Method for controlling a gas turbine by means of a future combustion dynamic

Patent metadata

Field	Value
Publication number	US-11898501-B2
Application number	US-202017442820-A
Country	US
Kind code	B2
Filing date	Mar 18, 2020
Priority date	Mar 29, 2019
Publication date	Feb 13, 2024
Grant date	Feb 13, 2024

Abstract

A method for controlling a gas turbine, having a measurement step, a prediction step which is carried out after the measurement step, and a control step which is carried out after the prediction step. In the measurement step, a state variable of a combustion within a gas turbine is measured. In the prediction step, a future combustion dynamic is predicted using the measured state variable. In the control step, a control signal is output using the prediction of the future combustion dynamic.

First claim

The invention claimed is:

1. A method for controlling a gas turbine, comprising:
measuring a state variable of a combustion within the gas turbine in a measuring step;
predicting a future combustion dynamic by means of the measured state variable in a predicting step; and
emitting a control signal by means of the prediction of the future combustion dynamic in a controlling step;
wherein a basic state process, a noise process and a peak process are taken into account in the predicting step so as to predict the future combustion dynamic.

2. The method as claimed in claim 1 ,
wherein a current combustion dynamic is determined from the measured state variable in a determining step, and the prediction of the future combustion dynamic by means of the measured state variable in the predicting step takes place while taking into account the current combustion dynamic.

3. The method as claimed in claim 2 ,
wherein the current combustion dynamic comprises a profile of the combustion dynamic in a first predefined period.

4. The method as claimed in claim 2 ,
wherein a plurality of current combustion dynamics are determined from a plurality of future combustion dynamics, wherein control signals to be emitted are established by means of the plurality of future combustion dynamics in an establishing step, and wherein the emission of the control signals in the controlling step takes place in such a manner that the control signal to be emitted is selected by means of a currently determined combustion dynamic.

5. The method as claimed in claim 1 ,
wherein the future combustion dynamic comprises a prediction pertaining to a profile of the combustion dynamic in a second predefined period.

6. The method as claimed in claim 1 ,
wherein the basic state process is a variation of an acceleration value within the gas turbine over time by virtue of different gas turbine states;
wherein the noise process includes a random distribution of a noise amplitude over time; and
wherein the peak process comprises individual peaks that indicate peak values of an acceleration within the gas turbine at one or more specific times.

7. The method as claimed in claim 1 ,
wherein the basic state process, the noise process and the peak process in the predicting step are predicted by means of a Bayesian model.

8. The method as claimed in claim 1 ,
wherein the basic state process, the noise process and the peak process are considered to be additive.

9. The method as claimed in claim 1 ,
wherein the peak process is modeled as a discrete function.

10. The method as claimed in claim 1 ,
wherein the basic state process is modeled as a continuous function.

11. The method as claimed in claim 1 ,
wherein a quantity of a fuel introduced into the gas turbine and/or a ratio of the fuel introduced into the gas turbine at different locations and/or an exhaust gas temperature can be varied by means of the control signal.

12. The method as claimed in claim 1 ,
wherein the control signal is emitted by means of a target parameter or a combination of target parameters, wherein at least one target parameter is established by means of an emission value and/or by means of a combustion stability and/or by means of an efficiency of a combustion.

13. A non-transitory computer readable medium, comprising:
a computer program stored thereon having commands which when executed by a computer carries out the method as claimed in claim 1 .

14. A control unit, comprising:
an input for measuring a state variable,
an output for emitting a control signal, and
a computer unit, wherein the computer unit is adapted for carrying out the method of claim 1 .

15. A gas turbine comprising:
a control unit as claimed in claim 14 .

16. The method as claimed in claim 1 , wherein the state variable is at least one of:
a temperature within the gas turbine;
an air pressure within or outside the gas turbine;
an air humidity within or outside the gas turbine; and
a vibration within the gas turbine.

17. The method as claimed in claim 1 , further comprising preventing specific accelerations in the future combustion dynamic that damage or destroy the gas turbine, based on the control signal of the emitting step.

18. The method as claimed in claim 1 ,
wherein the measuring the state variable comprises measuring, with one or more sensors, a value of the state variable;
wherein the method further comprises transmitting, from the sensors to an input of a controller, data that indicates the measured state variable; and
wherein the emitting the control signal comprises emitting, from an output of the controller to one or more fuel intakes of the gas turbine, the control signal to vary an amount of fuel input at the respective one or more fuel intakes.

19. The method as claimed in claim 2 , further comprising:
dividing the current combustion dynamic into the basic state process, the noise process and the peak process;
predicting a future profile of the basic state process, the noise process and the peak process; and
determining the future combustion dynamic based on the future profile of the basic state process, the noise process and the peak process.

20. The method as claimed in claim 6 , wherein the controlling step comprises identifying one or more of the individual peaks of the peak process whose peak values of acceleration exceed a limit value of acceleration and wherein the emitted control signal prevents the identified one or more individual peak values of acceleration within the gas turbine.

Assignees

• Siemens Energy Global Gmbh & Co Kg

Inventors

• Kaiser Markus
• Heesche Kai

Classifications

• F02C9/26 Primary

  Control of fuel supply (F02C9/48 takes precedence; fuel valves F02C7/232) · CPC title

• F02C9/28

  Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed (F02C9/30 - F02C9/38, F02C9/44 take precedence) · CPC title

• F23R3/00 Primary

  Continuous combustion chambers using liquid or gaseous fuel · CPC title

• F02C9/00

  Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants (controlling air intakes F02C7/057; controlling turbines F01D; controlling compressors F04D27/00; controlling in general G05) · CPC title

• F05D2260/964

  counteracting thermoacoustic noise · CPC title