Patent ID: 8764395

Claim:
A blade for a gas turbine, comprising: a blade airfoil having a leading edge and a trailing edge extending in a blade longitudinal direction up to a blade tip, and at the blade tip the blade airfoil merges into a shroud segment; a first rib, projecting upwards, arranged on the shroud segment in a flow direction of a hot gas flow, extending transversely to said flow direction; a winglet formed on the shroud segment upstream of the first rib, in a region of the leading edge of the blade airfoil, for guiding a hot gas flow in this region; and a plurality of cooling holes which extend inside the winglet for direct cooling of the winglet, wherein the winglet comprises a leading terminal edge for arranging transversely to the flow direction of the hot gas flow wherein the entire leading terminal edge is curved, the plurality of cooling holes being led up to the curved portion of the leading terminal edge of the winglet obliquely, and wherein the cooling holes are in communication with a cooling passage arranged in an interior of the blade airfoil and below a central portion of the first rib for supply with a cooling medium, the cooling holes leading up to the leading terminal edge of the winglet obliquely from the central portion of the first rib only to portions of the winglet on either side of the blade airfoil.