Patent ID: 6422809
Filing Date: 2002-07-23
Classification: F01D

Abstract:
A gas turbine arrangement, comprising:a compressor with a compressor rotor, a turbine with a turbine rotor and connected with the compressor, and a balancing member connected with the turbine rotor and arranged to counteract axial forces generated by the compressor rotor and the turbine rotor, wherein the balancing member is arranged to be activated by means of a pressure fluid, wherein the arrangement comprises at least one channel which is arranged to lead at least a part of the pressure fluid used for said activation to at least a part of the turbine for influencing the temperature of the same, wherein said part of the turbine is a rotor portion, wherein the balancing member is attached to that end of the turbine rotor which is located downstream and wherein said channel leads to a space which is formed between said end of the turbine rotor and the balancing member.