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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.
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2.发明授权公开(公告)号：US11702213B2
公开(公告)日：2023-07-18
申请号：US16377813
申请日：2019-04-08
Applicant: Airbus Operations SAS
Inventor： Alain Porte , François Pons , Jonathan Carcone
CPC classification number: B64D15/22 , B64D15/12 , B64D15/20 , B64D29/00 , B64D33/02 , F02C7/047 , H05B1/0236 , H05B3/0019 , B64D2033/0233
Abstract: An aircraft engine nacelle comprising an icing protection system and an icing protection method for such an aircraft engine nacelle. The aircraft engine nacelle comprises an air inlet comprising a lip, a tubular air inlet piece and an icing protection system. The icing protection system comprises an icing prevention means powered continuously by a first electrical energy source and wholly or partly covering the lip, a de-icing means powered by a second electrical energy source covering the tubular air inlet piece and a controller configured to acquire a current total air temperature value, and control the second electrical energy source as a function of the current total air temperature value.
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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
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.
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公开(公告)号：US11952136B2
公开(公告)日：2024-04-09
申请号：US17387529
申请日：2021-07-28
Applicant: Airbus Operations SAS
Inventor： Alain Porte , Jacques Lalane , Florian Ravise , Franck Dobigeon
CPC classification number: B64D29/00 , B29D99/0021 , F02C7/045 , F02C7/24 , F02K1/827 , G10K11/162 , B29L2031/3076
Abstract: An acoustic panel comprising a cellular structure, such as a honeycomb structure, having cells that open at least onto a first frontal face of the structure. The panel comprises a capsular skin which is fastened to the first frontal face of the cellular structure next to a plurality of cells. The capsular skin including a continuous layer of material, in one piece, forming capsules that extend into the cellular structure. At least one channel is provided at the apex of each capsule for the passage of acoustic waves. Such a panel effectively attenuates the noise of aircraft engines, in particular, the low frequencies. It is extremely easy to manufacture industrially, the capsular skin being able to be obtained by molding with polymerization in situ, the polymerizable material then adhering to the cellular structure while it polymerizes.
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公开(公告)号：US11655045B2
公开(公告)日：2023-05-23
申请号：US16990260
申请日：2020-08-11
Applicant: Airbus Operations SAS
Inventor： Alain Porte , Jacques Lalane , Frédéric Vinches , Franck Dobigeon
IPC: B64D29/06
CPC classification number: B64D29/06
Abstract: An anterior part of an aircraft propulsion assembly nacelle, having an air intake lip disposed at a front end and an outer panel, of which an outer face extends an outer part of the air intake lip. A front edge of the outer panel and a rear edge of the air intake lip are shaped so as to overlap radially and to nest so as to ensure a continuous surface between the outer surface of the outer part of the air intake lip and the outer face of the outer panel. Moreover, the front edge of the outer panel is connected to the rear edge of the air intake lip with no added rigid element. This permits a rigid connection while avoiding creating local irregularities on the outer surface of the nacelle, which irregularities might disrupt the flow of air around the nacelle, giving rise to additional drag.
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Patent Agency Ranking
公开(公告)号：US11649062B2
公开(公告)日：2023-05-16
申请号：US16654119
申请日：2019-10-16
Applicant: Airbus Operations SAS
Inventor： Alain Porte , Jacques Lalane , Julien Sentier
CPC classification number: B64D33/02 , B64D29/06 , B64D2033/0206
Abstract: A forward part of an aircraft propulsion unit nacelle, comprising an air intake lip, an acoustic panel, and a rigid connection between the acoustic panel and the air intake lip. The acoustic panel has a resistive surface and a back skin, and the rigid connection is formed between the air intake lip and the back skin of the acoustic panel to form a propagation path for forces between the air intake lip and the back skin. This configuration gives freedom from design constraints, which enables an increase in the acoustic treatment region toward the front of the nacelle. An aircraft propulsion unit comprising a nacelle having such a forward part is also provided.
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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
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.
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公开(公告)号：US11220343B2
公开(公告)日：2022-01-11
申请号：US16156272
申请日：2018-10-10
Applicant: Airbus Operations SAS
Inventor： Alain Porte , Jonathan Carcone
Abstract: A frost protection system for an aircraft engine nacelle, the nacelle comprising an inner shroud provided with at least one acoustic panel and an air intake lip forming a leading edge of the nacelle. The protection system comprises a heat exchanger device including at least one heat pipe configured to transfer heat emitted by a heat source to the at least one acoustic panel.
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公开(公告)号：US20170096238A1
公开(公告)日：2017-04-06
申请号：US15280130
申请日：2016-09-29
Applicant: Airbus Operations SAS
Inventor： Alain Porte , Jean Michel Rogero
CPC classification number: B64D45/00 , B64C7/02 , B64D27/18 , B64D29/02 , B64D2045/009 , F01D19/00 , F01D25/24 , F02C7/25 , F02K3/06 , F05D2220/323 , F05D2250/36 , F05D2250/71 , Y02T50/671
Abstract: A propulsion system comprising a nacelle substantially tubular around a longitudinal axis, having an inner wall extending from a front to a rear of the nacelle and by an outer wall, external of the inner wall, extending from the front to the rear of the nacelle, a turbojet comprising a fan and situated internally of the inner wall of the nacelle, at least one tank containing an extinguishing fluid, and a network of pipes hydraulically connected to the tank. The propulsion system comprises each tank being located in the nacelle, around the inner wall and internally of the outer wall. Such a propulsion system makes it possible to shift the one or more tanks, which no longer occupy the space at the mast, and makes it possible to carry a large volume of extinguishing fluid so as to be able to accommodate future regulations.
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10.发明授权Aircraft nacelle comprising a reinforced connection between an air intake and a powerplant 有权飞机机舱包括进气口和动力装置之间的加强连接公开(公告)号：US09567905B2
公开(公告)日：2017-02-14
申请号：US14086314
申请日：2013-11-21
Applicant: Airbus Operations (SAS)
Inventor： Alain Porte , Matthieu Fargues , Martial Marro
CPC classification number: F02C7/04 , B64D33/02 , B64D2033/0286 , F01D21/045 , F01D25/243 , F05D2260/96 , F05D2300/603 , Y02T50/672 , Y10T137/0536
Abstract: An aircraft nacelle comprising a first duct secured to an air intake and a second duct secured to a powerplant, the first duct comprising an exterior surface and an end portion connected to the second duct. The nacelle includes a hollow section piece in contact with the exterior surface of the first duct which extends over at least part of the circumference of that end portion of the first duct that is connected to the second duct.
Abstract translation: 包括固定到进气口的第一管道和固定到动力装置的第二管道的飞机机舱，所述第一管道包括外表面和连接到第二管道的端部。 所述机舱包括与所述第一管道的外表面接触的中空部件，所述中空部件在与所述第二管道连接的所述第一管道的所述端部的所述圆周的至少一部分上延伸。
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