Heat treatment of titanium alloy

Patent metadata

Field	Value
Publication number	US-2016273085-A1
Application number	US-201514661315-A
Country	US
Kind code	A1
Filing date	Mar 18, 2015
Priority date	Mar 18, 2015
Publication date	Sep 22, 2016
Grant date	—

Abstract

The present disclosure describes methods for forming metal components, including aircraft landing gear components, from high strength and suitably high ductility titanium alloys, including an improved Ti-5553 alloy.

First claim

What is claimed is:

1 . A method for forming a titanium component comprising:
forming a metal component into a final configuration using a titanium alloy comprising Ti-5553; solutionizing the metal component between about 30° C. and 60° C. less than a beta transus temperature of the titanium alloy for between about 1 hour and 2 hours to form a solutionized metal component; and aging the solutionized metal component between about 575° C. and wherein about 625° C. for between about 2 hours and about 4 hours to form a heat treated metal component.

2 . The method of claim 1 , further comprising a step of finishing the heat treated metal component.

3 . The method of claim 1 , wherein the solutionized metal component comprises between about 15 percent and about 20 percent of primary alpha phase particles by volume.

4 . The method of claim 1 , wherein the heat treated metal component comprises a plurality of fine scale alpha phase particles having a lenticular configuration with an average diameter of between about 0.1 microns and about 0.3 microns and an average length of between about 1 micron and about 3 microns.

5 . The method of claim 1 , wherein the heat treated metal component comprises a ductility of at least about 4% elongation in any grain direction.

6 . The method of claim 1 , wherein the heat treated metal component comprises a yield tensile strength of at least about 1.17×10 6 kPa in any grain direction.

7 . The method of claim 1 , wherein the heat treated metal component comprises an ultimate tensile strength of at least about 1.24×10 6 kPa in any grain direction.

8 . The method of claim 1 , wherein the heat treated metal component comprises a landing gear component.

9 . The method of claim 8 , wherein the heat treated metal component comprises one of a piston, an upper torque link, and a lower torque link.

10 . A method comprising:
solutionizing a Ti-5553 alloy between component between about 30° C. and 60° C. less than a beta transus temperature of the Ti-5553 alloy for between about 1 hour and 2 hours; and aging the Ti-5553 alloy between about 575° C. and about 625° C. for between about 2 hours and 4 hours to form a heat treated Ti-5553 alloy.

11 . The method of claim 10 , wherein after solutionizing, the Ti-5553 alloy comprises between about 15 volume percent and about 20 volume percent of primary alpha phase particles.

12 . The method of claim 10 , wherein after aging, the Ti-5553 alloy comprises a plurality of fine scale alpha phase particles having a lenticular configuration with an average diameter of between about 0.1 micron and 0.3 microns and an average length of between about 1 and 3 microns.

13 . The method of claim 10 , wherein aging, the heat treated Ti-5553 alloy comprises a ductility of at least about 4% elongation in any grain direction.

14 . The method of claim 10 , wherein after aging, the heat treated Ti-5553 alloy comprises a yield tensile strength of at least about 1.17×10 6 kPa in any grain direction.

15 . The method of claim 10 , wherein after aging, the heat treated Ti-5553 alloy comprises an ultimate tensile strength of at least about 1.24×10 6 kPa in any grain direction.

Assignees

• Goodrich Corp

Inventors

• Panza-Giosa Roque

Classifications

• B64C25/00

  Alighting gear (air-cushion alighting gear B60V3/08) · CPC title

• C22C14/00

  Alloys based on titanium · CPC title

• C22F1/183 Primary

  of titanium or alloys based thereon · CPC title