Coolant recovery type gas turbine
View Patent ↗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.
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.
2. A gas turbine according to claim 1 , wherein the fluid introduced into said gap portions is exhausted into a gas flow path of said gas turbine.
3. 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 steam for cooling to said moving blades and a recovery flow path for recovering heated steam, 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.
4. 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 steam for cooling to said moving blades and a recovery flow path for recovering heated steam, 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 flow path for introducing fluid into said gap portion is constructed so as to be supplied with air extracted from a compressor, and arranged on a more radially inner side than said supply flow path,
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.