公开(公告)号：US20200291896A1

公开(公告)日：2020-09-17

申请号：US16887501

申请日：2020-05-29

Applicant: Safran Nacelles

Inventor： Philippe BIENVENU ,  Olivier BONMARTEL ,  Aurélie SOULA ,  Thomas PERROTIN ,  Serge BELINY

IPC: F02K1/82 ,  B64C7/02 ,  B32B3/12 ,  F02C7/045

Abstract: An acoustic panel for an aircraft turbojet nacelle, of the type including an outer skin, an inner skin, and a cellular core which is interposed between the outer skin and the inner skin, includes a plurality of corrugated strips, each corrugated strip extending longitudinally in length while forming a succession of bosses and recesses, the corrugated strips arranged to delimit cells which extend globally perpendicularly to the skins. Each corrugated strip extends in width from a first end forming an outer folded edge, which bears on the outer skin, to a second end forming an inner folded edge, which bears on the inner skin.

公开(公告)号：US20200316701A1

公开(公告)日：2020-10-08

申请号：US16870391

申请日：2020-05-08

Applicant: Safran Nacelles

Inventor： Philippe BIENVENU ,  Aurélie SOULA ,  Thomas PERROTIN

IPC: B23K1/00 ,  B64D29/00 ,  B23K20/02 ,  B23K20/24

Abstract: A method and a device for manufacturing a structural and/or acoustic panel for a nacelle of an aircraft propulsion assembly involves heating, by producing electromagnetic radiation, at least one skin of the structural and/or acoustic panel in such a way as to assemble this skin with a cellular structure of the structural and/or acoustic panel, by diffusion brazing or welding. This heating device can also be used to shape the skin to the cellular structure prior to assembly.

公开(公告)号：US20220325681A1

公开(公告)日：2022-10-13

申请号：US17641383

申请日：2020-09-07

Applicant: SAFRAN NACELLES

Inventor： Tony MIOSSEC ,  Philippe BIENVENU ,  Emilie BEMONT

IPC: F02K1/82

Abstract: A structural and/or acoustic panel including an inner skin, an outer skin, a honeycomb structure and at least one sealing flange. The sealing flange has a U-shaped section directed toward the honeycomb structure and is clamped with the honeycomb structure between the inner and the outer skins. A method for manufacturing such a panel by soldering the component elements thereof is also disclosed.

公开(公告)号：US20190002131A1

公开(公告)日：2019-01-03

申请号：US16022910

申请日：2018-06-29

Applicant: Safran Nacelles

Inventor： Philippe BIENVENU ,  CHRISTOPHE CORNU ,  BOUALEM MERABET ,  DAVID DELAMOTTE ,  SERGE BELINY

IPC: B64F5/10 ,  B64D29/02 ,  B23K20/02

Abstract: A device and a method of assembly by brazing or diffusion-welding under a gaseous pressure is provided to make structures for a nacelle of an aircraft turbojet engine such as an inner fixed structure. Sealing of the assembly space inside which the parts to assemble are disposed is provided by tie members exerting a mechanical pressure on mold elements. The tie members include jaws made of a first material and a holding element made of a second material. The first material has a thermal expansion coefficient higher than that of the second material.

公开(公告)号：US20180066608A1

公开(公告)日：2018-03-08

申请号：US15810267

申请日：2017-11-13

Applicant: Safran Nacelles

Inventor： Philippe BIENVENU ,  Jean-Claude RIVOAL ,  Michel LEFEBVRE

IPC: F02K1/82 ,  B32B3/12 ,  B32B1/00 ,  B32B15/01 ,  B32B15/04

Abstract: The present disclosure relates to a composite panel having a sandwich structure formed by a central core having a primary cellular structure, for example, of the honeycomb type, sandwiched between two skins. The primary cellular structure includes an array of main cells. The composite panel further includes a plurality of pins, each pin being, on the one hand, arranged to be housed and to cooperate inside a main cell and, on the other hand, formed of a secondary cellular structure having an array of secondary cells.

公开(公告)号：US20170274466A1

公开(公告)日：2017-09-28

申请号：US15619968

申请日：2017-06-12

Applicant: SAFRAN NACELLES

Inventor： Philippe BIENVENU ,  Jean-Claude RIVOAL ,  Guillaume THERON

IPC: B23K3/08 ,  B23K1/00

CPC classification number: B23K3/087 ,  B23K1/0014 ,  B23K2101/02

Abstract: The present disclosure relates to a brazing tooling for the manufacture of a part, and in particular to a tooling adapted for brazing a set of metallic parts, in particular a composite panel, in an enclosure of a brazing furnace. The tooling includes a first mold element and a second mold element clasped together and a bearing device. The first and the second mold elements respectively include a first material and a second material, the first material having an expansion coefficient greater than the expansion coefficient of the material of the set of parts, and the second material having an expansion coefficient lower than the expansion coefficient of the material of the set of parts. At the brazing temperature, constraining of the set of parts between the bearing device of the first and second mold elements is provided.

公开(公告)号：US20170203378A1

公开(公告)日：2017-07-20

申请号：US15468138

申请日：2017-03-24

Applicant: SAFRAN NACELLES

Inventor： Philippe BIENVENU ,  Helene MALOT ,  Charlotte JULIENNE

IPC: B23K1/00 ,  F01D25/24 ,  B23K1/19 ,  B23K3/053 ,  B23K1/008

CPC classification number: B23K1/0018 ,  B23K1/0014 ,  B23K1/008 ,  B23K1/19 ,  B23K3/0471 ,  B23K3/053 ,  B23K2103/14 ,  F01D25/24 ,  F02K1/78 ,  F05D2230/237 ,  F05D2300/133

Abstract: The present disclosure relates to a method for producing a final metal part for a nacelle of a turbojet. The method includes brazing at least two parts, one being an inner part having an inner surface and the other being an outer part having an outer surface. The method further includes a step of heating the outer surface of the outer part using an external heating means, and a step of heating the inner surface of the inner part using an internal heating means.