Aircraft turbomachine casing and method of manufacturing same

Patent metadata

Field	Value
Publication number	US-12129761-B2
Application number	US-202117795511-A
Country	US
Kind code	B2
Filing date	Jan 26, 2021
Priority date	Jan 29, 2020
Publication date	Oct 29, 2024
Grant date	Oct 29, 2024

Abstract

A casing of an aircraft turbomachine includes an annular shell extending around an axis A and made of a composite material having fibers that which are woven and embedded in a resin. An annular layer made of abradable material extends inside the shell, around axis A and is obtained by spreading and polymerizing a paste. Support panels extend around axis A and are interposed between the shell and the abradable layer.

First claim

The invention claimed is:

1. A method for manufacturing an aircraft turbomachine casing, this casing comprising:
an annular envelope extending around an axis A and made of a composite material comprising fibers which are woven and embedded in a resin,
an annular layer of abradable material extending inside the envelope, and
support panels extending around the axis A and interposed between the envelope and the abradable layer,
wherein the method comprises the steps of:
a) preparing a paste by mixing at least two components,
b) depositing the paste on an internal annular surface of the panels,
c) spreading the paste by means of at least one roll extending parallel to the axis A and configured to roll on guide annulus arranged on either side of the panels or of the envelope, coaxially thereto, so as to form an angular sector of the abradable layer which extends over a predetermined angle about the axis A,
d) forming a chamfer at a circumferential end of the sector thus formed,
e) and repeating the steps a) to d) until a plurality of consecutive angular sectors of the abradable layer are formed and cover the entire internal surface of the panels, the sectors formed in the step e) each comprising a circumferential end covering the chamfered circumferential end of the previously deposited sector.

2. The method according to claim 1 , wherein the paste is based on epoxy resin.

3. The method according to claim 1 , wherein the mixing is done in the step a) by incorporating the components into a pot of a machine that comprises at least one rotating mixing element along two non-parallel axes (X, Y) of rotation.

4. The method according to claim 3 , wherein the rotating element rotates about said axes at a speed of between 4400 and 1000 rpm and for a time of between 50 and 200 seconds.

5. The method according to claim 4 , wherein said pot comprises a bottom extractable from the inside to the outside of the pot so as to facilitate the removal of the paste from the pot.

6. The method according to claim 1 , wherein the paste deposited in the step b) has a mass of between 400 and 2600 g.

7. The method according to claim 1 , wherein the casing is positioned so that the axis A is horizontal during the steps b) to e).

8. The method according to claim 7 , wherein the casing is rotated about the axis A during the step c) or during each step c).

9. The method according to claim 1 , wherein the paste is deposited in the step b) in the form of a string or a ball.

10. The method according to claim 1 , wherein the abradable layer has a thickness of between 3 and 10 mm.

11. The method according to claim 1 , further comprising between the steps b) and c) and/or between the steps c) and d), a step i) of scraping the paste or the sector by means of a blade.

12. The method according to claim 1 , wherein a plastic film is interposed between said at least one roll and the paste during the step c).

13. The method according to claim 1 , wherein said at least one roll used in the step c) has a non-cylindrical profiled shape.

14. The method according to claim 1 , wherein the guide annulus in the step c) are solicited axially towards each other and into abutment against the panels by elastic bands extending between the guide annulus.

15. The method according to claim 1 , wherein the chamfer formed in the step d) extends along the entire axial dimension of the sector and is oriented at 45° to a normal to the internal surface of that sector.

Assignees

• Safran Aircraft Engines
• Safran Aerospace Composites

Inventors

• Roberts Meredith
• Anderson Chris
• Broussais-Colella Nicolas François Paul
• Malfroy Ambroise Nicolas Marie
• Maxwell Foster Alexander
• Myslinski Paul
• Retiveau-Leca Adrienne

Classifications

• B05D7/22

  to internal surfaces, e.g. of tubes · CPC title

• B05D3/12

  by mechanical means · CPC title

• B05D1/40

  Distributing applied liquids or other fluent materials by members moving relatively to surface · CPC title

• F05D2230/31

  Layer deposition · CPC title

• B05C17/10

  Hand tools for removing partially or for spreading or redistributing applied liquids or other fluent materials, e.g. colour touchers · CPC title