Al-Cu-Li alloys with improved cryogenic fracture toughness

• US 5,455,003 A
• Filed: 08/10/1993
• Issued: 10/03/1995
• Est. Priority Date: 08/18/1988
• Status: Expired due to Term

• Current Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Original Assignee: Martin Marietta Corporation
• Inventors: Tack, William T., Pickens, Joseph R.
• Primary Examiner(s): Simmons, David A.
• Assistant Examiner(s): Koehler, Robert R.
• Application Number:
  US08/103,662
• Time in Patent Office: 784 Days
• Field of Search: 420/529, 420/531, 420/532, 420/533, 420/539, 420/540, 420/541, 420/542, 420/543, 420/545, 420/552, 420/553, 148/695, 148/698, 148/699, 148/700, 148/701, 148/416, 148/417, 148/418, 148/438, 148/439
• US Class Current: 420/529
• CPC Class Codes: C22C 21/00 Alloys based on aluminium
• CPC Class Codes: C22C 21/12 with copper as the next major constituent
• CPC Class Codes: C22F 1/04 of aluminium or alloys based thereon
• CPC Class Codes: C22F 1/057 of alloys with copper as the next major constituent

Abstract

A method is disclosed for the production of aluminum-copper-lithium alloys that exhibit improved strength and fracture toughness at cryogenic temperatures. Improved cryogenic properties are achieved by controlling the composition of the alloy, along with processing parameters such as the amount of cold-work and artificial aging. The ability to attain substantially equal or greater strength and fracture toughness at cryogenic temperature in comparison to room temperature allows for use of the alloys in cryogenic tanks for space launch vehicles and the like.

Claims

1. A method for producing an improved aluminum-base alloy comprising the steps of:

a) providing a solution heat treated and quenched aluminum-base alloy consisting essentially of from 2.0 to 6.5 weight percent Cu, from 0.2 to 2.0 weight percent Li, and the balance aluminum and incidental impurities; and

b) at least one of working and artificially aging said alloy in an amount sufficient to provide strength and fracture toughness to said alloy at cryogenic temperature substantially equal to or greater than the strength and fracture toughness at room temperature, wherein the fracture toughness at room temperature is at least 18.7 ksi√

in and the fracture toughness at -196°

C. is at least 19.2 ksi√

in.

2. A method according to claim 1, wherein said aluminum-base alloy further contains Mg in an amount up to 40. weight percent and from 0.01 to 1.0 weight percent of at least one grain refiner selected from the group consisting of Zr, Ti, Cr, Mn, Hf, Nb, B, V, and TiB₂.

3. A method according to claim 1, wherein said aluminum-base alloy further contains at least one of Ag in an amount up to 4.0 weight percent, Mg in an amount up to 4.0 weight percent, and Zn in an amount up to 3.0 weight percent.

4. A method according to claim 2, wherein said aluminum-base alloy further contains at least one of Ag in an amount up to 4.0 weight percent, Mg in an amount up to 4.0 weight percent, and Zn in an amount up to 3.0 weight percent.

5. A method according to claim 1, wherein said working of said alloy is performed substantially at room temperature.

6. A method according to claim 1, wherein said working of said alloy is achieved by introducing the equivalent of from 3 to 7 percent stretch to said alloy.

7. A method according to claim 1, wherein the time and temperature at which said artificial aging is performed results in underaging of said alloy to a yield strength at least 5 ksi below the peak yield strength that said alloy is capable of attaining.

8. A method according to claim 1, wherein said artificial aging is performed at a temperature of from 125°

to 150°

C.

9. A method according to claim 1, wherein said Cu comprises from 2.8 to 4.8 weight percent, said Li comprises from 0.4 to 1.5 weight percent, and furthermore comprises Mg in an amount from 0.2 to 1.0 weight percent of said alloy.

10. A method according to claim 2, wherein said Cu comprises from 2.8 to 4.8 weight percent, said Li comprises from 0.4 to 1.5 weight percent, and the aluminum base alloy furthermore comprises Mg in an amount from 0.2 to 1.0 weight percent of said alloy.

11. A method according to claim 9, wherein said aluminum-base alloy further contains at least one of Ag in an amount up to 0.8 weight percent and Zn in an amount up to 1.0 weight percent.

12. A method according to claim 10, wherein said aluminum-base alloy further contains at least one of Ag in an amount up to 0.8 weight percent and Zn in an amount up to 1.0 weight percent.

13. A method according to claim 4, wherein said Cu comprises from 3.0 to 4.5 weight percent, said Li comprises from 0.7 to 1.1 weight percent, said Mg comprises from 0.3 to 0.6 weight percent, and said grain refiner comprises from 0.08 to 0.3 weight percent of said alloy, wherein said grain refiner is selected from the group consisting of Zr, Ti, and combinations thereof.

14. A method according to claim 2, wherein said Cu comprises from 2.8 to 4.8 weight percent, said Li comprises from 0.4 to 1.5 weight percent, and the aluminum base alloy furthermore comprises Mg in an amount from 0.2 to 1.0 weight percent of said alloy.

15. A method according to claim 14, wherein said aluminum-base alloy further contains at least one of Ag in an amount up to 0.8 weight percent and Zn in an amount up to 1.0 weight percent.

16. A method according to claim 13, wherein said aluminum-base alloy further contains at least one of Ag in an amount up to 0.8 weight percent and Zn in an amount up to 1.0 weight percent.

17. A method according to claim 1, wherein the yield strength of said alloy at cryogenic temperature is greater than its yield strength at room temperature, which is greater than 85 ksi (longitudinal), and the plane strain fracture toughness of said alloy at cryogenic temperature is greater than its plane strain fracture toughness at room temperature, which is greater than 25 ksi√

in.

18. A method according to claim 13, wherein the yield strength of said alloy at cryogenic temperature is greater than its yield strength at room temperature, which is greater than 85 ksi (longitudinal), and the plane strain fracture toughness of said alloy at cryogenic temperature is greater than its plane strain fracture toughness at room temperature, which is greater than 25 ksi√

in.

19. A wrought aluminum-base alloy consisting essentially of from 2.8 to 4.8 weight percent Cu, from 0.4 to 1.5 weight percent Li, from 0.2 to 1.0 weigth percent Mg, and the balance aluminum and incidental impurities, wherein said alloy is worked, artificially aged, or worked and artificially aged an amount sufficient to provide strength and fracture toughness to said alloy at cryogenic temperature substantially equal to or greater than the strength and fracture toughness at room temperature, wherein the fracture toughness at room temperature is a least 18.7 ksi√

in.

20. A wrought aluminum-base alloy according to claim 19, wherein said alloy further contains from 0.01 to 1.0 weight percent of at least one grain refiner selected from the group consisting of Zr, Ti, Cr, Mn, Hf, Nb, B, V, and TiB₂.

21. A wrought aluminum-base alloy according to claim 20, wherein said aluminum-base alloy further contains at least one of Ag in an amount up to 0.8 weight percent and Zn in an amount of up to 1.0 weight percent.

22. A wrought aluminum-base alloy according to claim 20, wherein said Cu comprises from 3.0 to 4.5 weight percent, said Li comprises from 0.7 to 1.1 weight percent, said Mg comprises from about 0.3 to about 0.6 weight percent, and said grain refiner comprises from 0.08 to 0.3 weight percent of said alloy, wherein said grain refiner is selected from the group consisting of Zr, Ti and combinations thereof.

23. A wrought aluminum-base alloy according to claim 21, wherein said Cu comprises from 3.0 to 4.5 weight percent, said Li comprises from 0.7 to 1.1 weight percent, said Mg comprises from about 0.3 to about 0.6 weight percent, and said grain refiner comprises from 0.08 to 0.3 weight percent of said alloy, wherein said grain refiner is selected from the group consisting of Zr, Ti, and combinations thereof.

24. A wrought aluminum-base alloy according to claim 20, wherein said Cu comprises from about 3.0 to about 4.5 weight percent of said alloy.

25. A wrought aluminum-base alloy according to claim 20, wherein said Li comprises from about 0.7 to about 1.1 weight percent of said alloy.

26. A wrought aluminum-base alloy according to claim 20, wherein said alloy is in the form of an extrusion.

27. A wrought aluminum-base alloy according to claim 20, wherein said alloy is in the form of a plate.

28. A wrought aluminum-base alloy according to claim 20, wherein said alloy is in the form of a sheet.

29. A wrought aluminum-base alloy according to claim 20, wherein the yield strength of said alloy at cryogenic temperature is substantially equal to greater than its yield strength at room temperature, which is greater than 85 ksi, and the plane strain fracture toughness of said alloy at cryogenic temperature is greater than its plane strain fracture toughness at room temperature, which is greater than 25 ksi√

in.

30. A wrought aluminum-base alloy according to claim 20, wherein the yield strength of said alloy at cryogenic temperature is greater than its yield strength at room temperature, which is greater than 85 ksi, and the plane stress fracture toughness of said alloy at cryogenic temperature is greater than its plane stress fracture toughness at room temperature, which is greater than 25 ksi√

in.

31. A wrought aluminum-base alloy according to claim 20, wherein said alloy is underaged to a yield strength at least 5 ksi below the peak yield strength that said alloy is capable of attaining.

32. A cryogenic material-holding container made from an alloy consisting essentially of from 2.8 to 4.5 weight percent Cu, from 0.4 to 1.5 weight percent Li, from 0.2 to 1.0 weight percent Mg, and the balance aluminum and incidental impurities, wherein said alloy is worked, artificially aged, or worked and artificially aged an amount sufficient to provide strength and fracture toughness to said alloy at cryogenic temperature substantially equal to or greater than the strength and fracture toughness at room temperature, wherein the fracture toughness at room temperature is at least 18.7 ksi√

in and the fracture toughness at -196°

C. is at least 19.2 ksi√

in.

33. A cryogenic material-holding container according to claim 32, wherein said alloy further contains from 0.01 to 1.0 weight percent of at least one grain refiner selected from the group consisting of Zr, Ti, Cr, Mn, Hf, Nb, B, V, and TiB₂.

34. A cryogenic material-holding container according to claim 33, wherein said aluminum-base alloy further contains at least one of Ag in an amount up to 0.8 weight percent and Zn in an amount of up to 1.0 weight percent.

35. A cryogenic material-holding container according to claim 33, wherein the yield strength of said alloy at cryogenic temperature is greater than its yield strength at room temperature, which is greater than 85 ksi (longitudinal), and the plane strain fracture toughness of said alloy at cryogenic temperature is greater than its plane strain fracture toughness at room temperature, which is greater than 25 ksi√

in.

36. A cryogenic material-holding container according to claim 33, wherein the yield strength of said alloy at cryogenic temperature is greater than its yield strength at room temperature, which is greater than 85 ksi (longitudinal), and the plane stress fracture toughness of said alloy at cryogenic temperature is greater than its plane stress fracture toughness at room temperature, which is greater than 25 ksi√

in.

37. A cryogenic material-holding container according to claim 33, wherein said alloy is underaged to a yield strength at least about 5 ksi below the peak yield strength that said alloy is capable of attaining.

38. A cryogenic material-holding container according to claim 33, wherein said container has been formed by welding.

39. A cryogenic material-holding container according to claim 33, wherein said cryogenic material is selected from the group consisting of liquid hydrogen, liquid oxygen, and liquid nitrogen.