Device for attaching an air inlet onto a fan casing of an aircraft turbojet nacelle

Patent metadata

Field	Value
Publication number	US-10415472-B2
Application number	US-201715459014-A
Country	US
Kind code	B2
Filing date	Mar 15, 2017
Priority date	Sep 18, 2014
Publication date	Sep 17, 2019
Grant date	Sep 17, 2019

Abstract

A device for fastening a downstream end of an air inlet on a fan casing of an aircraft turbojet engine nacelle is provided. The device includes an acoustic shroud, a first flange coupled to the fan casing, a second L-shaped flange having a base coupled to the acoustic shroud, and a collar linked to the first flange. The acoustic shroud extends from an upstream segment to a downstream segment which defines an inner skin and an outer skin that encloses an acoustic panel. The collar further includes a protrusion that extends from the outer skin to the downstream segment.

First claim

What is claimed is:

1. A device for fastening a downstream end of an air inlet on a fan casing of an aircraft turbojet engine nacelle wherein the downstream end comprises an acoustic shroud having an annular shape, the acoustic shroud extending axially from an upstream point to a downstream point along a longitudinal axis and delimited radially by an inner skin and an outer skin enclosing an acoustic panel, the device comprising:
a first flange coupled to the fan casing;
a second L-shaped flange having a base coupled to the acoustic shroud and a collar linked to the first flange; and
a protrusion, wherein the protrusion extends longitudinally from an upstream segment to a downstream segment, wherein the upstream segment is fixed to the acoustic shroud and the downstream segment delimits a radial space with the acoustic shroud, and
wherein the protrusion is adapted to be fastened on the base of the second L-shaped flange by fastening means.

2. The device according to claim 1 , wherein the protrusion is in a shape of an annular ring.

3. The device according to claim 1 , wherein the acoustic panel of the acoustic shroud extends continuously from the upstream segment to the downstream segment of the protrusion.

4. The device according to claim 1 , wherein the second L-shaped flange comprises a metallic material.

5. The device according to claim 1 , wherein the second L-shaped flange includes a plurality of independent portions arranged annularly along the longitudinal axis of the acoustic shroud.

6. The device according to claim 1 , wherein the protrusion comprises a composite material.

7. The device according to claim 1 , wherein the protrusion comprises a wave shape that draws an alternation of hollows and bumps distributed about the longitudinal axis of the acoustic shroud, said bumps each forming a radial overthickness designed to promote fastening of the second L-shaped flange on the protrusion.

8. The device according to claim 1 , wherein the acoustic panel extends longitudinally downstream beyond the plane of the second L-shaped flange.

9. The device according to claim 1 , wherein the device further comprises a corner disposed radially between the outer skin and the downstream segment of the protrusion.

10. The device according to claim 1 , wherein the fastening means includes a plurality of metal links configured to connect the downstream segment of the protrusion to the base of the second L-shaped flange.

11. The device according to claim 1 , wherein the protrusion is integral with the outer skin of the acoustic shroud.

Assignees

• Safran Nacelles

Inventors

• Desjoyeaux Bertrand
• Verger Simon
• Sentis Sylvain

Classifications

• F05D2230/53

  by integrally manufacturing a component, e.g. by milling from a billet or one piece construction · CPC title

• F05D2300/133

  Titanium · CPC title

• B64D29/06

  Attaching of nacelles, fairings or cowlings · CPC title

• F01D25/243

  Flange connections; Bolting arrangements (F01D25/265 takes precedence) · CPC title

• F05D2300/121

  Aluminium · CPC title