Patent ID: 6966752

Claim:
A jacket ring for an axial-flow low-pressure turbine region or power-turbine region of a gas turbine, comprising a plurality of segments which are lined up in a circumferential direction and arranged radially outside a moving blade ring with a shroud band and inside a casing of the gas turbine, each of the plurality of segments carrying a run-in lining for at least one sealing tip of the shroud band and which hold a plurality of guide blades in a positive-locking manner to the casing at their radially outer downstream end, the locking performed only by the segments, said guide blades being arranged upstream of the moving blade ring, wherein each segment comprises a hot-gas-side seal carrier provided with the run-in lining and a casing-side securing element supporting at least one upstream guide blade and extending axially to an extent comparable with the seal carrier, wherein the seal carrier and the securing element are at a distance from one another over regions of their surfaces which are as large as possible and only have common heat-conducting contact points in regions which are as small as possible, and wherein the securing element is axially supported directly on the casing of the gas turbine via a stop part.