SHROUD FOR ROTATING BLADES OF A TURBO MACHINE, AND TURBO MACHINE

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. The invention further relates to a turbo machine, in particular a gas turbine, comprising at least one rotor (12) that has at least one row of several rotating blades (14, 50). A shroud (12) according to the invention is arranged along the circumference of the row of rotating blades.