Patent ID: 8182225

Claim:
A blade for a gas turbine comprising: a leading edge running in a longitudinal direction substantially radially to an axis of the turbine; a trailing edge running in the longitudinal direction; a blade body disposed between the leading edge and the trailing edge so as to define a pressure side and a suction side; an exit slot disposed in the blade body in an area of the trailing edge and running in the longitudinal direction and configured to discharge a cooling medium from an interior of the blade body; and a row of first and second control elements disposed in the exit slot in a distributed manner so as to alternate, one after the other, between the first and second control elements in the longitudinal direction and configured to control a mass flow of the cooling medium exiting through the exit slot, the first control elements having a first edge contour and the second control elements having a second edge contour different from the first edge contour wherein the largest cross-sectional area of each of the first control elements is larger than the largest cross-sectional area of each of the second control elements, and the largest cross-sectional area of each of the first control elements and the second control elements lie in a single plane extending across the exit slot.