Abstract: In a cooled blade for a gas turbine, a cooling fluid, preferably cooling air, flows for convective cooling through internal cooling passages located close to the wall and is subsequently deflected for external film cooling through film-cooling holes onto the blade surface. The fluid flow is directed in at least some of the internal cooling passages in counterflow to the hot-gas flow flowing around the blade. Homogeneous cooling in the radial direction is achieved by providing a plurality of internal cooling passages and film-cooling holes arranged one above the other in the radial direction in the blade in such a way that the discharge openings of the film-cooling holes in each case lie so as to be offset from the internal cooling passages, and in particular the discharge openings lie between the internal cooling passages.

Abstract: In a cooled blade for a gas turbine, in which blade a cooling fluid, preferably cooling air, flows for convective cooling through internal cooling passages (141-143) located close to the wall and is subsequently deflected for external film cooling through film-cooling holes (161-163) onto the blade surface, and the fluid flow is directed in at least some of the internal cooling passages (141-143) in counterflow to the hot-gas flow (18) flowing around the blade, homogeneous cooling in the radial direction is achieved owing to the fact that a plurality of internal cooling passages (141-143) and film-cooling holes (161-163) are arranged one above the other in the radial direction in the blade (10, 20, 30) in such a way that the discharge openings of the film-cooling holes (161-163) in each case lie so as to be offset from the internal cooling passages (141-143), in particular lie between the internal cooling passages (141-143).