Patent ID: 8545171

Claim:
A rotor for a gas turbine, comprising: a compressor-side section; a turbine-side section; a first plurality of individual rotor components located in the compressor-side section; a second plurality of individual rotor components located in the turbine-side section; a common tie-bolt; and a hollow shaft, wherein the first plurality of individual rotor components and the second plurality of individual components are held together using the common tie-bolt which is freely guided through a center of the plurality of rotor components, wherein the hollow shaft encompasses the tie-bolt leaving a clearance and is located between a compressor-side rotor component which is arranged nearest to the turbine-side section and a turbine-side rotor component which is arranged nearest to the compressor-side section, and wherein the tie-bolt is fixed in an axial section of the hollow shaft via a star spring which extends around in a circumferential direction and which is supported on a nearest outer rotor component.