告)日：2024-07-09

申请号：US16990214

申请日：2020-08-11

Applicant: Airbus Operations SAS

Inventor： Alain Porte ,  Jacques Lalane ,  Frédéric Vinches ,  Gregory Albet

IPC: B64D33/02

CPC classification number: B64D33/02 ,  B64D2033/0206

Abstract: An anterior part of a nacelle of an aircraft propulsion assembly, which comprises an air intake lip, an outer panel extending an outer part of the air intake lip, an inner structure extending an inner part of the air intake lip, a front frame connecting the outer wall to the air intake lip or to the inner structure. The outer panel and the outer part of the air intake lip together form an outer wall of the anterior part. The front frame and the outer wall are connected to one another by assembly means located inside the anterior part. The anterior part constituted in this manner ensures laminar flow of the air on an outer surface of the anterior part and reduces drag. A nacelle of a propulsion unit, comprising an anterior part of this kind is also provided.

公开(公告)号：US11161620B2

公开(公告)日：2021-11-02

申请号：US16364888

申请日：2019-03-26

Applicant: Airbus Operations SAS

Inventor： Alain Porte ,  François Pons ,  Gregory Albet

IPC: B64D29/06 ,  B64D29/08 ,  B64C7/02

Abstract: An aircraft nacelle comprising an air inlet, with a single fan cowling made of a single piece which extends over all the circumference of the fan. The fan cowling is borne by the air inlet and is mounted to be rotationally mobile about the axis of the nacelle relative to the air inlet, via a link and guiding arrangement comprising a circular rail and a runner capable of sliding along the circular rail. The fan cowling comprises one or more openings closed by hatches allowing access to the interior of the nacelle. The fan cowling has little susceptibility to being deformed both in flight and on the ground during maintenance operations. Furthermore, no pylon portion is needed in the zone of the fan cowling since the latter is not attached to the pylon.

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：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：US11643216B2

公开(公告)日：2023-05-09

申请号：US16655406

申请日：2019-10-17

Applicant: Airbus Operations SAS

Inventor： Alain Porte ,  François Pons ,  Gregory Albet ,  Maxime Zebian

IPC: B64D15/04 ,  B64D29/00 ,  B64D33/02 ,  F02C7/047 ,  F01D25/02

CPC classification number: B64D15/04 ,  B64D29/00 ,  B64D33/02 ,  F01D25/02 ,  F02C7/047 ,  B64D2033/0233

Abstract: An anti-icing protection system for an aircraft engine nacelle, the nacelle comprising an inner shroud, 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 inner shroud.