公开(公告)号：US11325717B2

公开(公告)日：2022-05-10

申请号：US15730954

申请日：2017-10-12

Applicant: Airbus Operations SAS

Inventor： Alain Porte ,  Frédéric Vinches

IPC: B64D33/02 ,  B64C7/02 ,  F02C7/045 ,  B64D29/00

Abstract: An aircraft nacelle including a conduit rigidly connected to an air inlet and a conduit rigidly connected to an engine, a link between the conduit rigidly connected to the air inlet and the conduit rigidly connected to the engine. The link includes a sleeve that receives one end of a first conduit and is rigidly connected to a second conduit, and linking elements that link the sleeve and the first conduit and that are distributed about the entire circumference of the nacelle, each linking element having a threaded stem oriented in a radial direction and being configured to enable tightening from inside the first conduit.

公开(公告)号：US10273015B2

公开(公告)日：2019-04-30

申请号：US15280300

申请日：2016-09-29

Applicant: Airbus Operations SAS

Inventor： Thierry Surply ,  Alain Porte

IPC: B64D29/00 ,  B64D15/04 ,  B64D33/02 ,  F02C7/045 ,  F02C7/047

Abstract: An acoustic structure for an aircraft nacelle which comprises an acoustically resistive substructure, at least one layer of cells and a reflective layer. The acoustic structure comprises at least one single-piece substructure which divides up the layer of cells and which incorporates elongated elements of a de-icing system.

公开(公告)号：US09803547B2

公开(公告)日：2017-10-31

申请号：US14083524

申请日：2013-11-19

Applicant: Airbus Operations (SAS)

Inventor： Alain Porte ,  Franck Le Flem

IPC: F02C7/04 ,  B64D33/02

CPC classification number: F02C7/04 ,  B64D33/02 ,  B64D2033/0206 ,  B64D2033/0286 ,  F05D2250/71 ,  F05D2250/75 ,  F05D2260/30 ,  Y02T50/672

Abstract: An aircraft nacelle comprising a first duct secured to an air intake and a second duct secured to a power plant. The two ducts are arranged end-to-end and connected by a connection. The connection comprises a bracket which extends between a first region for connecting to the power plant and a second region for connecting to the air intake, and which comprises a J-shaped profile in longitudinal planes, having at least one curved portion offset towards the outside of the nacelle with respect to the connecting regions.

公开(公告)号：US20150191239A1

公开(公告)日：2015-07-09

申请号：US14575392

申请日：2014-12-18

Applicant: Airbus Operations (SAS)

Inventor： Alain Porte ,  Matthieu Fargues

IPC: B64C7/02 ,  F01D25/24 ,  F01D25/00

CPC classification number: F01D25/24 ,  B64D29/00 ,  B64D33/02 ,  B64D2033/0286 ,  F01D25/005

Abstract: An aircraft turbojet engine nacelle comprising an air intake assembly of substantially annular shape, the air intake assembly comprising an external wall and an internal wall which are connected to one another upstream by an air intake lip and downstream by an annular rear structure. The annular rear structure comprises, arranged concentrically, one or more monolithic panels forming a first annular zone and comprising one or more hollow casings forming at least a second annular zone, and at least one connecting ring which provides the connection with at least one of the external and internal walls. The annular rear structure thus has increased structural mechanical strength.

Abstract translation: 一种包括大致环形形状的进气组件的飞机涡轮喷气发动机机舱，所述进气组件包括外壁和内壁，所述外壁和内壁在进气口的上游彼此连接，并且通过环形后部结构在下游连接。 环形后部结构包括同心布置的一个或多个整体板，其形成第一环形区域并且包括形成至少第二环形区域的一个或多个中空壳体和至少一个连接环，该连接环提供与至少一个 外墙和内墙。 因此，环形后部结构具有增加的结构机械强度。

公开(公告)号：US20140144519A1

公开(公告)日：2014-05-29

申请号：US14086314

申请日：2013-11-21

Applicant: Airbus Operations (SAS)

Inventor： Alain Porte ,  Matthieu Fargues ,  Martial Marro

IPC: F02C7/04

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。

公开(公告)号：US08733501B2

公开(公告)日：2014-05-27

申请号：US13709300

申请日：2012-12-10

Applicant: Airbus Operations SAS

Inventor： Alain Porte ,  Nicolas Casse ,  Grégory Albet

IPC: E04B1/82

CPC classification number: F02K1/827 ,  B32B3/266 ,  B32B3/30 ,  B32B5/022 ,  B32B5/024 ,  B32B5/24 ,  B32B7/045 ,  B32B15/01 ,  B32B37/146 ,  B32B38/06 ,  B32B2307/10 ,  B32B2307/102 ,  B32B2605/00 ,  B32B2605/18 ,  B32B2607/00 ,  B64F5/00 ,  F02C7/045 ,  F02C7/047 ,  F05B2250/283 ,  F05D2250/22 ,  G10K11/172 ,  Y02T50/672 ,  Y10T29/4957

Abstract: A method for producing an acoustic treatment panel, including: assembling two plates, at least one of which is deformed so as to separate the plates locally in order to form cavities of a cellular structure between the two plates, said cavities being delimited by facets and partitions formed by at least one of the deformed plates, producing at least one opening on the facets of one of the two plates, and pressing an acoustically resistive plate against the surface of the cellular structure including the openings.

Abstract translation: 一种用于制造声学处理面板的方法，包括：组装两个板，其中至少一个被变形以局部分离板，以便在两个板之间形成多孔结构的空腔，所述空腔由小平面限定， 由至少一个变形的板形成的隔板，在两个板之一的小面上产生至少一个开口，并将隔音板压在包括开口的多孔结构的表面上。