Patent ID: 8523526

Claim:
A blade for a gas turbine, comprising a blade airfoil which extends in a blade longitudinal direction and at a lower end merges into a shank, having a concave and a convex side, which terminates in a blade root for fastening the blade on a blade carrier, wherein devices for cooling the blade, which are supplied with a cooling medium, via a feed hole arranged on the shank that opens into an outside space on the convex side of the shank, are arranged inside the blade airfoil, the blade having a center plane which lies transversely to a machine axis, and the feed hole opens into the outside space on the one side of the center plane wherein in a region of the feed hole provision is made for a generally planar stiffening element which reaches beyond immediate surrounds of the feed hole for reducing peaks of mechanical stress, the stiffening element is formed symmetrically to the center plane and also encompasses the mouth of the feed hole, and extends over an entire length of the shank in the blade longitudinal direction and has an approximately trapezoidal edge contour.