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There is described a turbine blade of a gas turbine comprising a suction-side blade wall and a pressure-side blade wall that, in the trailing edge area, runs toward the suction-side blade wall. This suction-side blade wall has a trailing edge projection projecting over the end edge of the pressure-s

There is described a turbine blade of a gas turbine comprising a suction-side blade wall and a pressure-side blade wall that, in the trailing edge area, runs toward the suction-side blade wall. This suction-side blade wall has a trailing edge projection projecting over the end edge of the pressure-side blade wall at least in a partial section of the trailing edge area. A turbine blade of the aforementioned type is designed for a particularly long serviceable life while requiring little cooling air. To this end, the pressure-side surface of the trailing edge projection has a number of trough-shaped recesses that increase the transfer of heat from the trailing edge projection by a local swirling of the cooling air.

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The invention claimed is: 1. A turbine blade for a gas turbine, comprising: a suction-side blade wall; a delivery-side blade wall tapering toward the suction-side blade wall in a trailing edge region; a trailing edge tab projecting beyond an end edge of the delivery-side blade wall at least in a po

The invention claimed is: 1. A turbine blade for a gas turbine, comprising: a suction-side blade wall; a delivery-side blade wall tapering toward the suction-side blade wall in a trailing edge region; a trailing edge tab projecting beyond an end edge of the delivery-side blade wall at least in a portion of the trailing edge region, wherein the suction-side blade wall comprises the trailing edge tab; and a plurality of through-shaped depressions at the delivery-side surface of the trailing edge tab, wherein the depressions have a boundary edge in the delivery-side surface of the trailing edge tab. 2. The turbine blade as claimed in claim 1, wherein the depressions have an elliptic boundary edge. 3. The turbine blade as claimed in claim 1, wherein the depressions have a circular boundary edge. 4. The turbine blade as claimed in claim 3, wherein the depressions have the configuration of a spherical segment. 5. The turbine blade as claimed in claim 3, wherein a radius of the circular boundary edge is 1/10 to ¼ of a width of the trailing edge tab. 6. The turbine blade as claimed in claim 4, wherein a radius of the circular boundary edge is 1/10 to ¼ of a width of the trailing edge tab. 7. The turbine blade as claimed in claim 4, wherein a depth of the spherical segment is essentially ⅓ of the sphere radius. 8. The turbine blade as claimed in claim 6, wherein a depth of the spherical segment is essentially ⅓ of the sphere radius. 9. The turbine blade as claimed in claim 6, wherein the depressions are arranged regularly. 10. The turbine blade as claimed in claim 4, wherein the depressions are regularly arranged and of the same dimension, and wherein a distance between the boundary edges of adjacent depressions is one to one-and-a-half of a sphere diameter. 11. The turbine blade as claimed in claim 10, wherein depressions at a end of the trailing edge tab are predetermined by the pattern and fitted partly onto a remaining surface of the trailing edge. 12. The turbine blade as claimed in claim 1, wherein the turbine blade has stiffening elements. 13. A method for cooling a turbine blade, comprising: providing a turbine blade having: a suction-side blade wall, a delivery-side blade wall tapering toward the suction-side blade wall in a trailing edge region, a trailing edge tab projecting beyond an end edge of the delivery-side blade wall at least in a portion of the trailing edge region, wherein the suction-side blade wall comprises the trailing edge tab, and a plurality of through-shaped depressions at the delivery-side surface of the trailing edge tab, wherein the depressions have a boundary edge in the delivery-side surface of the trailing edge tab; providing a cooling air flowing along the trailing edge tab swirled locally by depressions arranged on the trailing edge tab. 14. The method for cooling a turbine blade as claimed in claim 13, wherein: the depressions form a regular pattern to form a uniformly cooling effect over the entire delivery-side surface of the trailing edge tab interrupted by stiffening elements. 15. A gas turbine, comprising: a plurality of turbine blades, wherein at least one of the turbine blades has: a suction-side blade wall, a delivery-side blade wall tapering toward the suction-side blade wall in a trailing edge region, a trailing edge tab projecting beyond an end edge of the delivery-side blade wall at least in a portion of the trailing edge region, wherein the suction-side blade wall comprises the trailing edge tab, and a plurality of through-shaped depressions at the delivery-side surface of the trailing edge tab, wherein the depressions have a boundary edge in the delivery-side surface of the trailing edge tab. 16. The turbine blade as claimed in claim 15, wherein the depressions have an elliptic boundary edge. 17. The turbine blade as claimed in claim 15, wherein the depressions have a circular boundary edge. 18. The turbine blade as claimed in claim 17, wherein the depressions have a configuration of a spherical segment. 19. The turbine blade as claimed in claim 17, wherein a radius of the circular boundary edge is 1/10 to ¼ of a width of the trailing edge tab, and wherein the depth of the spherical segment is essentially ⅓ of the sphere radius.