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：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.