Patent ID: 7028487
Filing Date: 2006-04-18
Classification: F01D,F02C,F05D

Abstract:
1. A gas turbine in which a rotor shaft comprises a plurality of discs each having a plurality of moving blades arranged annularly on a 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 to said moving blades and a recovery flow path for recovering heated refrigerant, each of said supply and recovery flow paths being provided in said rotor shaft; and a flow path for introducing fluid into said gap portions, provided in said discs; and wherein said recovery flow path is arranged on a more radially outer side than said supply flow path, and said flow path for introducing fluid into said gap portion is arranged on a more radially inner side than said supply flow path.