Patent ID: 9464529
Filing Date: 2016-10-11
CPC Classification: F01D,F05D

Claim Text:
1. A blade, for a gas turbine, comprising a blade airfoil, having a shroud segment arranged on its upper end, the shroud segment together with shroud segments of other blades of a blade row forming an annular shroud which delimits hot gas passage of the gas turbine, and said shroud segment, on sides on which it adjoins adjacent shroud segments of the annular shroud, is provided with upwardly projecting side rails which extend along a side edge, to improve sealing to the hot gas passage, wherein the side rails comprise rail-parallel or essentially rail-parallel, upwardly open slots through which cooling air, which is introduced via the shroud segment from an interior of the blade airfoil, discharges into the space above the shroud segment.