Method for manufacturing a ceramic matrix composite part

Patent metadata

Field	Value
Publication number	US-11958784-B2
Application number	US-202118257029-A
Country	US
Kind code	B2
Filing date	Dec 8, 2021
Priority date	Dec 18, 2020
Publication date	Apr 16, 2024
Grant date	Apr 16, 2024

Abstract

A method for manufacturing a turbomachine blade made of ceramic matrix composite component includes at least a structural part and a functional part secured to the structural part, the method including obtaining an assembly including a first preform of the functional part that is mounted on a second preform of the structural part or on the structural part, the first preform including a fibrous reinforcement of short fibres, and the second preform or the structural part comprising a woven fibrous reinforcement, and densification of the first preform of the assembly by infiltration with a molten composition.

First claim

The invention claimed is:

1. A method for manufacturing a turbomachine blade made of ceramic matrix composite material, comprising at least a structural part and a functional part secured to the structural part, the functional part comprising three functional portions: a downstream wall, an upstream wall and a root platform of the blade and the structural part comprising a lower platform distinct from the root platform and the method comprising:
obtaining an assembly comprising a first preform of the functional part that is mounted on a second preform of the structural part or on the structural part, the first preform comprising a fibrous reinforcement of short fibres having a length between 50 μm and 5000 μm, and the second preform or the structural part comprising a woven fibrous reinforcement, and
densification of at least the first preform of the assembly by infiltration with a molten composition.

2. The manufacturing method according to claim 1 , 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.

3. The manufacturing method according to claim 1 , wherein the first preform is mounted on the structural part and wherein the molten composition solders the functional part to the structural part.

4. The manufacturing method according to claim 1 , wherein obtaining the assembly further comprises forming the first preform, said forming comprising of forming a first blank comprising the fibrous reinforcement of short fibres present in a binder, debonding the first blank and compacting the first debonded blank so as to obtain the first preform.

5. The manufacturing method according to claim 4 , wherein the first blank further comprises first additional fillers present in the binder and distinct from the short fibres of the reinforcement, the first additional fillers having a metallic or ceramic surface.

6. The manufacturing method according to claim 5 , wherein a consolidation of the first preform is carried out by sintering the first additional fillers before the densification.

7. The manufacturing method according to claim 1 , wherein the first preform is mounted on the second preform and obtaining the assembly comprises forming a second blank comprising the woven fibrous reinforcement, so as to obtain the second preform.

8. The manufacturing method according to claim 7 , wherein the second blank further comprises second additional fillers having a metal or ceramic surface.

9. The manufacturing method according to claim 8 , wherein a consolidation of the second preform is carried out by sintering the second additional fillers before densification.

10. The manufacturing method according to claim 1 , wherein the root platform closes a cavity in which a blade root is located and creates a pressure chamber.

11. The manufacturing method according to claim 1 , wherein the root platform is located radially inside with respect to the lower platform.

Assignees

• Safran Ceram

Inventors

• Delehouze Arnaud
• Bouillon Eric
• Garnier Gildas
• Roussille Clément Marie Benoît

Classifications

• C04B35/657 Primary

  for manufacturing refractories (C04B35/05, C04B35/107, C04B35/484 take precedence) · CPC title

• C04B35/62844

  Coating fibres · CPC title

• C04B35/80 Primary

  Fibres, filaments, whiskers, platelets, or the like · CPC title

• F01D5/282

  Selecting composite materials, e.g. blades with reinforcing filaments · CPC title

• C04B2235/5256

  Two-dimensional, e.g. woven structures · CPC title