Method and system for gas turbine engine simulation using adaptive Kalman filter

• US 20070073525A1
• Filed: 09/27/2005
• Published: 03/29/2007
• Est. Priority Date: 09/27/2005
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (General Electric Company)
• Original Assignee: General Electric Company
• Inventors: Rosson, Randy, Healy, Timothy
• Granted Patent: US 7,742,904 B2
• Time in Patent Office: Days
• US Class Current: 703/7
• CPC Class Codes: G05B 13/04 involving the use of models or simulators
• CPC Class Codes: G05B 17/02 electric

Abstract

A method for simulating a gas turbine including the steps of: sensing values of a plurality of first operating parameters of an actual gas turbine; applying the sensed values of the first operating parameters to a model of the gas turbine, wherein the model generates a plurality of predicted second operating parameters; determining difference values between the predicted second operating parameters and corresponding sensed second operating parameters of the actual gas turbine; modifying the difference values based on tuning factors generated by a Kalman filter gain matrix during operation of the gas turbine, and using the adjusted difference values to adjust the model of the gas turbine. The method may further comprise generating the tuning factors by applying to the model the sensed values of the plurality of first operating parameters and pertubated values of the adjusted different values to determine optimal tuning factors.

Claims

1. A method for simulating a gas turbine comprising:

a. sensing values of a plurality of first operating parameters of an actual gas turbine;

b. applying the sensed values of the first operating parameters to a model of the gas turbine, wherein the model generates a plurality of predicted second operating parameters;

c. determining difference values between the predicted second operating parameters and corresponding sensed second operating parameters of the actual gas turbine;

d. modifying the difference values based on tuning factors generated by a Kalman filter gain matrix during operation of the gas turbine, and

e. using the adjusted difference values to adjust the model of the gas turbine.

2. The method of claim 1 further comprising applying a third operating parameter generated by the model to control the actual gas turbine.

3. The method of claim 1 wherein the adjusted difference values are used to generate correction factors for component efficiencies and flow capacities in the model.

4. The method of claim 1 wherein the tuning factors are generated in real-time during operation of the gas turbine.

5. The method of claim 1 further comprising removing at least one of the sensed values, and repeating steps (c) to (e).

6. The method of claim 1 wherein the tuning factors are gains applied to the difference values.

7. The method of claim 1 further comprising generating the tuning factors by applying to the model the sensed values of the plurality of first operating parameters and pertubated values of the adjusted different values to determine optimal tuning factors.

8. A method for simulating a gas turbine comprising:

a. sensing values of a plurality of input operating parameters of an actual gas turbine;

b. applying the sensed values of the first operating parameters to a model of the gas turbine that generates predicted values of a plurality of primary output operating parameters;

c. determining difference values by comparing the predicted values to sensed primary output operating parameters of the actual operating gas turbine;

d. adjusting the difference values based on tuning factors generated using a Kalman filter gain matrix during operation of the gas turbine, and

e. applying the adjusted difference values to adjust the model of the gas turbine, wherein the model generates at least one of predicted operating parameter applied to control the gas turbine;

f. after step (e) removing one of the difference value and repeating steps (a) through (e).

9. The method of claim 8 wherein in step (f) the removed difference value is removed due to a sensor failure.

10. The method in claim 8 wherein the adjusted difference values are used to generate correction factors for component efficiencies and flow capacities in the model.

11. The method of claim 8 wherein the tuning factors are generated in real-time during operation of the actual gas turbine.

12. The method of claim 8 wherein the tuning factors are gains applied to the difference values.

13. The method of claim 8 further comprising generating the tuning factors by applying the sensed values of the plurality of first operating parameters and pertubated adjusted difference values to determine a sensitivity of the model to the first operating parameters.

14. The method as in claim 13 wherein the sensitivity is applied to determine the tuning factors.

15. A control and modeling system for simulating an operating gas turbine comprising:

sensors generating sensed values of a plurality of first operating parameters of the gas turbine;

a controller including a mathematical model of the operating gas turbine receiving the sensed values of the first operating parameters and a plurality of correction factors, wherein the model generates a plurality of predicted second operating parameters;

a comparator determining difference values between the predicted second operating parameters and corresponding sensed operation parameters of the operating gas turbine; and

said controller further includes a Kalman filter gain matrix generating tuning factors to be applied to the difference values to generate the correction factors.

16. The system of claim 15 wherein the third operating parameter is applied to control the actual gas turbine.

17. The system of claim 15 wherein the adjusted difference values are used to generate correction factors for component efficiencies and flow capacities in the model.

18. The system of claim 15 wherein the tuning factors are generated in real-time during operation of the gas turbine.

19. The system of claim 15 wherein the Kalman filter gain matrix generates the correction factor adjustments by applying the sensed values of the plurality of first operating parameters and a series of pertubated values of the predicted second operating parameters.

20. The system of claim 15 wherein the controller is a computer controller for the gas turbine.