Patent ID: 8506239

Claim:
A gas turbine, comprising: a rotor which includes a plurality of rotor blades arranged in a plurality of planes on a periphery of a plurality of rotor disks; and a tie-bolt, wherein the tie-bolt extends along a first recess in the plurality of rotor disks and holds the plurality of rotor disks together as a unit, wherein an inner annular passage and/or an outer annular passage in the rotor encompasses the tie-bolt, wherein within the inner annular passage and/or the outer annular passage an annularly designed spacer is provided for fixing a position of the tie-bolt relative to a center line of the rotor, wherein the spacer includes a plurality of second recesses, the plurality of second recesses are arranged radially to the tie-bolt or to the center line and extend coaxially, wherein the inner annular passage and/or the outer annular passage is used for guiding a cooling medium through and is delimited by an inner separation pipe and/or an outer separation pipe radially on the outside, and wherein the plurality of second recesses serve as through-openings for the cooling medium, wherein the spacer is a spring-elastic ring element.