Abstract: A turbine blade for a gas turbine, having a blade root and an aerodynamically curved blade airfoil arranged above the blade root. The blade airfoil has a pressure-side and a suction-side blade wall, together extending from a leading edge, that can receive a flow of working medium, to a trailing edge. A multiplicity of cooling air outlet openings are formed on the pressure-side blade wall, which extend upstream from the trailing edge with respect to the flow direction, and through these openings cooling air that is conveyed through the interior of the blade airfoil can exit. At least one of the cooling air outlet openings has a substantially rectangular or trapezoidal shape with rounded corners. At least the lower corner, pointing towards the leading edge, of the cooling air outlet opening forms a relief notch, which projects outwardly from the rectangular shape, with a rounded notch bottom.

Abstract: A turbine blade for a gas turbine, having a blade root and an aerodynamically curved blade airfoil arranged above the blade root. The blade airfoil has a pressure-side and a suction-side blade wall, together extending from a leading edge, that can receive a flow of working medium, to a trailing edge. A multiplicity of cooling air outlet openings are formed on the pressure-side blade wall, which extend upstream from the trailing edge with respect to the flow direction, and through these openings cooling air that is conveyed through the interior of the blade airfoil can exit. At least one of the cooling air outlet openings has a substantially rectangular or trapezoidal shape with rounded corners. At least the lower corner, pointing towards the leading edge, of the cooling air outlet opening forms a relief notch, which projects outwardly from the rectangular shape, with a rounded notch bottom.