Patent ID: 8721281

Claim:
A cooled blade, for a gas turbine, comprising: a blade airfoil which extends between a leading edge and a trailing edge in a flow direction and on a suction side and on a pressure side is delimited by a wall, wherein the walls include an interior space in which cooling air flows towards the trailing edge in the flow direction and discharges to an outside area in the region of the trailing edge, the pressure-side wall terminating at a distance in front of the trailing edge in the flow direction, forming a pressure-side lip, in such a way that the cooling air discharges from the interior space on the pressure side, the interior space, at a distance in front of the trailing edge, is sub-divided by a plurality of ribs, which are oriented parallel to the flow direction, into a plurality of parallel cooling passages which create a pressure drop and in which turbulators are additionally arranged for increasing the cooling effect, and before an outlet of the cooling air from the interior space a plurality of flow barriers are arranged in the flow path of the cooling air and distributed transversely to the flow direction, wherein each flow barrier extends in the flow direction to a point upstream of the pressure-side lip.