Dynamically auto-tuning a gas turbine engine

• US 8,417,433 B2
• Filed: 03/22/2011
• Issued: 04/09/2013
• Est. Priority Date: 04/30/2010
• Status: Active Grant

• Current Assignee: H2 IP UK Limited
• Original Assignee: Alstom Technology Ltd. (Alstom SA)
• Inventors: Gauthier, Donald, Demougeot, Nicolas, Stuttaford, Peter, Rizkalla, Hany
• Primary Examiner(s): Tarcza, Thomas
• Assistant Examiner(s): MYHRE, KEVIN C
• Application Number:
  US13/053,910
• Publication Number:
  US 20110265487A1
• Time in Patent Office: 749 Days
• Field of Search: 701/100, 60/392.81, 607/73
• US Class Current: 701/100
• 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: F05D 2270/301 Pressure
• CPC Class Codes: F05D 2270/303 Temperature
• CPC Class Codes: F23N 1/002 using electronic means F23N1/04 - F23N1/10 take precedence
• CPC Class Codes: F23N 2237/02 two or more burners
• CPC Class Codes: F23N 2237/18 fluidized bed burners
• CPC Class Codes: F23N 2237/28 oxygen as pure oxydant
• 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 3/34 Feeding into different combustion zones

Abstract

Tuning processes implemented by an auto-tune controller are provided for measuring and adjusting the combustion dynamics and the emission composition of a gas turbine (GT) engine via a tuning process. Initially, the tuning process includes monitoring parameters, such as combustion dynamics and emission composition. Upon determining that one or more of the monitored parameters exceed a critical value, these “out-of-tune” parameters are compared to a scanning order table. Upon comparison, the first out-of-tune parameter that is matched within the scanning order table is addressed. The first out-of-tune parameter is then plotted as overlaid slopes on respective graphs, where the graph represents a fuel-flow split. Typically, the slopes are plotted as a particular out-of-tune parameter against a particular fuel-flow split. The slopes for each graph are considered together by taking into account the combined impact on each out-of-tune parameter when a fuel-flow split is selected for adjustment.

Claims

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

monitoring parameters of the GT engine during operation, wherein the parameters quantify at least one of combustion dynamics or emission composition;

detecting that a plurality of the monitored parameters exceed predetermined upper or lower limits;

identifying the plurality of monitored parameters that exceed the predetermined upper or lower limits as exhibiting an out-of-tune condition;

comparing the identified parameters against a scanning order table to determine which one of the identified parameters is highest ranked;

selecting a fuel-flow split for adjustment based, in part, on at least one of the identified parameters exhibiting the out-of-tune condition, wherein the process of selecting comprises;

(a) using graphical representations to evaluate a set of fuel-flow splits, wherein a graphical representation includes one or more slopes associated with a respective fuel-flow split, and wherein the one or more slopes correspond with a respective identified parameter plotted against tuning values of the respective fuel-flow split; and

(b) identifying a fuel-flow split that, upon incrementing its tuning values within an associated graphical representation, produces a greatest positive impact on the highest-ranked parameter and produces a least negative impact on a remainder of the identified parameters; and

incrementally adjusting the selected fuel-flow split a predefined amount.

2. The method of claim 1, wherein monitoring parameters of the GT engine comprises:

measuring the parameters of the GT engine as pressure signals; and

employing a transformative operation to convert the measured parameters into an amplitude versus frequency plot.

3. The method of claim 2, wherein detecting that a plurality of the monitored parameters exceed predetermined upper or lower limits comprises:

comparing a maximum amplitude of the pressure signals against a critical value associated with at least one combustor mode; and

detecting the maximum amplitude exceeds the critical value.

4. The method of claim 2, wherein employing a transformative operation to convert the measured parameters into an amplitude versus frequency plot comprises passing the pressure signals through a Fourier Transform to generate frequency readings associated with the pressure signals.

5. The method of claim 1, wherein identifying a fuel-flow split that produces a greatest positive impact on the highest-ranked parameter comprises:

inspecting the one or more slopes to identify a slope that, upon adjusting the tuning values of the respective fuel-flow split, most expeditiously moves the highest-ranked ranked parameter to a prescribed range between the predetermined upper and lower limits; and

recognizing a fuel-flow split corresponding to the identified slope.

6. The method of claim 1, wherein identifying a fuel-flow split that produces a least negative impact on a remainder of the identified parameters comprises:

inspecting the one or more slopes to identify a group of slopes within a single graphical representation that, upon adjusting the tuning values of the respective fuel-flow split, minimally degrades the remainder of the identified parameters with respect to a prescribed range between the predetermined upper and lower limits; and

recognizing a fuel-flow split corresponding to the identified group of slopes.

7. The method of claim 1, further comprising generating the graphical representations by a procedure comprising:

plotting data points of the identified parameters exhibiting the out-of-tune condition against the tuning values for a fuel-flow split within the set of fuel-flow splits;

forming the one or more slopes from the plotted data points; and

overlaying the one or more slopes associated with a particular fuel-flow split.

8. The method of claim 7, wherein the fuel-flow split governs a portion of a total fuel-flow that is directed to a fuel nozzle of the combustor'"'"'s fuel circuit.

9. The method of claim 1, further comprising verifying that the incremental adjusting to the selected fuel-flow split reduced the highest-ranked parameter to a prescribed range between the predetermined upper and lower limits.

10. The method of claim 9, wherein verifying comprises:

pausing for a period of time to allow the identified parameters to stabilize;

rerecording the pressure signals from the combustor; and

determining whether the amplitudes derived from the pressure signals moves the identified parameters to prescribed ranges between the predetermined upper and lower limits.

11. The method of claim 10, further comprising, upon incrementally adjusting the selected fuel-flow split a predefined amount, regenerating the one or more slopes associated with the fuel-slow splits using the parameters identified as exhibiting an out-of-tune condition upon stabilizing.

12. The method of claim 11, further comprising ceasing incrementally adjusting the selected fuel-flow split upon determining that the highest-ranked parameter has moved to a prescribed range between the predetermined upper and lower limits.

13. The method of claim 12, wherein incrementally adjusting the selected fuel-flow split a predefined amount comprises applying a uniform amount of adjustment to the selected fuel-flow split.

14. The method of claim 12, incrementally adjusting the selected fuel-flow split a predefined amount comprises applying a varying amount of adjustment to the selected fuel-flow split.

15. The method of claim 1, wherein the combustor dynamics that include at least one of lean blow out, cold tone, hot tone, or screech.

16. A computerized method, implemented by a processing unit, for generating one or more slopes used to dynamically tune a combustor of a gas turbine (GT) engine, the method comprising:

recording a plurality of operational conditions from the GT engine;

determining that a first operational condition and a second operational condition of the plurality of operational conditions are outside a prescribed range;

generating slopes for both the first and second operational conditions via a graphing process comprising;

(a) constructing a first slope associated with a particular fuel-flow split within a set of fuel-flow splits by plotting data points derived from the first operational condition against tuning values associated with the fuel flow split;

(b) constructing a second slope associated with the fuel-flow split by plotting data points derived from the second operational condition against the tuning values associated with the fuel flow split;

(c) overlaying the first slope and the second slope to form a graphical representation associated with the fuel-flow split; and

(d) repeating the graphing process for a remainder of the set of fuel-flow splits;

compiling graphical representations associated with the set of fuel-flow splits, respectively, within a slopes schedule; and

correcting the first and second operational conditions by employing the slopes schedule to select one of the set of fuel-flow splits for incremental adjustment.

17. The computerized method of claim 16, further comprising comparing the first and second operational conditions against a scanning order table to determine which one is highest ranked.

18. The computerized method of claim 17, wherein the scanning order table prioritizes the plurality of operational conditions and assigns a ranking to the operations conditions based on its priority.

19. The computerized method of claim 18, further comprising placing an enhanced importance on the first or second operational condition determined to be the highest ranked when employing the slopes schedule to select one of the set of fuel-flow splits for incremental adjustment.

20. One or more computer-readable media that, when invoked by computer-executable instructions, perform a method for dynamically auto-tuning a gas turbine (GT) engine, the method comprising:

detecting that one or more operating parameters have overcome a threshold value, wherein the one or more detected parameters exhibit an out-of-tune condition upon overcoming the threshold value;

comparing the one or more detected parameters against a scanning order table to determine which of the one or more detected parameters is first encountered within the scanning order table;

selecting a fuel-flow split for adjustment as a function of the one or more detected parameters via a process comprising;

(a) generating a set of slopes that are particular to a respective fuel-flow split, wherein a slope in the set of slopes corresponds with a respective detected parameter plotted against tuning values of the respective fuel-flow split; and

(b) identifying a fuel-flow split that, upon incrementing its tuning values along the set of slopes, produces a greatest positive impact on the first encountered parameter and produces a least negative impact on a remainder of the one or more detected parameters; and

initiating the adjustment of the selected fuel-flow split.