Abstract: A rotor (1) of a turbomachine comprises a basic rotor element (2) and a multiplicity of rotor blades (3, 3′, 3″, 3′″). The rotor blades (3, 3′, 3″, 3′″) are arranged in a distributed manner in at least one row on the circumference of the basic rotor element (2). An area for a row of guide vanes is furthermore provided in front of and/or behind the row of rotor blades. A heat shield element (4) or a plurality of heat shield elements (4′, 4′, 4′″) lined up on the circumference of the rotor (1) is arranged in such a way between the basis rotor element (2) and the rotor blades (3, 3′, 3″, 3′″) of the row of rotor blades that the basic rotor element (2) is completely covered in the areas of the row of rotor blades and the row of guide vanes.

Abstract: A multistage turbocompressor is equipped with a tapping point between two compressor stages. The guide-blade cascade of the stage arranged directly upstream or downstream of the tapping point is designed with adjustable geometry. The pressure at the tapping point can be set within wide limits, irrespective of the compressor operating point, by an adjustment of this guide-blade cascade.

Abstract: Between the rotor and stator of an axial turbo machine, sealing strips of a labyrinth seal that are mortised into sealing strip grooves are provided. Between the sealing strips relief grooves are provided in such a way that the axial stiffness of the rotor or stator is essentially steady. This may be achieved by one or more flat relief grooves, a corrugated surface, or by filling the relief grooves entirely or partially with a suitable, elastic material so that a more even axial tension distribution is achieved between the sealing strip grooves and relief grooves along the rotor or stator section.