Abstract: A damping system for damping vibrations of a rotor blade of a rotor of a turbomachine is disclosed. A damping element is guided on a support such that the damping element is radially outwardly movable during a rotation of the rotor and is contactable with a lower platform area of a rotor blade. A circumferential contact surface is formed by an elevation on the lower platform area, where the circumferential contact surface is a limit stop for a movement of the damping element.

Abstract: The stage of a turbine or of a compressor having a plurality of blades which are mounted on a rotor and/or a stator of the stage. The blades are combined into a number of blade clusters as integral components which are each composed of at least two blades and which are each equipped with one shared blade mount for mounting the cluster on the rotor or stator.

Abstract: A turbo compressor in an axial type of construction is disclosed. The turbo compressor having a bladed stator and a bladed rotor, and having a longitudinally split compressor casing and a guide blade ring with adjustable guide blades. The guide blades are pivotably mounted about radial axes radially within their aerofoil on an inner ring belonging to the stator. The inner ring is split, i.e., segmented, at at least two points of its circumference. Furthermore, the inner ring has for each guide blade at least one bearing bush which can be inserted radially into an opening from inside.