METHODS FOR CONTROLLING FUEL SPLITS TO A GAS TURBINE COMBUSTOR

• US 20120023953A1
• Filed: 07/27/2010
• Published: 02/02/2012
• Est. Priority Date: 07/27/2010
• Status: Abandoned Application

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Thomas, Stephen Robert, Childers, Priscilla Graves, Duraibabu, Vamsi
• Application Number:
  US12/844,280
• Publication Number:
  US 20120023953A1
• Time in Patent Office: Days
• US Class Current: 60/772
• CPC Class Codes: F02C 7/228 Dividing fuel between various burners
• CPC Class Codes: F02C 9/28 Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed F02C9/30 - F02C9/38, F02C9/44 take precedence
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

Methods for controlling fuel splits to a combustor of a gas turbine are disclosed. The methods may include determining a combustion reference temperature of the gas turbine, measuring a biasing parameter of the gas turbine, determining at least one fuel split biasing value based on the combustion reference temperature and the biasing parameter and adjusting a nominal fuel split schedule based on the at least one fuel split biasing value.

Claims

1. A method for controlling fuel splits to a combustor of a gas turbine, the method comprising:

determining a combustion reference temperature of the gas turbine;

measuring an inlet guide vane angle of the gas turbine;

determining at least one fuel split biasing value based on the combustion reference temperature and the inlet guide vane angle; and

adjusting a nominal fuel split schedule of the gas turbine based on the at least one fuel split biasing value.

2. The method of claim 1, wherein determining the at least one fuel split biasing value comprises locating the combustion reference temperature and the inlet guide vane angle in at least one lookup table.

3. The method of claim 2, wherein the at least one lookup table is stored within a controller of the gas turbine such that the at least one fuel split biasing value is determined automatically.

4. The method of claim 1, wherein determining the at least one fuel split biasing value comprises inputting the combustion reference temperature and the inlet guide vane angle into at least one correlated mathematical function.

5. The method of claim 4, wherein the at least one correlated mathematical function is stored within a controller of the gas turbine such that the at least one fuel split biasing value is determined automatically.

6. The method of claim 1, further comprising measuring at least one secondary biasing parameter of the gas turbine, wherein the at least one fuel split biasing value is determined based on the combustion reference temperature, the inlet guide vane angle and the at least one secondary biasing parameter.

9. The method of claim 1, wherein the at least one fuel split biasing value comprises a percentage change of a total fuel flow into the combustor, the nominal fuel split schedule being adjusted by summing the at least one fuel split biasing value with at least one fuel split percentage of the nominal fuel split schedule.

10. The method of claim 1, wherein adjusting the nominal fuel split schedule comprises automatically adjusting the nominal fuel split schedule with a controller of the gas turbine.

11. The method of claim 1, wherein measuring the inlet guide vane angle comprises automatically measuring the inlet guide vane angle using a sensor in communication with a controller of the gas turbine.

12. The method of claim 1, wherein determining the combustion reference temperature comprises automatically determining the combustion reference temperature with a controller of the gas turbine.

7. The method of claim 7, wherein determining the at least one fuel split biasing value comprises locating the combustion reference temperature, the inlet guide vane angle, and the at least one secondary biasing parameter in at least one lookup table or inputting the combustion reference temperature, the inlet guide vane angle and the secondary biasing parameter into at least one correlated mathematical function.

8. The method of claim 7, wherein the at least one secondary biasing parameter comprises at least one of compressor discharge pressure, compressor inlet temperature, compressor pressure ratio, compressor discharge temperature, ambient temperature, compressor inlet air mass flow, gaseous fuel flow and liquid fuel flow.

13. A method for controlling fuel splits to a combustor of a gas turbine, the method comprising:

determining a combustion reference temperature of the gas turbine;

measuring an inlet guide vane angle of the gas turbine;

measuring at least one secondary biasing parameter of the gas turbine;

determining at least one fuel split biasing value based on the combustion reference temperature, the inlet guide vane angle and the at least one secondary biasing parameter; and

adjusting a nominal fuel split schedule of the gas turbine based on the at least one fuel split biasing value.

14. The method of claim 13, wherein determining the at least one fuel split biasing value comprises automatically determining the at least one fuel split biasing value by locating the combustion reference temperature, the inlet guide vane angle and the secondary biasing parameter in at least one lookup table, wherein the at least one lookup table is stored within a controller of the gas turbine.

15. The method of claim 13, wherein determining the at least one fuel split biasing value comprises automatically determining the at least one fuel split biasing value by inputting the combustion reference temperature, the inlet guide vane angle and the secondary biasing parameter into at least one correlated mathematical function, wherein the at least one correlated mathematical function is stored within a controller of the gas turbine.

16. The method of claim 13, wherein the at least one secondary biasing parameter comprises at least one of compressor discharge pressure, compressor inlet temperature, compressor pressure ratio, compressor discharge temperature, ambient temperature, compressor inlet air mass flow, gaseous fuel flow and liquid fuel flow.

17. A method for controlling fuel splits to a combustor of a gas turbine, the method comprising:

determining a combustion reference temperature of the gas turbine;

measuring a biasing parameter of the gas turbine, wherein the biasing parameter is a parameter selected from the group consisting of inlet guide vane angle, compressor discharge pressure, compressor pressure ratio, compressor discharge temperature, ambient temperature, compressor inlet air mass flow, gaseous fuel flow and liquid fuel flow;

determining at least one fuel split biasing value based on the combustion reference temperature and the biasing parameter; and

adjusting a nominal fuel split schedule based on the at least one fuel split biasing value.

18. The method of claim 17, wherein determining the at least one fuel split biasing value comprises locating the combustion reference temperature and the biasing parameter in at least one lookup table.

19. The method of claim 17, wherein determining the at least one fuel split biasing value comprises inputting the combustion reference temperature and the biasing parameter into a correlated mathematical function.

20. The method of claim 17, further comprising measuring at least one secondary biasing parameter of the gas turbine, wherein the at least one fuel split biasing value is determined based on the combustion reference temperature, the biasing parameter and the at least one secondary biasing parameter.