Titanium alloy composition for the production of high-performance parts, in particular for the aeronautical industry

Patent metadata

Field	Value
Publication number	US-9399806-B2
Application number	US-201013376882-A
Country	US
Kind code	B2
Filing date	Jun 8, 2010
Priority date	Jun 8, 2009
Publication date	Jul 26, 2016
Grant date	Jul 26, 2016

Abstract

A titanium alloy having at least 4% by weight aluminum and at least 0.1% by weight oxygen, the alloy also including at least one element selected from vanadium, molybdenum, chromium, and iron. The titanium alloy also includes hafnium in a proportion by weight of at least 0.1%.

First claim

What is claimed is:

1. A forged aircraft landing gear composed of a titanium alloy, in addition to titanium constituting the majority proportion by weight, the alloy including at least the following elements, in the proportions by weight that are specified:

aluminum
4.0% to 7.5%

vanadium
3.5% to 5.5%

molybdenum
4.5% to 7.5%

chromium
1.8% to 3.6%

iron
0.2% to 0.5%

hafnium
0.1% to 0.7%

oxygen
0.1% to 0.3%

carbon
0.01% to 0.2%

zirconium
0.1% to less than 0.7%,

wherein the combined proportion by weight of hafnium plus zirconium does not exceed 1%.

2. The forged aircraft landing gear part according to claim 1 , further including silicon in a proportion by weight lying in the range 0.05% to 0.25%.

3. The forged aircraft landing gear part according to claim 1 , wherein the proportions by weight of the elements constituting the titanium alloy are specified as:

Aluminum
7.0%

Vanadium
4.5%

Molybdenum
6.5%

Chromium
3.0%

Iron
0.4%

Hafnium
0.5%

Zirconium
0.5%

Oxygen
0.3%

Carbon
0.05%

Titanium
the balance.

4. The titanium alloy according to claim 1 , wherein the proportions by weight of the elements constituting the titanium alloy are specified as:

Aluminum
7.0%

Vanadium
4.5%

Molybdenum
6.5%

Chromium
3.0%

Iron
0.4%

Hafnium
0.5%

Zirconium
0.3%

Silicon
0.15%

Oxygen
0.3%

Carbon
0.05%

Titanium
the balance.

5. A method of production of a forged aircraft landing gear part composed of a titanium alloy, the method including the steps of:
forging the titanium alloy at a temperature close to the β→α+β polymorphic transition temperature, said titanium alloys, in addition to titanium constituting the majority proportion by weight, including at least the following elements, in the proportions by weight that are specified:

aluminum
4.0% to 7.5%

vanadium
3.5% to 5.5%

molybdenum
4.5% to 7.5%

chromium
1.8% to 3.6%

iron
0.2% to 0.5%

hafnium
0.1% to 0.7%

oxygen
0.1% to 0.3%

carbon
0.01% to 0.2%

zirconium
0.1% to less than 0.7%,

wherein the combined proportion by weight of hafnium plus zirconium not exceeding 1%
heating the forged titanium alloy to a temperature in a range of 30° C. to 70° C. below the β→α+β polymorphic transition temperature of the alloy;
pausing at said temperature for 2 h to 5 h;
cooling;
pausing at a temperature in the range 540° C. to 600° C for a period of 8 h to 16 h; and
cooling.

Assignees

• Soniak Francis
• De Monicault Jean-Michel
• Messier Bugatti Dowty

Inventors

• Soniak Francis
• De Monicault Jean-Michel

Classifications

• C22F1/18

  High-melting or refractory metals or alloys based thereon · CPC title

• C22C14/00 Primary

  Alloys based on titanium · CPC title