Patent ID: 7766619
Filing Date: 2010-08-03
Classification: F01D,F05D

Abstract:
1. A gas turbine blade, with a blade airfoil, which extends from a blade root to a blade tip, wherein the blade airfoil comprises a blade airfoil leading edge and a cooling air passage which extends along the leading edge of the blade airfoil inside the blade airfoil, which cooling air passage is defined by the wall of the blade airfoil on the leading edge, and also on the suction side and the pressure side of the blade airfoil, and which, furthermore, is defined by a partition which extends inside the blade airfoil from the pressure-side wall to the suction-side wall, and which cooling air passage steps down to an outlet opening which is arranged in the region of the blade tip, wherein the contour of the opening is geometrically similar to the cross section of the cooling air passage, and wherein the cross-sectional area of the outlet opening is smaller than the cross-sectional area of the cooling air passage.