Method of reinforcing a mechanical part

Patent metadata

Field	Value
Publication number	US-9482102-B2
Application number	US-201214122917-A
Country	US
Kind code	B2
Filing date	May 23, 2012
Priority date	May 27, 2011
Publication date	Nov 1, 2016
Grant date	Nov 1, 2016

Abstract

A method of reinforcing a mechanical part, for example a turbine engine part, the part being made by assembling together two portions, the method including: inserting reinforcing mechanisms of elongate shape at least in part in at least one recess formed in one of the portions and opening out into a junction surface between the portions; and assembling the two portions together.

First claim

The invention claimed is:

1. A method for producing a metal reinforcement for mounting on a leading edge or a trailing edge of a composite blade for a turbine engine, a fan blade of an airplane turboprop or turbojet, the metal reinforcement including a solid portion extended by first and second lips which are attached to pressure and suction side surfaces of the blade, the method comprising:
providing first and second sheets of the metal reinforcement, each of the sheets including a first portion corresponding to the solid portion of the metal reinforcement and a second portion corresponding to a lip of the metal reinforcement, the first portion including a junction surface;
providing at least one recess in each junction surface of the first and second sheets of the metal reinforcement;
inserting a bundle of reinforcing fibers surrounded by a sheath of elongate shape at least in part in the recess; and
assembling together the first and second sheets such that the junction surfaces of the first and second sheets abut each other; and
diffusion bonding the first and second sheets to form the metal reinforcement.

2. A method according to claim 1 , wherein the reinforcing fibers are made of ceramic.

3. A method according to claim 1 , wherein the first and second sheets are made of titanium-based alloy.

4. A method according to claim 1 , wherein the reinforcing fibers are coated in a metal material.

5. A method according to claim 4 , wherein the coating of the reinforcing fibers and the first and second sheets are all made of a same metal material, and the first and second sheets are assembled together by diffusion welding such that, after diffusion, the piece of metal reinforcement comprises a homogeneous metal matrix having the reinforcing fibers inserted therein.

6. A method according to claim 1 , wherein the sheath is, made by braiding fibers.

7. A method according to claim 1 , wherein, prior to being inserted in the recess of one of the portions, the bundle of reinforcing fibers is shaped to match a shape of the recess.

8. A method according to claim 1 , wherein a cross-sectional area of the bundle of reinforcing fibers is less than or equal to 95% of a cross-sectional area of the sheath.

9. A piece of metal reinforcement for mounting on a leading edge or a trailing edge of a composite blade for a turbine engine, or a fan blade of an airplane turboprop or turbojet, and obtained by performing the method according to claim 1 , comprising reinforcing means arranged in a core of the piece of metal reinforcement in recesses in junction surfaces of two portions of the piece of metal reinforcement.

10. A method according to claim 2 , wherein the reinforcing fibers are made of silicon carbide.

Assignees

• Klein Gilles Charles Casimir
• Franchet Jean-Michel Patrick Maurice
• Leconte Gilbert Michel Marin
• Magnaudeix Dominique
• Snecma

Inventors

• Klein Gilles Charles Casimir
• Franchet Jean-Michel Patrick Maurice
• Leconte Gilbert Michel Marin
• Magnaudeix Dominique

Classifications

• B29C65/48

  using adhesives {, i.e. using supplementary joining material; solvent bonding} · CPC title

• B29C66/742

  to metals or their alloys · CPC title

• F04D29/023 Primary

  especially adapted for elastic fluid pumps · CPC title

• F01D5/282 Primary

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

• F05D2300/2261

  of silicon · CPC title