Method for manufacturing a TiAl blade of a turbine engine

Patent metadata

Field	Value
Publication number	US-10758957-B2
Application number	US-201615576783-A
Country	US
Kind code	B2
Filing date	May 26, 2016
Priority date	May 26, 2015
Publication date	Sep 1, 2020
Grant date	Sep 1, 2020

Abstract

A method for manufacturing a titanium aluminide blade of a turbine engine, including production of a titanium aluminide ingot, extrusion of the ingot through an opening in a die having one main arm and at least one side arm, such as to obtain a extruded ingot having the shape of a bar with a cross-section having one main arm and at least one side arm substantially perpendicular to the main arm, transverse cutting of the extruded ingot such as to obtain sections of extruded ingot, forging of each section of extruded ingot such as to obtain a turbine engine blade.

First claim

The invention claimed is:

1. A method for manufacturing a turbine engine blade, made of titanium aluminide, comprising:
forming a titanium aluminide ingot;
extruding the titanium aluminide ingot through an opening of a die, the opening having a main slot and at least one side slot which extends from one of the ends of the main slot substantially perpendicular to said main slot, so as to obtain an extruded ingot having the shape of a bar with a cross-section having a main branch and at least one side branch substantially perpendicular to the main branch;
transverse cutting of the extruded ingot so as to obtain sections of extruded ingot;
forging of each section of extruded ingot so as to obtain a turbine engine blade, wherein said forging is carried out in hot dies with a temperature comprised between 600° and 950° C.,
wherein the titanium aluminide ingot is formed by powder spraying,
said method further comprising cladding the titanium aluminide ingot prior to said extruding and stripping between said extruding and the forging.

2. The method for manufacturing a turbine engine blade according to claim 1 , wherein the opening of the die has a single side slot which extends from one of the ends of the main slot, perpendicular to said main slot, so as to obtain the extruded ingot in the form of a bar with a cross-section having the main branch and a single side branch which extends from one of the ends of the main branch, perpendicular to said main branch.

3. The method for manufacturing a turbine engine blade according to claim 1 , wherein the opening of the die has a first side slot winch extends from one end of the main slot, substantially perpendicular to said main slot, and a second side slot which extends from the other end of the main slot substantially perpendicular to said main slot, so as to obtain the extruded ingot in the form of a bar having a cross-section having the main branch, a first side branch extending substantially perpendicular to the main branch from one end thereof, and a second side branch extending substantially perpendicular to the main branch from the other end thereof.

4. The method for manufacturing a turbine engine blade according to claim 1 , said forging being carried out in the open air.

5. The method for manufacturing a turbine engine blade according to claim 1 , further including machining after said forging.

Assignees

• Safran Aircraft Engines
• Safran

Inventors

• Leconte Gilbert
• Franchet Jean-Michel
• Sallot Pierre

Classifications

• B23P13/04

  involving slicing of profiled material · CPC title

• B22F5/04

  of turbine blades · CPC title

• B21C23/142

  Making profiles · CPC title

• F05D2230/24

  by extrusion · CPC title

• B21C23/16

  Making turbo blades or propellers · CPC title