Patent ID: 8585351

Claim:
A gas turbine blade, comprising: a root; an airfoil with a leading edge and a trailing edge, a radial outer tip, and a pressure side and a suction side between the leading edge and the trailing edge; and a cooling air channel system extending from an air inlet opening in the root throughout the airfoil to a plurality of air outlets at the pressure side and the leading edge of the top of the tip of the airfoil, wherein a number of air outlets per area near the leading edge of the tip is higher than the average number of air outlets per area in the top of the tip, wherein a concentration of air outlets at the top of the tip of the airfoil is higher on the pressure side than on the suction side, and wherein the plurality of air outlets closest to the trailing edge are larger in air cross section than the plurality of air outlets in the middle between the leading edge and the trailing edge.