Abstract: A jacket ring for the low-pressure-turbine region of a gas turbine, having a plurality of lined-up segments which are arranged between a moving blade ring with a shroud band and the casing of the gas turbine, which carry a run-in lining and which hold guide blades in a positive-locking manner, wherein each segment comprises a hot-gas-side seal carrier and a casing-side securing element, the seal carrier and the securing element are at the greatest possible distance from one another and only have common contact points which are as small as possible, and the securing element is axially supported directly on the casing of the gas turbine.

Abstract: A jacket ring for the low-pressure-turbine region of a gas turbine, having a plurality of lined-up segments which are arranged between a moving blade ring with shroud band and the casing of the gas turbine, which carry a run-in lining and which hold guide blades in a positive-locking manner, said guide blades being arranged upstream.

Abstract: Two components such as pipes having radial end flanges with conical flange clamping surfaces are clamped together by a clamping ring having at least two ring sections with conical ring clamping surfaces engaging said conical flange clamping surfaces when clamping screws passing through section ends are tightened. The ring sections have an inner ring radius (RR) slightly larger than a respective flange radius (FR) for providing a positive but gradual engagement between said conical surfaces when said ring sections are clamped together for example by threaded bolts or screws at ring section ends.

Abstract: The present axial-flow turbine blade has two cooling channels extending radially through the blade. These radial channels communicate with each other through impingement cooling ducts or holes (3) extending substantially axially through the blade. One channel (1) supplies cooling fluid through the holes (3) into the other channel (2) which is located nearer the leading edge (8) of the blade and extends substantially in parallel to the leading edge (8). The cooling fluid impacts on the wall of the other channel (2) and is laterally blown out at a side wall of the blade. For optimal cooling, especially of the leading edge of the blade, which is subject to severe thermal loads, this edge is penetrated by cooling elements (4) in the form of pins or wires in axial alignment with the impingement cooling holes or ducts (3). These cooling pins or wires (4) reach into the channel (2) nearer the leading edge with their tapered end (5) and are made of a highly thermally conductive material.