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

Patent metadata

Field	Value
Publication number	US-12090741-B2
Application number	US-202016800286-A
Country	US
Kind code	B2
Filing date	Feb 25, 2020
Priority date	Aug 25, 2017
Publication date	Sep 17, 2024
Grant date	Sep 17, 2024

Abstract

A panel for a nacelle of an aircraft propulsion assembly includes two skins and a cell structure provided with transverse partitions defining cells. The cell structure includes folds with at least one central part forming at least one part of at least one transverse partition and at least one peripheral part extending along at least one of the skins. A nacelle with such a panel is provided, as well as a method for manufacturing such a panel.

First claim

The invention claimed is:

1. A panel for a nacelle of an aircraft propulsion assembly, comprising:
two skins;
a cellular structure between the two skins, the cellular structure comprising transverse partition walls delimiting cells;
fibrous folds each comprising:
a first peripheral portion extending along one of the two skins,
a pair of central portions extending transversely from opposing ends of the first peripheral portion so as to form at least one portion of a pair of the transverse partition walls, the pair of the transverse partition walls defining the same one of the cells, the pair of central portions having ends disposed at the other one of the skins, and
a pair of second peripheral portions extending from the ends of the pair of transverse partition walls toward each other and along the other one of the two skins, the pair of second peripheral portions being spaced apart from each other on the other one of the skins,

wherein at least some of the fibrous folds are integrally manufactured as a continuous structure during manufacturing of the fibrous folds such that the first and second peripheral portions of the at least some of the fibrous folds are continuously formed to define a plurality of openings corresponding to respective ones of the cells,
wherein the first peripheral portion has a main surface extending laterally from the pair of central portions and extending along and parallel to the one of the two skins and the pair of second peripheral portions each have a main surface extending laterally from one of the pair of central portions and extending along and parallel to the other one of the two skins.

2. The panel according to claim 1 , wherein for one or several of the fibrous folds at least one of the pair of central portions extends transversely from the one of the two skins to the other one of the two skins.

3. The panel according to claim 1 , wherein for one or several of the fibrous folds, the first peripheral portion extends along the one of the two skins so as to delimit at least one portion of at least one first cell.

4. The panel according to claim 1 , wherein for one or several fibrous folds the first peripheral portion extends along the one of the two skins so as to delimit at least one portion of at least one of the cells, and the pair of second peripheral portions extend 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.

5. The panel according to claim 1 , wherein the fibrous folds comprise fibers of a ceramic material.

6. The panel according to claim 1 , wherein the fibrous folds are textile folds.

7. A component of an exhaust nozzle or of a nacelle of an aircraft propulsion assembly, wherein the component comprises the panel according to claim 1 .

8. The panel according to claim 1 , wherein the fibrous folds form a one-piece component.

9. The panel according to claim 1 , wherein at least some of the fibrous folds are integrally manufactured by draping textile folds on a plurality of molds having a shape conforming to a shape of the plurality of cells, followed by extracting the plurality of molds.

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