Abradable coating having a honeycomb structure made of composite material having a ceramic matrix made of short fibers

Patent metadata

Field	Value
Publication number	US-2024262756-A1
Application number	US-202218568587-A
Country	US
Kind code	A1
Filing date	Jun 6, 2022
Priority date	Jun 15, 2021
Publication date	Aug 8, 2024
Grant date	—

Abstract

An abradable coating includes a tubular cell structure, wherein the the tubular cell structure includes a fibrous reinforcement of discontinuous short fibers which is densified by a ceramic matrix.

First claim

1 . An abradable coating comprising a tubular cell structure, wherein the tubular cell structure comprises a fibrous reinforcement of discontinuous short fibers which is densified by a ceramic matrix, the discontinuous short fibers having a length comprised between 50 μm and 500 μm.

2 . The abradable coating according to claim 1 , wherein a volume ratio of discontinuous short fibers is comprised between 10% and 25% of a volume of the tubular cell structure.

3 . The abradable coating according to claim 1 , wherein the tubular cells are honeycomb-shaped.

4 . A method for manufacturing an abradable coating according to claim 1 comprising:
obtaining an assembly comprising a first preform of the tubular cell structure mounted on a second preform or on a turbomachine component, the first preform comprising a fibrous reinforcement of discontinuous short fibers and the second preform or the turbomachine component comprising a fibrous reinforcement of continuous fibers, and
densifying the first preform of the assembly by infiltration with a molten composition comprising silicon.

5 . The method for manufacturing an abradable coating according to claim 4 , wherein the first preform is mounted on the second preform and wherein there is a co-densification of the first and second preforms by the molten composition.

6 . The method for manufacturing an abradable coating according to claim 4 , wherein the first preform is mounted on the turbomachine component and wherein the molten composition makes it possible to weld the tubular cell structure to the component.

7 . The method for manufacturing an abradable coating according to claim 6 , wherein the first preform is mounted on an abradable track of the turbomachine component.

8 . The method for manufacturing an abradable coating according to claim 4 , wherein obtaining the assembly comprises obtaining the first preform, by additive manufacturing or by powder injection molding, from a mixture present in a binder and comprising a matrix powder and discontinuous short fibers.

9 . The method for manufacturing an abradable coating according to claim 4 wherein, the second preform is a preform of first-stage ring of a low-pressure turbomachine or the turbomachine component is a first-stage ring of a low-pressure turbomachine.

10 . The method for manufacturing an abradable coating according to claim 4 wherein, the second preform is a preform of a turbomachine stator or the turbomachine component is a turbomachine stator placed facing wipers located on a rotor opposite the stator.

Assignees

• Safran Aircraft Engines
• Safran Ceram

Inventors

• Jarrossay Clément
• Gaillard Aurélien
• Richard Yann

Classifications

• F05D2300/611

  Coating · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F05D2250/283

  honeycomb · CPC title

• F05D2230/20

  essentially without removing material · CPC title

• F01D11/127 Primary

  with a deformable or crushable structure, e.g. honeycomb · CPC title