Structural and/or acoustic panel of a nacelle of an aircraft propulsion assembly and related manufacturing method

Patent metadata

Field	Value
Publication number	US-2024391206-A1
Application number	US-202418795709-A
Country	US
Kind code	A1
Filing date	Aug 6, 2024
Priority date	Aug 25, 2017
Publication date	Nov 28, 2024
Grant date	—

Abstract

A method for manufacturing a panel for a nacelle of an aircraft propulsion assembly includes: preparing mold elements each including lateral faces, an upper face, and a lower face; draping a material on a portion of the upper face and/or the lower face and at least one of the lateral faces of each of the mold elements to form at least one fold; and extracting the mold elements such that the at least one fold forms a cellular structure of the panel. The portion of the material on the upper face and/or the lower face forms a peripheral portion of the fold. The portion on the at least one of the lateral faces of each of the mold elements forms a central portion of the fold. The central portion is a portion of transverse partition walls of the panel, which define a plurality of cells.

First claim

What is claimed is:

1 . A method for manufacturing a panel for a nacelle of an aircraft propulsion assembly, the pane comprising two skins and a cellular structure between the two skins, the cellular structure comprising transverse partition walls delimiting cells, the method comprising a draping step wherein at least one fold is placed on at least one polyhedral mold element, the at least one mold element comprising lateral faces, an upper face and a lower face, during the draping step:
a central portion of the at least one fold is disposed on at least one portion of at least one of the lateral faces of the at least one polyhedral mold element, a peripheral portion of the at least one fold is disposed on at least one portion of the upper and/or lower face of the at least one polyhedral mold element, and wherein the method comprises an extraction step of the at least one polyhedral mold element so as to define at least one cell, the central portion of the at least one fold forming at least one portion of at least one of the transverse partition walls of the panel, the peripheral portion of the at least one fold extending along at least one of the two skins of the panel.

2 . The method according to claim 1 , wherein the method further comprises a manufacturing step of the at least one polyhedral mold element in a fugitive material, and wherein the extraction step comprises a heat and/or chemical treatment step arranged to eliminate the fugitive material.

3 . The method according to claim 1 , wherein for one or several folds the at least one central portion extends transversely from one of the two skins to the other one of the two skins.

4 . The method according to claim 1 , wherein one or several folds each comprise at least one first peripheral portion extending along one of the two skins and at least one second peripheral portion extending along the other one of the two skins.

5 . The method according to claim 4 , wherein for one or several folds, the at least one first peripheral portion extends along one of the two skins so as to delimit at least one portion of at least one first cell, and in that the at least one second peripheral portion extends along the other one of the two skins so as to delimit at least one portion of at least one second cell adjacent to the at least one first cell.

6 . The method according to claim 4 , wherein for one or several folds the at least one first peripheral portion extends along one of the two skins so as to delimit at least one portion of at least one of the cells, and in that the at least one second peripheral portion extends along the other one of the two skins so as to delimit at least one portion of the same at least one of the cells.

7 . The method according to claim 1 , wherein one or several folds each comprise a first central portion extending transversely so as to form at least one portion of at least one first transverse partition wall of at least one of the cells and a second central portion extending transversely so as to form at least one portion of at least one second transverse partition wall of the same at least one of the cells.

8 . The method according to claim 1 , wherein for one or several folds, the at least one central portion extends longitudinally so as to form at least one portion of several adjacent transverse partition walls.

9 . The method according to claim 1 , wherein the folds are fibrous folds comprising fibers of a ceramic material.

10 . The method according to claim 1 , wherein the folds are textile folds.

11 . A method for manufacturing a panel for a nacelle of an aircraft propulsion assembly, the method comprising:
preparing a plurality of mold elements each including a plurality of lateral faces, an upper face, and a lower face; draping a material on a portion of at least one of the upper face and the lower face and at least one of the plurality of lateral faces of each of the mold elements to form at least one fold; and extracting the plurality of mold elements such that the at least one fold forms a cellular structure of the panel, wherein the portion of the material on the at least one of the upper face and the lower face in the draping step forms a peripheral portion of the fold, the portion on the at least one of the plurality of lateral faces of each of the mold elements in the draping step forms a central portion of the fold, the central portion being a portion of a plurality of transverse partition walls of the panel, the plurality of transverse partition walls defining a plurality of cells.

12 . The method according to claim 11 , further comprising assembling at least one skin on one of opposing ends of the central portion to form the panel.

13 . The method according to claim 11 , further comprising assembling an upper skin and a lower skin on opposing ends of the central portion to form the panel.

14 . The method according to claim 13 , wherein the peripheral portion overlaps at least one of the upper skin and the lower skin.

15 . The method according to claim 11 , wherein the material is a fibrous material.

16 . The method according to claim 11 , wherein the plurality of mold elements are made of a fugitive material.

17 . The method according to claim 11 , further comprising positioning the plurality of mold elements according to positions of the cells of the cellular structure to be formed in the draping step.

18 . The method according to claim 11 , wherein the plurality of mold elements are connected by a plurality of channels.

19 . The method according to claim 11 , wherein the extracting the plurality of mold elements comprising heating or chemically treating the mold elements to eliminate the mold elements.

20 . The method according to claim 11 , wherein each of the mold elements is a polyhedral mold.

Assignees

• Safran Nacelles
• Safran Ceram

Inventors

• Desjoyeaux Bertrand
• Silva De Vasconcellos Davi
• Bouillon Florent
• Delehouze Arnaud

Classifications

• B32B2605/18

  Aircraft · CPC title

• B32B2307/102

  Insulating · CPC title

• B32B2262/105

  Ceramic fibres · CPC title

• B32B2250/03

  3 layers · CPC title

• B32B3/12

  characterised by a layer of regularly- arranged cells, e.g. a honeycomb structure · CPC title