Patent ID: 7267527
Filing Date: 2007-09-11
Classification: F01D,F16B

Abstract:
1. Rotor for a turbomachine, in particular a low-pressure turbine rotor for a gas turbine, having at least one stage, each stage comprising a rotor disk having rotor blades attached to the rotor disk, and the rotor disk of each stage being removably connected either to oppositely situated rotor disks of adjoining stages or to a rotor connection of a rotor shaft by at least one respective attachment, wherein at least one of the attachments extends through the rotor disk of at least one stage, whereby the at least one attachment is guided with radial play into at least one borehole passing through the rotor disk, so that an interior borehole surface is not subjected to load or force, wherein the at least one attachment extends through a flange for a first rotor disk of two oppositely situated rotor disks to be connected to one another, whereby the at least one attachment further extends through a second rotor disk of the two oppositely situated rotor disks to be connected to one another, and the at least one attachment is guided with radial play into at least one borehole passing through the second rotor disk, so that an interior borehole surface is not subjected to load or force, and wherein the at least one attachment is guided without radial play into each borehole in the flange for the first rotor disk or the rotor connection.