Nickel-base single-crystal superalloys, method of manufacturing same and gas turbine high temperature parts made thereof

• US 6,673,308 B2
• Filed: 08/30/2001
• Issued: 01/06/2004
• Est. Priority Date: 08/30/2000
• Status: Expired due to Term

• Current Assignee: Independent Administrative Institution National Institute For Materials Science, Toshiba Energy Systems & Solutions Corporation (Toshiba Corporation)
• Original Assignee: Independent Administrative Institution National Institute For Materials Science, Kabushiki Kaisha Toshiba (Toshiba Corporation)
• Inventors: Ishiwata, Yutaka, Nakazawa, Shizuo, Hino, Takehisa, Yoshioka, Yomei, Harada, Hiroshi, Kobayashi, Toshiharu, Koizumi, Yutaka
• Primary Examiner(s): King, Roy
• Assistant Examiner(s): Wilkins, III, Harry D.
• Application Number:
  US09/941,699
• Publication Number:
  US 20020062886A1
• Time in Patent Office: 859 Days
• Field of Search: 420/448, 420/443, 148/428
• US Class Current: 420/448
• CPC Class Codes: C22C 19/057 with the maximum Cr content being less 10%
• CPC Class Codes: C22F 1/10 of nickel or cobalt or alloys based thereon

Abstract

A nickel-base single-crystal superalloy, essentially consists of, in percentages by weight, 4.0% to 11.0% of cobalt, 3.5% to less than 5.0% of chromium, 0.5% to 3.0% of molybdenum, 7.0% to 10.0% of tungsten, 4.5% to 6.0% of aluminum, 0.1% to 2.0% of titanium, 5.0% to 8.0% of tantalum, 1.0% to 3.0% of rhenium, 0.01% to 0.5% of hafnium, 0.01% to 0.1% of silicon, and a balance being nickel and inevitable impurity, a total amount of rhenium and chromium being not less than 4.0% and a total amount of rhenium, molybdenum, tungsten and chromium being not more than 18.0%.

Claims

1. A nickel-base single-crystal superalloy, consisting of, in percentages by weight, 4.0% to 11.0% of cobalt, 3.5% to less than 5.0% of chromium, 0.5% to 3.0% of molybdenum, 8.2% to 10.0% of tungsten, 4.5% to 6.0% of aluminum, 0.1% to 2.0% of titanium, 5.0% to 8.0% of tantalum, 1.0% to 3.0% of rhenium, 0.01% to 0.5% of hafnium, 0.01% to 0.1% of silicon, and at least one element selected from the group consisting of less than 2% of niobium, less than 1% of vanadium, less then 2% of ruthenium, less than 0.1% of carbon, less than 0.1% of lanthanum, and less than 0.1% of cerium, and a balance being nickel and inevitable impurity, a total amount of rhenium and chromium being not less than 4.0% and a total amount of rhenium, molybdenum, tungsten and chromium being not more than 18.0%.

2. A nickel-base single-crystal superalloy according to claim 1, wherein, in percentages by weight, cobalt is 5.0% to 10.0%, chromium is 4.0% to less than 5.0%, molybdenum is 1.0% to 2.5%, tungsten is 8.2% to 9.0%, aluminum is 5.0% to 5.5%, titanium is 0.1% to 1.0%, tantalum is 6.0% to less than 8.0%, rhenium is 2.0% to 3.0%, hafnium is 0.01% to 0.5%, and silicon is 0.01% to 0.1%.

3. A nickel-base single-crystal superalloy according to claim 1, wherein, in percentages by weight, cobalt is 5.0% to 10.0%, chromium is 4.0% to less than 5.0%, molybdenum is 1.0% to 2.5%, tungsten is 8.2% to 9.0%, aluminum is 5.0% to 5.5%, titanium is 0.8% to 1.5%, tantalum is 5.0% to less than 6.0%, rhenium is 2.0% to 3.0%, hafnium is 0.01% to 0.5%, and silicon is 0.01% to 0.1%.

4. A high temperature gas turbine part comprising the nickel-base single-crystal superalloy claimed in claim 1.

5. The nickel-base superalloy of claim 1, wherein niobium is present therein.

6. The nickel-base superalloy of claim 1, wherein vanadium is present therein.

7. The nickel-base superalloy of claim 1, wherein ruthenium is present therein.

8. The nickel-base superalloy of claim 1, wherein carbon is present therein.

9. The nickel-base superalloy of claim 1, wherein lanthanum is present therein.

10. The nickel-base superalloy of claim 1, wherein cerium is present therein.

11. A nickel-base single-crystal superalloy, consisting of, in percentages by weight, cobalt 5.0% to 10.0%, chromium 4.0% to less than 5.0%, molybdenum 1.0% to 2.5%, tungsten 8.2% to 9.0%, aluminum 5.0% to 5.5%, titanium 0.1% to 1.0%, tantalum 6.0% to 7.0%, rhenium 2.0% to 3.0%, hafnium 0.01% to 0.2%, silicon 0.01% to 0.1%, and at least one element selected from the group consisting of niobium of less than 2%, vanadium of less than 1%, ruthenium of less than 2%, carbon of less than 0.1%, boron of less than 0.05%, zirconium of less than 0.1%, yttrium of less than 0.1%, lanthanum of less than 0.1% and cerium of less than 0.1%.

12. A high temperature gas turbine part comprising the nickel-base single-crystal superalloy claimed in claim 11.

13. The nickel-base superalloy of claim 11, wherein niobium is present therein.

14. The nickel-base superalloy of claim 11, wherein vanadium is present therein.

15. The nickel-base superalloy of claim 11, wherein ruthenium is present therein.

16. The nickel-base superalloy of claim 11, wherein carbon is present therein.

17. The nickel-base superalloy of claim 11, wherein boron is present therein.

18. The nickel-base superalloy of claim 11, wherein zirconium is present therein.

19. The nickel-base superalloy of claim 11, wherein yttrium is present therein.

20. The nickel-base superalloy of claim 11, wherein lanthanum is present therein.

21. The nickel-base superalloy of claim 11, wherein cerium is present therein.