SYSTEM AND METHOD FOR MODIFYING ROTOR THRUST

• US 20110027064A1
• Filed: 08/03/2009
• Published: 02/03/2011
• Est. Priority Date: 08/03/2009
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: GARCIA-CRESPO, ANDRES JOSE, PAL, DIPANKAR
• Granted Patent: US 8,434,994 B2
• Time in Patent Office: Days
• US Class Current: 415/1
• CPC Class Codes: F01D 3/00 Machines or engines with axial-thrust balancing effected by working-fluid
• CPC Class Codes: F02C 3/06 the compressor comprising only axial stages F02C3/10 takes precedence

Abstract

A gas turbine includes a compressor, a turbine downstream of the compressor having stators, and a rotor connecting the compressor to the turbine. The rotor includes rotor cavities. A supply plenum containing a process by-product gas and a control valve is connected to at least one of the rotor cavities to supply the process by-product gas to at least one of the rotor cavities. A process for operating a gas turbine having a compressor and a turbine includes connecting the compressor to the turbine by a rotor, creating cavities in the rotor, and injecting a process by-product gas into at least one of the cavities. The process further includes regulating the flow of the process by-product gas into at least one of the cavities according to a pre-programmed parameter.

Claims

1. A gas turbine, comprising:

a. a compressor;

b. a turbine downstream of the compressor, wherein the turbine includes a plurality of stators;

c. a rotor connecting the compressor to the turbine, the rotor including a plurality of rotor cavities; and

d. a supply plenum containing a process by-product gas, wherein the supply plenum includes a control valve and is connected to at least one of the rotor cavities to supply the process by-product gas to at least one of the rotor cavities.

2. The gas turbine of claim 1, wherein the supply plenum is connected to multiple rotor cavities.

3. The gas turbine of claim 1, wherein the supply plenum is connected to at least one of the rotor cavities through at least one stator.

4. The gas turbine of claim 1, further including a controller for regulating the flow of the process by-product gas to at least one of the rotor cavities.

5. The gas turbine of claim 4, wherein the controller regulates the flow of the process by-product gas to at least one of the rotor cavities according to a rotor cavity pressure or temperature.

6. The gas turbine of claim 4, wherein the controller regulates the flow of the process by-product gas to at least one of the rotor cavities according to a power level of the turbine.

7. The gas turbine of claim 4, further including a thrust bearing connected to the rotor, wherein the controller regulates the flow of the process by-product gas to at least one of the rotor cavities according to a force on the thrust bearing.

8. A gas turbine, comprising:

a. a compressor;

b. a turbine downstream of the compressor, wherein the turbine includes a plurality of stators;

c. a rotor connecting the compressor to the turbine, the rotor including a plurality of rotor cavities;

d. a supply plenum containing a process by-product gas, wherein the supply plenum is connected to at least one of the rotor cavities to supply the process by-product gas to at least one of the rotor cavities; and

e. a controller for regulating the flow of the process by-product gas to at least one of the rotor cavities.

9. The gas turbine of claim 8, wherein the supply plenum is connected to multiple rotor cavities.

10. The gas turbine of claim 8, wherein the supply plenum is connected to at least one of the rotor cavities through at least one stator.

11. The gas turbine of claim 8, further including a pressure or temperature sensor in at least one of the plurality of rotor cavities.

12. The gas turbine of claim 8, further including a thrust bearing connected to the rotor, wherein the controller regulates the flow of the process by-product gas to at least one of the rotor cavities according to a force on the thrust bearing.

13. The gas turbine of claim 8, further including a signal reflective of a power level of the turbine, supplied to the controller.

14. The gas turbine of claim 8, further including a control valve in the supply plenum.

15. A process for operating a gas turbine having a compressor and a turbine, comprising:

a. connecting the compressor to the turbine by a rotor;

b. creating a plurality of cavities in the rotor;

c. injecting a process by-product gas into at least one of the plurality of cavities; and

d. regulating the flow of the process by-product gas into at least one of the plurality of cavities according to a pre-programmed parameter.

16. The process of claim 15, further including receiving the process by-product gas into at least one of the plurality of cavities through the rotor.

17. The process of claim 15, further including receiving the process by-product gas into at least one of the plurality of cavities through a stator in the turbine.

18. The process of claim 15, further including regulating the flow of the process by-product gas into at least one of the plurality of cavities according to a pressure or temperature in the cavities.

19. The process of claim 15, further including regulating the flow of the process by-product gas into at least one of the plurality of cavities according to a power level of the turbine.

20. The process of claim 15, further including regulating the flow of the process by-product gas into at least one of the plurality of cavities according to a force on the rotor.