Abstract: A shroud for the rotating blades of a turbo machine, particularly a gas turbine, in which shroud is arranged along the circumference of a row of several rotating blades disposed on a rotor and has at least one separation gap along its circumference. The separation gap is formed in zigzag shape and has at least three damping gaps that are distanced from one another and extend at an angle relative to an axis of rotation of the rotor, and adjacent to these, has connection gaps each connecting damping gaps or extending the latter in the direction of shroud edges, wherein, when the rotor rotates, the gap width of damping gaps is reduced until the gap walls forming the damping gaps come to rest against each other.

Abstract: The invention relates to a shroud for rotating blades of a turbo machine, in particular a gas turbine. Said shroud (10) is arranged along the circumference of a row of several rotating blades (14, 50) disposed on a rotor (12) and has at least one separation gap (16, 16?, 16?) along the circumference. The separation gap (16, 16?, 16?) is serrated and has at least three damping gaps (20, 22, 24, 26, 28) that are located at a distance from one another and extend at an angle from the axis of rotation (18) of the rotor (12), and adjacent connection gaps (30, 32, 34, 36, 38, 40) which connect the damping gaps (20, 22, 24, 26, 28) or extend the same in the direction of the shroud edges (46, 48). When the rotor (12) rotates, the width of the damping gaps (20, 22, 24, 26, 28) is reduced to the point where the gap walls (42, 44) forming the damping gaps (20, 22, 24, 26, 28) rest against each other.

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: A suspension of an annular secondary structure on a primary structure, in the form of a spoke-type centering device, has at least three sliding guides distributed uniformly over the structure circumference. Each sliding guide allows at least a linear relative movement of the structures transversely to their axial direction. The linear direction of movement of each sliding guide runs, in relation to the structure-related radial direction at the location of the sliding guide, at an angle having radial and tangential direction components.

Abstract: Suspension of an annular secondary structure on a primary structure, in the form of a spoke-type centering device having at least three sliding guides distributed uniformly over the structure circumference, each sliding guide allowing at least a linear relative movement of the structures transversely to their axial direction.