Method for brazing parts made from a composite material, with anchoring of the brazed joint

Patent metadata

Field	Value
Publication number	US-9573852-B2
Application number	US-201314415393-A
Country	US
Kind code	B2
Filing date	Jul 12, 2013
Priority date	Jul 18, 2012
Publication date	Feb 21, 2017
Grant date	Feb 21, 2017

Abstract

A method of assembling together by brazing two parts made of composite material, each part having an assembly face for brazing with the assembly face of the other part, the method including: making a plurality of cavities in the assembly face of at least one of the two composite material parts, at least some of the cavities opening out into one or more portions of the part that are situated outside the assembly face; interposing capillary elements between the assembly faces of the composite material parts; placing a brazing composition in contact with a portion of the capillary elements; and applying heat treatment to liquefy the brazing composition so as to cause the molten brazing composition to spread by capillarity between the assembly faces of the composite material parts.

First claim

The invention claimed is:

1. A method of assembling together by brazing two parts each made of composite material, each part having an assembly face for brazing with the assembly face of the other part, the method comprising:
making a plurality of cavities in the assembly face of at least one of the two composite material parts, at least some of said cavities opening out into one or more portions of the part that are situated outside the assembly face;
interposing capillary elements between the assembly faces of the composite material parts;
placing a brazing composition in contact with a portion of the capillary elements; and
applying heat to liquefy the brazing composition so as to cause the molten brazing composition to spread by capillarity via the capillary elements between the assembly faces of the composite material parts,
wherein a plurality of grooves are made in the assembly face of at least one of the two composite material parts, at least some of said grooves including perforations formed in a surface thereof opening out into the face opposite from the assembly face of the at least one of the two composite material parts.

2. A method according to claim 1 wherein the part is configured for use in an assembly in which a primary force is applied to the part in a known direction and at least some of the grooves extend over the assembly face of the part in a determined direction that is perpendicular to the direction of the primary force to which the part is to be subjected.

3. A method according to claim 1 wherein some of the grooves extend in the assembly face of the part in two determined directions that are perpendicular to each other.

4. A method according to claim 1 wherein the capillary elements are selected format least one of the following elements: particles of SiC, a web of SiC, a mat of carbon, particles of carbon, and nanotubes of carbon.

5. A method according to claim 1 , wherein the composite material parts for assembling together by brazing are afterbody parts of an aeroengine.

6. A method according to claim 1 , wherein the brazing composition is a metallic composition.

7. A method according to claim 1 , wherein the brazing composition is a silicon based composition.

8. A method according to claim 1 , wherein the brazing composition comprises a mixture of oxides selected from the group consisting of: SiO 2 , Al 2 O 3 , and MgO.

9. A method according to claim 1 , further comprising:
after the applying heat, obtaining a brazed joint; and
inspecting the brazed joint by determining a presence or absence of brazing in the grooves.

Assignees

• Herakles
• Commissariat L Energie Atomique Et Aux Energies Alternatives

Inventors

• Revel Thomas
• Conete Eric
• Philippe Eric
• Chaumat Valérie

Classifications

• C04B2237/086

  Carbon interlayers · CPC title

• C04B2237/062

  based on silica or silicates · CPC title

• C04B2237/86

  Joining of two substrates at their largest surfaces, one surface being complete joined and covered, the other surface not, e.g. a small plate joined at it's largest surface on top of a larger plate · CPC title

• C04B2237/365

  Silicon carbide · CPC title

• C04B2237/06

  Oxidic interlayers · CPC title