Acoustic attenuation panel for an aircraft jet engine nacelle

Patent metadata

Field	Value
Publication number	US-11719192-B2
Application number	US-202017103424-A
Country	US
Kind code	B2
Filing date	Nov 24, 2020
Priority date	May 24, 2018
Publication date	Aug 8, 2023
Grant date	Aug 8, 2023

Abstract

The present disclosure concerns an acoustic attenuation panel for an aircraft turbojet engine nacelle and a method for manufacturing this panel. The acoustic attenuation panel includes an alveolar central core interposed between an acoustic front skin comprising perforations and a rear skin, the acoustic attenuation panel including a front structure and a rear structure. The front structure includes the acoustic front skin and a first network of alveolar walls, the rear structure including the rear skin and a second network of alveolar walls, the first and second networks of alveolar walls being complementary so as to form, in an assembled position, the alveolar central core, the front structure and the rear structure being positioned opposite to each other and so that the network of alveolar walls of a structure is spaced from the skin of the other structure facing it by a clearance d.

First claim

What is claimed is:

1. An acoustic attenuation panel for an aircraft turbojet engine nacelle, the acoustic attenuation panel including an alveolar central core interposed between an acoustic front skin comprising perforations and a rear skin, the acoustic attenuation panel including a front structure and a rear structure,
wherein:
the front structure includes the acoustic front skin and a first network of alveolar walls, the rear structure including the rear skin and a second network of alveolar walls, the front and rear structures each comprising a peripheral border, said border of the front and rear structures being fastened to each other for assembly of the front and rear structures, the first and second networks of alveolar walls being complementary so as to form, in an assembled position, the alveolar central core, the front structure and the rear structure being positioned opposite to each other and so that the first and second networks of alveolar walls are spaced from the front and rear skins by a clearance d.

2. The acoustic attenuation panel according to claim 1 , wherein the clearance d is less than 2 mm.

3. The acoustic attenuation panel according to claim 2 , wherein the clearance d is than 1.5 mm.

4. The acoustic attenuation panel according to claim 1 , wherein each of the first and second networks of alveolar walls is formed of walls protruding on a respective inner surface of the front and rear skin, notches being provided on the alveolar walls, the notches being arranged to be inserted, in a complementary manner, into the notches of other alveolar walls, allowing the nesting of the first network of alveolar walls of the front structure into the second network of alveolar walls of the rear structure.

5. The acoustic attenuation panel according to claim 1 , wherein the networks of alveolar walls each comprise walls of a frusto-conical section overlapping relative to each other to allow the nesting of the first network of alveolar walls of the front structure into the second network of alveolar walls of the rear structure.

6. The acoustic attenuation panel according to claim 1 , whereinafter assembly, the rear structure has alveolar patterns offset by a half-period relative to alveolar patterns of the front structure.

7. A thrust reverser flap for an aircraft turbojet engine nacelle wherein the thrust reverser flap is formed of an acoustic attenuation panel according to claim 1 .

8. A method for manufacturing an acoustic attenuation panel for an aircraft turbojet engine nacelle according to claim 1 , wherein the method comprises:
obtaining the front structure including the acoustic front skin and the first network of alveolar walls;
obtaining the rear structure including the rear skin and the second network of alveolar walls; and
assembling the front structure to the rear structure to form the acoustic attenuation panel, the front and rear structures each comprising the peripheral border, said borders being fastened to each other for assembly of the front and rear structures, the first and second networks of alveolar walls cooperating together so as to form an alveolar central core positioned between the acoustic front skin and the rear skin, the front structure and the rear structure being positioned opposite to each other and so that the network of alveolar walls is spaced by the clearance d.

9. The manufacturing method according to claim 8 , wherein during the assembling, the first network of alveolar walls of the front structure is nested into the second network of alveolar walls of the rear structure.

10. The manufacturing method according to claim 9 , wherein during the assembling, the first network of alveolar walls of the front structure is nested into the second network of alveolar walls of the rear structure by notches.

11. The manufacturing method according to claim 8 , wherein, during the assembling, the front and rear structures are fastened to each other only at peripheral borders respectively provided on each of the front and rear structures.

Assignees

• Safran Nacelles

Inventors

• Le Boulicaut Loïc Hervé André
• Thorel Christophe
• Verger Simon
• Preau Mathieu

Classifications

• F02K1/827 Primary

  Sound absorbing structures or liners · CPC title

• B64C7/02

  Nacelles · CPC title

• B64D33/06

  Silencing exhaust or propulsion jets · CPC title

• F02C7/24

  Heat or noise insulation (air intakes having provisions for noise suppression F02C7/045; turbine exhaust heads, chambers, or the like F01D25/30; silencing nozzles of jet-propulsion plants F02K1/00) · CPC title

• F05D2260/963

  by Helmholtz resonators · CPC title