Titanium alloy and method for heat treatment of large-sized...

Alloys or metallic compositions – Titanium base – Aluminum containing

Reexamination Certificate

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C148S421000, C420S421000

Reexamination Certificate

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06800243

ABSTRACT:

FIELD OF THE INVENTION
The inventions relates to non-ferrous metallurgy, and more particularly, to production of modern titanium alloys preferably used for manufacturing of large-sized forgings, stampings, fasteners and other parts for aeronautical engineering.
PRIOR STATE OF ART
Titanium-based alloy of the following composition, % by mass, is known:
aluminum
4.0-6.3
vanadium
4.5-5.9
molybdenum
4.5-5.9
chromium
2.0-3.6
iron
0.2-0.8
zirconium
0.01-0.08
carbon
0.01-0.25
oxygen
0.03-0.25
titanium
the balance
(RF Patent # 2122040, C22C 14/00, 1998) as the prototype.
The said alloy possesses a good combination of high strength and plasticity of large-sized parts up to 150-200 mm thick, water or air hardened. The alloy is easily hot deformed and is welded by argon-arc and electron-bean welding.
The disadvantage of the alloy is an insufficient level of strength of massive large-sized parts more than 150-200 mm thick, air hardened.
The method of heat treatment of large-sized semifinished items made of two-phase titanium alloys comprising pre-heating up to the temperature 7-50° C. higher than the polymorphic transformation temperature, holding for 0.15-3 hours, cooling to the two-phase region temperature, 20-80° C. lower than the polymorphic transformation temperature, holding for 0.15-3 hours, hardening and aging is known (USSR Inventor's Certificate # 912771. C22F, Jan. 18, 1982) as the prototype.
The disadvantage of the method is an insufficient level of strength of massive large-sized parts more than 150-200 mm thick.


REFERENCES:
patent: 4067734 (1978-01-01), Curtis et al.
patent: 4889170 (1989-12-01), Mae et al.
patent: 5332545 (1994-07-01), Love
patent: 2122040 (1998-11-01), None
patent: 555161 (1977-05-01), None
patent: 912771 (1982-03-01), None

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