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An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality o

An object is to improve the operational reliability of a gas turbine by suppressing thermal stress and thermal deformation acting on the rotor of the gas turbine. The gas turbine has a rotor shaft constructed by arranging, in an axial direction in turn, a plurality of discs each having a plurality of combustion gas-driven moving blades annularly arranged on the peripheral portion and spacers arranged between the discs, and is characterized in that gap portions are formed between a region, on the rotor shaft center portion side, of the above-mentioned discs facing the spacers and spacers adjacent thereto, contact surfaces are formed both of which contact on both a region, on the rotor peripheral side, of the above-mentioned discs facing the spacers and adjacent spacers thereto, and a third flow path leading fluid to the above-mentioned gap portions is provided.

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1. 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 i

1. 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. 2. 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, formed in said discs, for introducing fluid into said gap portion; 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, and formed so that steam passing through said flow path is recoverable without cooling said moving blades. 3. A method of supplying refrigerant of a gas turbine cooling system, wherein said gas turbine cooling system comprises a rotor shaft formed with 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; 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; and a flow path, formed in said discs, for introducing fluid into said gap portion; said method characterized in that said flow path for introducing fluid into said gap portions is arranged so as to communicate said gap potions and supply flow path or said recovery flow path, and the refrigerant is flowed into said flow path for introducing fluid into said gap portions without cooling said moving blades when said gas turbine is started.