OPERATIONS SUPPORT SYSTEMS AND METHODS FOR CALCULATING AND EVALUATING TURBINE TEMPERATURES AND HEALTH

• US 20140163838A1
• Filed: 12/06/2012
• Published: 06/12/2014
• Est. Priority Date: 12/06/2012
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Moeckly, Kevin, Ling, Richard, Sandoval, Robert
• Granted Patent: US 9,317,249 B2
• Time in Patent Office: Days
• US Class Current: 701/100
• CPC Class Codes: F02C 9/00 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 Class Codes: F05D 2260/80 Diagnostics
• CPC Class Codes: F05D 2260/81 Modelling or simulation
• CPC Class Codes: G06F 7/00 Methods or arrangements for processing data by operating upon the order or content of the data handled logic circuits H03K19/00

Abstract

An operations support system is provided for an engine with a turbine having a turbine inlet. The system includes a diagnostic engine model unit configured to receive engine data from the engine and to generate diagnostics data based on the engine data, the diagnostics data including scalars. The system further includes an engine-specific model unit coupled to the diagnostic engine model unit and configured to receive the scalars from the diagnostic engine model unit and configured to generate turbine inlet temperature information for the engine using a thermodynamic model. The thermodynamic model is based on component maps associated with the engine. The system further includes a storage unit coupled to the engine-specific model unit and configured to store the turbine inlet temperature information.

Claims

1. An operations support system for an engine with a turbine having a turbine inlet, comprising:

a diagnostic engine model unit configured to receive engine data from the engine and to generate diagnostics data based on the engine data, the diagnostics data including scalars;

an engine-specific model unit coupled to the diagnostic engine model unit and configured to receive the scalars from the diagnostic engine model unit and configured to generate turbine inlet temperature information for the engine using a thermodynamic model, the thermodynamic model being based on component maps associated with the engine; and

a storage unit coupled to the engine-specific model unit and configured to store the turbine inlet temperature information.

2. The operations support system of claim 1, wherein the engine-specific model unit is configured to generate condition indicators based on the diagnostics data using the thermodynamic model.

3. The operations support system of claim 1, further comprising a graphical user interface coupled to the engine-specific model unit and configured to display the turbine inlet temperature information.

4. The operations support system of claim 1, further comprising a predictive model unit coupled to the engine-specific model unit and configured to evaluate the turbine inlet temperature information.

5. The operations support system of claim 4, wherein the predictive model unit is configured to generate prognostic indicators of components of the turbine based on turbine inlet temperature information.

6. The operations support system of claim 5, wherein further comprising a remaining useful life calculation unit coupled to the engine-specific model unit and configured to generate remaining useful life of the components of the turbine based on the turbine inlet temperature information.

7. The operations support system of claim 6, wherein the remaining useful life calculation unit is configured to generate a warning indication based on the remaining useful life of the components of the turbine.

8. The operations support system of claim 1, wherein the engine-specific model unit is configured to calibrate the calculation of the turbine inlet temperature information.

9. The operations support system of claim 1, wherein the engine-specific model unit is configured to calculate the turbine inlet temperature information in real-time.

10. The operations support system of claim 1, wherein the engine-specific model unit is configured to calculate the turbine inlet temperature information based on at least one of engine temperature, engine air pressure, engine air flow, engine fuel flow, and engine speed.

11. The operation support system of claim 1, wherein the engine-specific model unit is configured to continuously determine the turbine inlet temperature information of the engine.

12. The operations support system of claim 1, wherein the engine-specific model unit is further configured to adjust the thermodynamic model based on the scalars.

13. The operations support system of claim 12, wherein the thermodynamic model is an engine-specific model.

14. The operations support system of claim 13, wherein at least a portion of the scalars represent erosion within the engine.

15. A method for supporting operations of an engine with a turbine having a turbine inlet, comprising:

collecting engine data;

generating condition indicators from the engine data using a thermodynamic model based on component maps associated with the engine;

calculating turbine inlet temperature information of the engine from the condition indicators; and

storing the turbine inlet temperature information

16. The method of claim 15, further comprising displaying the turbine inlet temperature information on a graphical user display.

17. The method of claim 16, generating prognostic indicators of components of the turbine based on the turbine inlet temperature information.

18. The method of claim 17, wherein the generating step includes generating remaining useful life of the components of the turbine based on the turbine inlet temperature information.

19. The method of claim 18, further comprising

generating scalars from the engine data using the thermodynamic model;

and

adjusting the thermodynamic model based on the scalars.

20. The method of claim 19, wherein the calculating step includes continuously calculating a remaining useful life of the components of the engine.