Patent ID: 6735957
Filing Date: 2004-05-18
Classification: F01D,F02C,F05D

Abstract:
A gas turbine in which a rotor shaft comprises a plurality of discs each having a plurality of moving blades driven by combustion gas and arranged annularly on the peripheral portion, and spacers arranged between said discs, said respective discs and spacers being arranged in an axial direction in turn, comprising:gap portions formed between rotor axis side regions of said discs facing said spacers and adjacent spacers; a supply flow path for supplying refrigerant for cooling and a recovery flow path for recovering heated refrigerant, each of said supply and recovery flow paths being provided in said discs and spacers of said rotor shaft; contact surfaces contacting each other on both rotor peripheral side regions of said discs facing said spacers and adjacent spacers; a flow path, which is led from a compressor and is different from said supply flow path, formed in said discs, for introducing fluid into said gap portions; flow paths, provided in said moving blades, for introducing said refrigerant for cooling and leading out said refrigerant heated by the combustion gas; and wherein said flow path for introducing fluid into said gap portions is arranged so as to communicate said gap portions and supply flow path or said recovery flow path.