Patent ID: 6393829
Filing Date: 2002-05-28
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 the axial direction in turn, characterized in thatgap portions are formed between rotor axis side regions of said discs facing said spacers and adjacent spacers, said spacers each being solid and said rotor axis side regions each including a radially central portion of said rotor shaft; contact surfaces contact each other on both rotor peripheral side regions of said discs facing said spacers and adjacent spacers are formed; a first flow path for supplying a coolant into said moving blades and a second flow path for recovering the coolant heated by said moving blades from said moving blades are provided; and a third flow path for introducing fluid into said gap portions is formed in said discs, said third flow path being independent from said first and second flow paths.