Stabilizing a gas turbine engine via incremental tuning

• US 9,097,185 B2
• Filed: 05/24/2010
• Issued: 08/04/2015
• Est. Priority Date: 05/26/2009
• Status: Active Grant

• Current Assignee: H2 IP UK Limited
• Original Assignee: Alstom Technology Ltd. (Alstom SA)
• Inventors: Demougeot, Nicolas, Gauthier, Donald, Rizkalla, Hany, Stuttaford, Peter, Oumejjoud, Khalid
• Primary Examiner(s): Wongwian, Phutthiwat
• Assistant Examiner(s): Mantyla, Michael B
• Application Number:
  US12/786,189
• Publication Number:
  US 20100300108A1
• Time in Patent Office: 1,898 Days
• Field of Search: 60/392.81, 607/73, 607/76, 731/120.1, 731/120.3, 702/77, 702/85, 702/104, 702/107, 701/100
• US Class Current: 1/1
• 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: F02C 9/32 characterised by throttling of fuel F02C9/38 takes precedence
• CPC Class Codes: F02C 9/34 Joint control of separate flows to main and auxiliary burners
• CPC Class Codes: F05D 2270/082 with as little NOx as possible
• CPC Class Codes: F05D 2270/301 Pressure
• CPC Class Codes: F05D 2270/31 Fuel schedule for stage combustors
• CPC Class Codes: F23N 2241/20 Gas turbines
• CPC Class Codes: F23R 2900/00013 Reducing thermo-acoustic vibrations by active means
• CPC Class Codes: F23R 3/343 Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion ignition in gas-turbine plants F02C7/264; pilot flame igniters F23Q9/00
• CPC Class Codes: F23R 3/346 for staged combustion

Abstract

An auto-tune controller and tuning process implemented thereby for measuring and tuning the combustion dynamics and emissions of a GT engine, relative to predetermined upper limits, are provided. Initially, the tuning process includes monitoring the combustion dynamics of a plurality of combustors and emissions for a plurality of conditions. Upon determination that one or more of the conditions exceeds a predetermined upper limit, a fuel flow split to a fuel circuit on all of the combustors on the engine is adjusted by a predetermined amount. The control system continues to monitor the combustion dynamics and to recursively adjust the fuel flow split by the predetermined amount until the combustion dynamics and/or emissions are operating within a prescribed range of the GT engine.

Claims

1. A computerized method, implemented by a processing unit, for automatically tuning a combustor of a gas turbine engine, the method comprising:

monitoring at least one operating condition of the gas turbine engine;

determining that the at least one operating condition overcomes a threshold value associated with the at least one operating condition; and

based on determining that the at least one operating condition overcomes the threshold value, performing a tuning process comprising;

(a) comparing an identity of the at least one operating condition against a schedule, the schedule providing, for the at least one operating condition, an identity of a predefined fuel flow split for adjustment and a predefined manner of adjustment for the predefined fuel flow split;

(b) selecting the predefined fuel flow split corresponding to the at least one operating condition from the schedule to target for adjustment, wherein selecting the predefined fuel flow split is based on (1) the identity of the at least one operating condition, (2) a predefined preferential guideline, and (3) a look-up table comprising an operating curve that corresponds to an ambient temperature parameter and a gas parameter;

(c) adjusting the selected predefined fuel flow split by a predefined increment according to the predefined manner of adjustment, wherein the selected predefined fuel flow split governs a portion of a total fuel flow that is directed to two or more fuel nozzles of the combustor'"'"'s fuel circuit, and wherein adjusting the selected predefined fuel flow split by the predefined increment comprises consistently applying a uniform amount of adjustment to the selected predefined fuel flow split;

obtaining a result of the tuning process; and

updating the look-up table based on the result of the tuning process, wherein the updated look-up table increases an efficiency of a future tuning process.

2. The method of claim 1, wherein monitoring the at least one operating condition of the gas turbine engine comprises:

recording pressure pulses of the combustor; and

passing the recorded pressure pulses through a Fourier Transform to form frequency readings associated with the recorded pressure pulses.

3. The method of claim 2, wherein determining that the at least one operating condition overcomes the threshold value comprises:

comparing a maximum amplitude of the pressure pulses against predetermined upper limits associated with at least one combustor mode; and

detecting the maximum amplitude exceeds at least one of the predetermined upper limits.

4. The method of claim 3, further comprising verifying that the adjustment to the selected predefined fuel flow split reduced the at least one operating condition corresponding to the selected predefined fuel flow split below the threshold value.

5. The method of claim 4, wherein the verifying comprises:

pausing for a period of time such that the at least one operating condition corresponding to the selected predefined fuel flow split stabilizes;

rerecording the pressure pulses of the combustor; and

determining whether a subsequent maximum amplitude, derived from the rerecorded pressure pulses, exceeds at least one of the predetermined upper limits.

6. The method of claim 5, further comprising, when it is determined that the subsequent maximum amplitude exceeds the at least one of the predetermined upper limits, implementing another adjustment of the selected predefined fuel flow split by the predefined increment.

7. The method of claim 5, further comprising, when it is determined that the subsequent maximum amplitude falls within an acceptable operating range, ceasing adjustment of the selected predefined fuel flow split.

8. The method of claim 1, wherein the uniform amount of adjustment consistently applied to the selected predefined fuel flow split is based on the identity of the selected predefined fuel flow split presently being adjusted.

9. The method of claim 1, wherein the at least one operating condition comprises emissions of the gas turbine engine.

10. The method of claim 1, wherein the at least one operating condition comprises combustor dynamics that include lean blow out, cold tone, hot tone, and screech.

11. The method of claim 1, wherein adjusting the selected predefined fuel flow split by the predefined increment comprises making a determination to either increase or decrease the selected predefined fuel flow split based on the schedule.

12. The method of claim 1, wherein adjusting the selected predefined fuel flow split by the predefined increment comprises making a determination to either increase or decrease the selected predefined fuel flow split as a function of the identity of the predefined fuel flow split selected for adjustment.

13. A system comprising:

a gas turbine engine including one or more combustors, wherein fuel flow splits govern a flow of fuel through fuel circuits for the one or more combustors; and

an auto-tune controller for controlling an auto-tuning process comprising;

monitoring at least one operating condition of the gas turbine engine,

determining the at least one operating condition overcomes a threshold value,

based on determining that the at least one operating condition overcomes the threshold value, comparing an identity of the at least one operating condition against a schedule, the schedule providing, for the at least one operating condition, an identity of a predefined fuel flow split for adjustment and a predefined manner of adjustment for the predefined fuel flow split,

determining a selected fuel flow split to target for adjustment, wherein determining the selected fuel flow split to target for adjustment is based on (1) the identity of the at least one operating condition, (2) a predefined preferential guideline, and (3) a look-up table comprising an operating curve that corresponds to an ambient temperature parameter and a gas parameter,

adjusting the selected predefined fuel flow split by a predefined increment according to the predefined manner of adjustment, wherein the selected predefined fuel flow split governs a portion of a total fuel flow that is directed to two or more fuel nozzles of the combustor'"'"'s fuel circuit, and wherein adjusting the selected predefined fuel flow split by the predefined increment comprises consistently applying a uniform amount of adjustment to the selected predefined fuel flow split;

obtaining a result of adjusting the selected predefined fuel flow split; and

updating the look-up table based on the result of adjusting the selected predefined fuel flow split, wherein the updated look-up table increases an efficiency of a future auto-tuning process.

14. The system of claim 13, wherein the auto-tuning process further comprises utilizing the schedule to determine an incremental amount to adjust the selected predefined fuel flow split.

15. The system of claim 14, wherein the auto-tuning process further comprises:

upon making the adjustment to the selected predefined fuel flow split, determining a number of adjustments recursively made to the selected predefined fuel flow split; and

when the number of recursive adjustments reaches an allowable number of iterations, taking an action prescribed by the schedule.

16. The system of claim 15, wherein the action prescribed by the schedule includes selecting and adjusting a different fuel flow split.

17. The system of claim 13, wherein the auto-tuning process further comprises utilizing the schedule to determine a direction in which to make the adjustment to the selected predefined fuel flow split.

18. One or more computer readable media that, when invoked by computer-executable instructions, perform a method for auto-tuning a combustor of a gas turbine engine, the method comprising:

monitoring a plurality of operating conditions of the gas turbine engine;

determining that at least one of the plurality of operating conditions overcomes a threshold value;

based on determining that the at least one of the plurality of operating conditions overcomes the threshold value, performing a tuning process comprising;

(a) comparing an identity of the at least one of the plurality of operating conditions against a schedule, the schedule providing, for the at least one of the plurality of operating conditions, an identity of a predefined fuel flow split for adjustment and a predefined manner of adjustment for the predefined fuel flow split,

(b) selecting the predefined fuel flow split corresponding to the at least one of the plurality of operating conditions from the schedule to target for adjustment, wherein selecting the predefined fuel flow split is based on (1) the identity of the at least one of the plurality of operating conditions, (2) a predefined preferential guideline, and (3) a look-up table comprising an operating curve that corresponds to an ambient temperature parameter and a gas parameter; and

(c) adjusting the predefined fuel flow split by a predefined increment according to the predefined manner of adjustment, wherein the predefined fuel flow split governs a portion of a total fuel flow that is directed to two or more fuel nozzles of the combustor'"'"'s fuel circuit, and wherein adjusting the predefined fuel flow split by the predefined increment comprises consistently applying a uniform amount of

adjustment to the predefined fuel flow split;

obtaining a result of the tuning process; and

updating the look-up table based on the result of the tuning process, wherein the updated look-up table increases an efficiency of a future tuning process.

19. A computerized method, implemented by a processing unit, for automatically turning a gas turbine engine, the method comprising:

monitoring a plurality of operating conditions of the gas turbine engine;

determining that at least one of the plurality of operating conditions overcomes a threshold value;

based on determining that the at least one of the plurality of operating conditions overcomes the threshold value, performing a tuning process comprising;

comparing an identity of the at least one of the plurality of operating conditions against a schedule, the schedule providing, for the at least one of the plurality of operating conditions, an identity of a predefined fuel flow split for adjustment and a predefined manner of adjustment for the predefined fuel flow split,

selecting the predefined fuel flow split corresponding to the at least one of the plurality of operating conditions from the schedule to target for adjustment, wherein selecting the predefined fuel flow split is based on (1) the identity of the at least one of the plurality of operating conditions (2) a predefined preferential guideline, and (3) a look-up table comprising an operating curve that corresponds to an ambient temperature parameter and a gas parameter, and

adjusting the selected predefined fuel flow split by a predefined increment according to the predefined manner of adjustment, wherein the selected predefined fuel flow split governs a portion of a total fuel flow that is directed to two or more fuel nozzles of the combustor'"'"'s fuel circuit, and wherein adjusting the selected predefined fuel flow split by the predefined increment comprises consistently applying a uniform amount of adjustment to the selected predefined fuel flow split;

obtaining a result of the tuning process; and

updating the look-up table based on the result of the tuning process, wherein the updated look-up table increases an efficiency of a future tuning process.