Composite reinforcing insert and manufacturing method

Patent metadata

Field	Value
Publication number	US-10119205-B2
Application number	US-201414912694-A
Country	US
Kind code	B2
Filing date	Aug 19, 2014
Priority date	Aug 21, 2013
Publication date	Nov 6, 2018
Grant date	Nov 6, 2018

Abstract

A composite reinforcement insert includes a strand formed by a central fiber made of ceramic material surrounded by filaments of metal alloy helically wound around the central fiber, and a metal reinforcement layer covering the strand.

First claim

The invention claimed is:

1. A composite reinforcing insert comprising:
a strand consisting of a central fibre made of a ceramic material surrounded by metal alloy filaments wound spirally around the central fibre, and
a metal reinforcing layer coating the strand.

2. The composite reinforcing insert according to claim 1 , wherein the strand comprises N filaments, where N is greater than or equal to 6.

3. The composite reinforcing insert according to claim 1 , wherein the central fibre is made of silicon carbide.

4. The composite reinforcing insert according to claim 1 , wherein the filaments are made of an alloy based on titanium, nickel or aluminium.

5. The composite reinforcing insert according to claim 1 , wherein the reinforcing layer is made from the same material as a basic material forming the filaments.

6. A turbomachine part comprising a composite reinforcing insert including
a strand consisting of a central fibre made of a ceramic material surrounded by metal alloy filaments wound spirally around the central fibre, and
a metal reinforcing layer coating the strand.

7. A method of making a reinforcing insert from a central ceramic fibre, the method comprising:
stranding metal alloy filaments around the central fibre so as to form a strand, and
coating the strand with a protective metal layer.

8. The method according to claim 7 , wherein the coating includes dipping the strand into a liquid metal bath in levitation fusion, the liquid metal in levitation fusion containing a filler with the same material as a basic material of the filaments.

9. The method according to claim 7 , further comprising fixing the filaments by spot welds.

10. The method according to claim 7 , further comprising, between the stranding and the coating, coating the strand with an oxidation-resistant protective layer.

11. The composite reinforcing insert according to claim 2 , wherein N is equal to 7, 19 or 37.

Assignees

• Safran Aircraft Engines
• Fsp One

Inventors

• Klein Gilles Charles Casimir
• Sanchez Gérald

Classifications

• C22C49/08

  Iron group metals · CPC title

• D02G3/12

  Threads containing metallic filaments or strips · CPC title

• D02G3/38 Primary

  Threads in which fibres, filaments, or yarns are wound with other yarns or filaments, {e.g. wrap yarns, i.e. strands of filaments or staple fibres are wrapped by a helically wound binder yarn; (D02G3/32 takes precedence)}; (covering endless core threads with fibres by using open-end spinning techniques D01H4/00) · CPC title

• D07B1/0633

  having a multiple-layer configuration · CPC title

• C22C49/11

  Titanium · CPC title