SYSTEMS AND METHODS FOR BULK TEMPERATURE VARIATION REDUCTION OF A GAS TURBINE THROUGH CAN-TO-CAN FUEL TEMPERATURE MODULATION

• US 20130014514A1
• Filed: 07/14/2011
• Published: 01/17/2013
• Est. Priority Date: 07/14/2011
• Status: Abandoned Application

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Romig, Bryan Wesley, Ziminsky, Willy Steve, Simons, Derrick Walter
• Application Number:
  US13/182,956
• Publication Number:
  US 20130014514A1
• Time in Patent Office: Days
• US Class Current: 60/776
• CPC Class Codes: F02C 7/224 Heating fuel before feeding to the burner
• CPC Class Codes: F23K 2300/204 Preheating
• CPC Class Codes: F23K 5/20 Preheating devices in burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space F23D11/44
• CPC Class Codes: F23R 2900/00013 Reducing thermo-acoustic vibrations by active means
• CPC Class Codes: F23R 3/28 characterised by the fuel supply burners F23D
• CPC Class Codes: F23R 3/46 Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings

Abstract

A gas turbine includes a plurality of combustion chambers; at least one fuel nozzle for each of the combustion chambers; at least one fuel line for each fuel nozzle in each of the combustion chambers; at least one heat exchanger for each fuel line configured to adjust a temperature of a fuel flow to each fuel nozzle; and a controller configured to control each of the heat exchangers to reduce temperature variations amongst the combustion chambers.

Claims

1. A gas turbine, comprising:

a plurality of combustion chambers;

at least one fuel nozzle for each of the combustion chambers;

at least one fuel line for each fuel nozzle in each of the combustion chambers;

at least one heat exchanger for each fuel line configured to adjust a temperature and an amount of a fuel flow to each fuel nozzle; and

a controller configured to control each of the heat exchangers to reduce temperature variations amongst the combustion chambers.

2. The gas turbine of claim 1, further comprising a plurality of manifolds, wherein a plurality of fuel lines extend from each manifold to the fuel nozzles in each of the combustion chambers.

3. The gas turbine of claim 2, wherein the plurality of manifolds have different fuel capacities.

4. The gas turbine according to claim 2, wherein at least one of the manifolds of the plurality of manifolds is configured to provide purge gas to at least one fuel nozzle of each combustion chamber.

5. The gas turbine of claim 1, further comprising a plurality of sensors for measuring a condition of exhaust gas from the plurality of combustion chambers.

6. The gas turbine of claim 5, wherein the plurality of sensors comprises a plurality of temperature sensors configured to sense temperatures at different regions of an exhaust outlet of the turbine, and the controller correlates the sensed exhaust temperatures to fuel flow to individual combustion chambers and controls the heat exchangers to modify a profile of exhaust gas temperatures.

7. The gas turbine of claim 6, wherein the controller controls each heat exchanger so that a temperature variation of each combustion chamber from an average temperature sensed by the plurality of sensors is about one percent or less.

8. The gas turbine of claim 1, wherein the plurality of sensors comprises at least one dynamic pressure sensor for each combustion chamber, and the controller correlates dynamic pressure oscillations to fuel flow to individual combustion chambers and the controller controls the heat exchangers to reduce deviations in cold tones for individual combustion chambers from an average cold tone of the turbine.

9. The gas turbine of claim 8, wherein the controller is configured to adjust cold tone deviations in order from largest to smallest.

10. The gas turbine of claim 1, wherein the plurality of sensors comprises at least one emission sensor for each combustion chamber for sensing emission levels at different regions of an exhaust outlet of the turbine, and the controller correlates the emission levels to fuel flow to individual combustion chambers and controls the heat exchangers to modify a profile of emission levels.

11. The gas turbine of claim 10, wherein the controller controls the heat exchangers to reduce an emission level variation of each combustion chamber from an average emission level.

12. The gas turbine of claim 10, wherein the plurality of sensors comprise CO sensors.

13. The gas turbine of claim 10, wherein the plurality of sensors comprise unburned hydrocarbon sensors.

14. The gas turbine of claim 10, wherein the plurality of sensors comprise NOx sensors.

15. A method of controlling fuel flow to individual combustion chambers of a gas turbine, comprising:

measuring exhaust gas temperatures and/or emission levels at a plurality of exhaust regions of the gas turbine;

correlating one of the measured exhaust gas temperatures and/or emission levels to fuel flow to individual combustion chambers; and

adjusting a temperature and an amount of the fuel flow to each individual combustion chamber to reduce a temperature level variation and/ or an emission level variation of each combustion chamber from an average temperature level and/or an average emission level.

16. The method of claim 15, wherein the temperatures of the fuel flow to the individual combustion chambers are adjusted so that a temperature variation of each combustion chamber from an average temperature is one percent or less.

17. The method of claim 15, wherein the emission levels comprise CO, unburned hydrocarbon, and/or NOx emission levels.

18. A method of controlling fuel flow to individual combustion chambers of a gas turbine, comprising:

determining a cold tone for each combustion chamber;

correlating the cold tone of each combustion chamber to a fuel flow to each combustion chamber; and

adjusting a temperature and an amount of the fuel flow to each combustion chamber to reduce a cold tone deviation of each combustion chamber from an average cold tone of the gas turbine.

19. A method according to claim 18, further comprising adjusting the cold tone deviations in order from largest to smallest.