System and method for cooling gas turbine components

Patent metadata

Field	Value
Publication number	US-9279340-B2
Application number	US-201313890332-A
Country	US
Kind code	B2
Filing date	May 9, 2013
Priority date	Mar 23, 2010
Publication date	Mar 8, 2016
Grant date	Mar 8, 2016

Abstract

The present application provides a cooling system for a gas turbine. The cooling system may include a source of CO 2 , a stator blade cooling system positioned about a casing of the gas turbine and in communication with the source of CO 2 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 CO 2 and a number of rotor blades. A first portion of a flow of CO 2 may flow through the stator blade cooling system and returns to the source of CO 2 in a first closed loop and a second portion of the flow of CO 2 may flow through the rotor blade cooling system and returns to the source of CO 2 in a second closed loop.

First claim

We claim:

1. A cooling system for a gas turbine, comprising:
a source of CO 2 ;
a stator blade cooling system positioned about a casing of the gas turbine and in communication with the source of CO 2 and a plurality 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 CO 2 and a plurality of rotor blades;
wherein a first portion of a flow of CO 2 flows through the stator blade cooling system and returns to the source of CO 2 in a first closed loop and wherein a second portion of the flow of CO 2 flows through the rotor blade cooling system and returns to the source of CO 2 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 CO 2 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 CO 2 .

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 CO 2 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 CO 2 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 CO 2 .

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 CO 2 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 CO 2 ;
a stator blade cooling system positioned about a casing of the gas turbine and in communication with the source of CO 2 and a plurality of stator blades;
wherein the plurality of stator blades comprises an internal stator plenum; and
a rotor blade cooling system positioned axially through a rotor shaft of the gas turbine and in communication with the source of CO 2 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 CO 2 flows through the stator blade cooling system and returns to the source of CO 2 in a first closed loop and wherein a second portion of the flow of CO 2 flows through the rotor blade cooling system and returns to the source of CO 2 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 CO 2 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 CO 2 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 CO 2 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 CO 2 storage system.

Assignees

• Gen Electric

Inventors

• Muthuramalingam Mahendhra
• Anand Ashok Kumar
• Muthaiah Veerappan

Classifications

• F02C7/18

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title

• F01D25/12 Primary

  Cooling · CPC title