Patent ID: 8632309

Claim:
A blade for a gas turbine, comprising: a blade root; a blade tip; a shroud segment formed at the blade tip; and an airfoil, which extends along a longitudinal axis from the blade root to the blade tip, wherein the shroud segment includes first and second edges which abut against shroud segments of adjacent blades to make a ring-like shroud, the first and second edges being each provided with a respective side rail on an upper side of the shroud segment, wherein the shroud segment comprises on its upper side: a plurality of fins running parallel in a circumferential direction, wherein the side rails are subdivided into sections having at least one of a different height and a different width, wherein extending from a first fin to a second fin is a first side rail section having side rails of a first height and a first width, and wherein extending from the second fin to the third fin is a second side rail section having side rails of a second height different from the first height and of a second width different from the first width.