Nickel-base superalloy with improved degradation behavior

1. A nickel-base superalloy, consisting of, in % by weight;

7.7-8.3 Cr;

5.0-5.25 Co;

2.0-2.1 Mo;

7.8-8.3 W;

5.8-6.1 Ta;

4.9-5.1 Al;

1.3-1.4 Ti;

0.1-0.6 Pt;

0.1-0.5 Nb;

0.11-0.15 Si:

0.11-0.15 Hf;

200-750 ppm C;

50-400 ppm B, and

remainder nickel and production-related impurities,

wherein the alloy does not, experience a drop in yield strength at room temperature after prior high-temperature creep loading.

2. A single-crystal component, comprising the super alloy of claim 1 .

3. The superalloy of claim 1 , having a Vickers hardness 5% greater than an alloy lacking Pt and Nb, after a degradation treatment cold-rolling and annealing at 1050° C. for 204 hours.

4. The superalloy of claim 1 , having 0.1 to 0.5 wt. % Pt.

5. The superalloy of claim 1 , having 0.1 to 0.2 wt. % Nb.

6. The superalloy of claim 1 , having 0.1 wt. % Pt.

7. The superalloy of claim 1 , having 1.4 wt. % Ti.

8. The superalloy of claim 1 , having 0.5 wt. % Pt.

9. The superalloy of claim 1 , having 0.2 wt. % Nb.

10. The superalloy of claim 1 , having 200-300 ppm C.

11. The superalloy of claim 1 , having 200 ppm C.

12. A gas turbine blade or vane, comprising the superalloy of claim 1 .

13. The gas turbine blade of claim 12 , having a length of 200 to 230 mm.

14. The gas turbine vane of claim 12 , having a length of 200 to 230 mm.

15. The superalloy of claim 1 , having, in % by weight:

0.1-0.5 Pt;

0.1-0.2 Nb;

200-300 ppm C; and

50-100 ppm B.

16. A single-crystal component, comprising the super alloy of claim 15 .

17. The superalloy of claim 15 , having, in % by weight:

8 Cr;

5 Co;

2 Mo;

8 W;

6 Ta;

5 Al;

1.4 Ti;

0.5 Pt;

0.2 Nb;

200 ppm C; and

80 ppm B.

18. The superalloy of claim 17 , having 0.12 wt. % Si; and 0.12 wt. % Hf.