Cooled turbine blade

1. A turbine blade for a gas turbine, comprising:

a leading edge;

a nose cavity located near the leading edge adapted to transfer coolant from a base of the blade toward a blade tip, wherein the nose cavity has a first coolant inlet reagion in a blade root such that a first coolant flow can flow into the nose cavity;

a crown pocket cavity located near the blade tip and connected to the nose cavity and adapted to transfer coolant from the leading edge toward a trailing edge of the blade;

an inner cavity with a portion having a meandering shape design, wherein the inner cavity has a second coolant inlet region in the blade root such that a second coolant flow, distinct from the first coolant flow, can flow into the inner cavity, and

a wall separating the inner cavity and the nose cavity, the wall comprising a plurality of impingement cooling openings that cool the leading edge.

2. The turbine blade as claimed in claim 1 , wherein a wall surface of the nose cavity, having a prominence in the nose cavity, is impinged by the coolant after the coolant has passed through the impingement cooling openings.

3. The turbine blade as claimed in claim 1 , wherein there is a first outlet opening in the region of the leading edge and the blade tip such that a portion of the first and the second coolant can discharge outward from the nose cavity.

4. The turbine blade as claimed in claim 1 , wherein the nose cavity is connected to the crown pocket by an opening such that a coolant can flow into the crown pocket from the nose cavity.

5. The turbine blade as claimed in claim 1 , wherein the crown pocket widens in a radial direction from the nose cavity toward a trailing edge of the turbine blade.

6. The turbine blade as claimed in claim 1 , wherein the crown pocket and the inner cavity are separated by a transverse web having an opening such that a portion at the second coolant flow can flow there through.

7. The turbine blade as claimed in claim 6 , wherein a natural mode of a blade vibration of the turbine blade can be adjusted by the position and thickness of the transverse web.

8. The turbine blade as claimed in claim 1 , wherein the nose cavity is located between an inner surface of the leading edge and the wall.

9. The turbine blade as claimed in claim 6 , wherein the crown pocket is located between the blade tip and the transverse web.

10. The turbine blade as claimed in claim 1 , wherein no film cooling is used.

11. The turbine blade as claimed in claim 1 , wherein no film cooling is used in the region of the leading edge.

12. A cooled gas turbine blade, comprising:

a blade root portion;

a blade platform portion;

a blade airfoil portion having a leading edge and a trailing edge;

a nose cavity located between an inner wall and an inner surface of the leading edge, an inner surface of the platform portion, and an inner surface of the blade root portion, and wherein the nose cavity has a first coolant inlet region in the blade root portion such that a first coolant flow can flow into the nose cavity;

an inner cavity having a meandering shape, wherein the inner cavity has a second coolant inlet region in the blade root portion such that a second coolant flow, separate from the first coolant flow, can flow into the inner cavity; and

a plurality of impingement cooling openings in the inner wall directed toward the inner surface of the leading edge,

wherein only a portion of the second coolant flow passes through the impingement cooling openings into the nose cavity.

13. The cooled turbine blade as claimed in claim 12 , further comprising a crown pocket cavity located near a blade tip and connected to the nose cavity.

14. The turbine blade as claimed in claim 13 , wherein the crown pocket and the inner cavity are separated by a transverse web having an opening such that a portion of the second coolant flow can flow there through.

15. The turbine blade as claimed in claim 14 , wherein a natural mode of a blade vibration of the turbine blade can be adjusted by the position and thickness of the transverse web.

16. The cooled turbine blade as claimed in claim 12 , wherein the inner surface of the leading edge has a prominence.

17. The cooled turbine blade as claimed in claim 12 , wherein there is a first outlet opening in the region of the leading edge and the blade tip such that a portion of the first and the second coolant can discharge outward from the nose cavity.

18. The cooled turbine blade as claimed in claim 13 , wherein the nose cavity is connected to the crown pocket by an opening such that a coolant can flow into the crown pocket from the nose cavity.

19. The turbine blade as claimed in claim 13 , wherein the crown pocket widens in a radial direction from the nose cavity toward a trailing edge of the turbine blade.

20. The turbine blade as claimed in claim 12 , wherein no film cooling is used.

21. The turbine blade as claimed in claim 12 , wherein no film cooling is used in the region of the leading edge.

22. A turbine, comprising: a cooled turbine blade, comprising: a leading edge; a nose cavity in the region of the leading edge located between an inner wall and an inner surface of the leading edge, wherein the nose cavity has a first coolant inlet region in a blade root portion of the cooled turbine blade such that a first coolant flow can flow into the nose cavity; a

crown pocket cavity in the region of a blade tip of the turbine blade and connected to the nose cavity; an inner cavity having a meandering shape, wherein the inner cavity has a second coolant inlet region in the blade root portion such that a second coolant flow, distinct from the first coolant flow, can flow into the inner cavity; and a plurality of impingement cooling openings in the inner wall that cool the leading edge.