Blade for a turbo engine

1. A blade for a turbomachine comprising:

an interior space surrounded by a wall structure forming a surface of the blade; and

openings in the wall structure, the openings comprising a plurality of micro-channels each individually extending from the interior space to the surface;

wherein each of the plurality of micro-channels forms a path defining a particular direction for flowing cooling gas; and

the plurality of micro-channels is distributed over an area region of the surface;

wherein the plurality of micro-channels is, in relation to a normal n to the surface, oriented with at least one of varying angles of inclination φ, measured in the blade cross section or varying angles of inclination ϑ, measured in the longitudinal orientation of the blade;

wherein the wall structure has a varying wall thickness, wherein the wall thickness is thinner as the impingement angle β of a flow in the turbomachine onto the surface of the blade increases.

2. The blade as claimed in claim 1 , wherein the micro-channels have a smaller angle φ as an impingement angle β of a flow in the turbomachine onto the surface of the blade increases.

3. The blade as claimed in claim 1 , further comprising a varying spacing from one opening to adjacent openings over the area region.

4. The blade as claimed in claim 3 , wherein the spacing a is smaller as an impingement angle β of a flow in the turbomachine onto the surface of the blade increases.

5. The blade as claimed in claim 1 , further comprising a support structure in the interior space of the blade;

wherein the support structure is mechanically connected to the wall structure;

wherein the support structure defines a channel system through which the micro-channels adjoining the support structure are accessible; and

wherein the channel system has a lower flow resistance than the micro-channels adjoining the support structure.

6. The blade as claimed in claim 5 , wherein the support structure comprises a three-dimensional lattice.

7. The blade as claimed in claim 5 , wherein the support structure comprises, in its interior, a supply channel for cooling gas; and

wherein the supply channel has a lower flow resistance than the support structure.

8. The blade as claimed in claim 7 , wherein the supply channel is separated from the support structure by a screen.

9. The blade as claimed in claim 8 , wherein screen openings in the screen have a cross section no larger than that of the micro-channels.

10. The blade as claimed in claim 8 , wherein a total cross section of the screen openings is no smaller than a total cross section of the micro-channels.

11. The blade as claimed in claim 7 , wherein the supply channel has an undulating or meandering contour viewed in cross section.

12. The blade as claimed in claim 7 , wherein a cross section of the supply channel increases in a radially outward direction proceeding from a blade root.

13. The blade as claimed in claim 7 , further comprising strut arrangements in the supply channel.

14. The blade as claimed in claim 7 , further comprising a cyclone separator for the cooling gas integrated into the supply channel.

15. The blade as claimed in claim 5 , wherein transitions from the support structure into the wall structure are of flowing form.

16. The blade as claimed in one of claim 1 , further comprising a supply channel connected to an outlet opening leading to the surface of the blade.

17. The blade as claimed in claim 16 , wherein the outlet opening in the surface of the blade is situated on a suction side of the blade or in a trailing edge of the blade.