Aluminum-copper alloys containing vanadium
View Patent ↗New 2xxx aluminum alloys containing vanadium are disclosed. In one embodiment, the aluminum alloy includes 3.3-4.1 wt. % Cu, 0.7-1.3 wt. % Mg, 0.01-0.16 wt. % V, 0.05-0.6 wt. % Mn, 0.01 to 0.4 wt. % of at least one grain structure control element, the balance being aluminum, incidental elements and impurities. The new alloys may realize an improved combination of properties, such as in the T39 or T89 tempers.
1. A method comprising:
(a) preparing an aluminum alloy product consisting of:
3.3 to 4.1 wt. % Cu;
0.7 to 1.3 wt. % Mg;
0.01 to 0.16 wt. % V;
0.05 to 0.6 wt. % Mn;
0.05 to 0.20 wt. % Zr; and
up to 0.6 wt. % Ag;
the balance being aluminum, incidental elements, and impurities;
wherein the combined amount of copper and magnesium is in the range of from 4.0 wt. % to 5.1 wt. %;
wherein the ratio of copper to magnesium is in the range of from 2 to 5.5 and
(b) processing the aluminum alloy product into one of a T3 or T8 temper.
2. The method of claim 1 , wherein the processing comprises:
solution-heat treating and quenching the aluminum alloy product; and
cold working the aluminum alloy product.
3. The method of claim 2 , comprising, after the cold working, naturally aging the aluminum alloy product to a T3 temper.
4. The method of claim 3 , wherein the T3 temper is selected from the group consisting of T39, T351, and T36.
5. The method of claim 2 , comprising, after the cold working, artificially aging the aluminum alloy product to a T8 temper.
6. The method of claim 5 , wherein the T8 temper is selected from the group consisting of T89, T851 and T86.
7. The method of claim 1 , wherein the preparing comprises at least one of rolling, extruding and forging.
8. The method of claim 1 , comprising:
forming the aluminum alloy product into an aerospace structural member.
9. The method of claim 8 , wherein the aerospace structural member is selected from the group consisting of an aircraft fuselage skin, an aircraft fuselage panel, a lower wing skin, a horizontal stabilizer, a pressure bulkhead, and a fuselage reinforcement.
10. The method of claim 1 , comprising:
forming the aluminum alloy product into a drill pipe.
11. The method of claim 1 , comprising:
forming the aluminum alloy product into a drill riser.
12. The method of claim 1 , wherein the aluminum alloy product includes:
3.3 to 3.9 wt. % Cu;
0.8 to 1.2 wt. % Mg;
0.05 to 0.16 wt. % V;
0.1 to 0.5 wt. % Mn; and
0.08 to 0.18 wt. % Zr.
13. The method of claim 12 , wherein the aluminum alloy product includes:
3.4 to 3.7 wt. % Cu;
0.9 to 1.1 wt. % Mg;
0.07 to 0.15 wt. % V;
0.2 to 0.4 wt. % Mn; and
0.08 to 0.15 wt. % Zr.
14. The method of claim 13 , wherein the alloy includes at least 0.09 wt. % V.
15. The method of claim 13 , wherein the impurities include one or more of Fe, Si and Zn, and wherein the aluminum alloy product includes not greater than 0.15 wt. % Fe, not greater than 0.10 wt. % Si, and not greater than 0.25 wt. % Zn.
16. The method of claim 14 , wherein the impurities include one or more of Fe, Si and Zn, and wherein the aluminum alloy product includes not greater than 0.05 wt. % Fe, not greater than 0.03 wt. % Si, and not greater than 0.25 wt. % Zn.
17. The method of claim 15 , wherein the aluminum alloy product is substantially free of Ag.
18. The method of claim 16 , wherein the aluminum alloy product is substantially free of Ag.
19. The method of claim 15 , wherein the ratio of copper to magnesium is in the range of from 3.25 to 4.5.
20. The method of claim 18 , wherein the ratio of copper to magnesium is in the range of from 3.25 to 4.5.