Abstract: A rotor for a thermal turbomachine, in particular a gas turbine, is configured to conduct a medium in its interior. In order to conduct the medium in the interior with low flow losses, it is provided that a rotor disk of the compressor has holes, in order to feed the medium from outside into the rotor interior. For improved temperature control of the rotor disk, the holes conduct the medium through the rotor disk counter to the flow direction in the compressor.

Abstract: A rotor for a turbine has a plurality of rotor components lined up in the axial direction and connected by a connecting rod, wherein a groove which extends in the circumferential direction and is open in the axial direction is disposed on one of the rotor components, wherein a coupling element running around the connecting rod in order to support the connecting rod is disposed in the groove. The rotor is adapted to enable particularly stable support of the connecting rod in order to prevent vibrations. The coupling element is disposed on a retaining element connected to the connecting rod.

Abstract: A rotor for a thermal turbomachine, in particular a gas turbine, is configured for guiding a medium in its interior. In order to guide the medium in the interior with low flow losses, a pair of rotor disks lie on one another, of which the first of the two rotor disks of the pair has holes, in order to feed the medium from the outside into the rotor interior, and rib-shaped ribs, in order to guide the medium further in the direction of the rotational axis, and the second rotor disk of the pair being configured with the aid of an auxiliary web in such a way that the flow passages which are formed between the ribs as viewed in the circumferential direction are delimited axially at least over the large part of the radial extent of the ribs.

Abstract: A rotor for a thermal turbomachine, in particular a gas turbine, is configured to conduct a medium in its interior. In order to conduct the medium in the interior with low flow losses, it is provided that a rotor disk of the compressor has holes, in order to feed the medium from outside into the rotor interior. For improved temperature control of the rotor disk, the holes conduct the medium through the rotor disk counter to the flow direction in the compressor.

Abstract: A rotor for a thermal turbomachine, in particular a gas turbine, is configured for guiding a medium in its interior. In order to guide the medium in the interior with low flow losses, a pair of rotor disks lie on one another, of which the first of the two rotor disks of the pair has holes, in order to feed the medium from the outside into the rotor interior, and rib-shaped ribs, in order to guide the medium further in the direction of the rotational axis, and the second rotor disk of the pair being configured with the aid of an auxiliary web in such a way that the flow passages which are formed between the ribs as viewed in the circumferential direction are delimited axially at least over the large part of the radial extent of the ribs.

Abstract: A rotor for a turbine has a plurality of rotor components lined up in the axial direction and connected by a connecting rod, wherein a groove which extends in the circumferential direction and is open in the axial direction is disposed on one of the rotor components, wherein a coupling element running around the connecting rod in order to support the connecting rod is disposed in the groove. The rotor is adapted to enable particularly stable support of the connecting rod in order to prevent vibrations. The coupling element is disposed on a retaining element connected to the connecting rod.

Abstract: A rotor for an axial flow turbomachine is provided, having a number of a plurality of disc-shaped or drum-shaped rotor components and at least one pin-shaped tie-rod extending through the rotor components, wherein a counter-bearing is screwed onto each of the projecting ends of the tie-rod for axially bracing the rotor components arranged therebetween. The tie-rod has at least two axially adjacent tie-rod elements which are each connected to one another in a detachable manner by connector. Elastic stretching characteristics of the two tie-rod elements are matched to each other such that, with the rotor components being clamped between the two counter-bearings, a clamping of the counter-bearing and the connection element and the rotor components arranged therebetween is at least partially released.

Abstract: A method for assembling and disassembling a rotor having a number of rotor components of an axial flow turbomachine and such a rotor is provided. The rotor has a number of a plurality of disc-shaped or drum-shaped rotor components and at least one pin-shaped tie-rod extending through the rotor components, wherein a counter-bearing is screwed onto each of the projecting ends of said tie-rod for axially bracing the rotor components arranged therebetween. In order to achieve shorter service intervals, a connector is screwed onto the tie-rod between both counter-bearings, wherein, after the release of one of the two counter-bearings, the rotor components arranged between the connector and the other of the two counter-bearings are braced with each other by the connector.