초록 ▼

The present application provides a cooling system for a gas turbine. The cooling system may include a source of CO2, a stator blade cooling system positioned about a casing of the gas turbine and in communication with the source of CO2 and a number of stator blades, and a rotor blade cooling system

The present application provides a cooling system for a gas turbine. The cooling system may include a source of CO2, a stator blade cooling system positioned about a casing of the gas turbine and in communication with the source of CO2 and a number of stator blades, and a rotor blade cooling system positioned about a rotor shaft of the gas turbine and in communication with the source of CO2 and a number of rotor blades. A first portion of a flow of CO2 may flow through the stator blade cooling system and returns to the source of CO2 in a first closed loop and a second portion of the flow of CO2 may flow through the rotor blade cooling system and returns to the source of CO2 in a second closed loop.

대표청구항 ▼

1. A cooling system for a gas turbine, comprising: a source of CO2;a stator blade cooling system positioned about a casing of the gas turbine and in communication with the source of CO2 and a plurality of stator blades; anda rotor blade cooling system positioned about a rotor shaft of the gas turbin

1. A cooling system for a gas turbine, comprising: a source of CO2;a stator blade cooling system positioned about a casing of the gas turbine and in communication with the source of CO2 and a plurality of stator blades; anda rotor blade cooling system positioned about a rotor shaft of the gas turbine and in communication with the source of CO2 and a plurality of rotor blades;wherein a first portion of a flow of CO2 flows through the stator blade cooling system and returns to the source of CO2 in a first closed loop and wherein a second portion of the flow of CO2 flows through the rotor blade cooling system and returns to the source of CO2 in a second closed loop. 2. The cooling system of claim 1, wherein the stator blade cooling system comprises a plurality of stator blades with an internal stator plenum therein. 3. The cooling system of claim 2, wherein the stator blade cooling system comprises a stator coolant inlet plenum in communication with the source of CO2 and the plurality of stator blades. 4. The cooling system of claim 2, wherein the internal stator plenum comprises a plurality of inlet flow channels leading to a cap plenum and a plurality of outlet flow channels. 5. The cooling system of claim 2, wherein the stator blade cooling system comprises a stator coolant outlet plenum in communication with the plurality of stator blades and the source of CO2. 6. The cooling system of claim 2, wherein the stator blade cooling system comprises a stator blade cooling inflow line and a stator blade cooling outflow line in communication with the plurality of stator blades. 7. The cooling system of claim 1, wherein the first closed loop comprises a heat exchanger, a gas conduit, and/or a CO2 storage system. 8. The cooling system of claim 1, wherein the rotor blade cooling system comprises a plurality of rotor blades with an internal rotor plenum therein. 9. The cooling system of claim 8, wherein the rotor blade cooling system comprises a rotor coolant inlet plenum in communication with the source of CO2 and the plurality of rotor blades. 10. The cooling system of claim 8, wherein the internal rotor plenum comprises a plurality of inlet flow channels leading to a cap plenum and a plurality of outlet flow channels. 11. The cooling system of claim 8, wherein the rotor blade cooling system comprises a rotor coolant outlet plenum in communication with the plurality of rotor blades and the source of CO2. 12. The cooling system of claim 8, wherein the rotor blade cooling system comprises a rotor blade cooling inflow line and a rotor blade cooling outflow line in communication with the plurality of rotor blades. 13. The cooling system of claim 1, wherein the second closed loop comprises a heat exchanger, a gas conduit, and/or a CO2 storage system. 14. The cooling system of claim 1, wherein the rotor bade cooling system extends axially through the rotor shaft. 15. A cooling system for a gas turbine, comprising: a source of CO2;a stator blade cooling system positioned about a casing of the gas turbine and in communication with the source of CO2 and a plurality of stator blades;wherein the plurality of stator blades comprises an internal stator plenum; anda rotor blade cooling system positioned axially through a rotor shaft of the gas turbine and in communication with the source of CO2 and a plurality of rotor blades;wherein the plurality of rotor blades comprises an internal rotor plenum;wherein a first portion of a flow of CO2 flows through the stator blade cooling system and returns to the source of CO2 in a first closed loop and wherein a second portion of the flow of CO2 flows through the rotor blade cooling system and returns to the source of CO2 in a second closed loop. 16. The cooling system of claim 15, wherein the stator blade cooling system comprises a stator coolant inlet plenum in communication with the source of CO2 and the plurality of stator blades. 17. The cooling system of claim 15, wherein the first closed loop comprises a heat exchanger, a gas conduit, and/or a CO2 storage system. 18. The cooling system of claim 15, wherein the rotor blade cooling system comprises a rotor coolant inlet plenum in communication with the source of CO2 and the plurality of rotor blades. 19. The cooling system of claim 15, wherein the second closed loop comprises a heat exchanger, a gas conduit, and/or a CO2 storage system.