Operations support systems and methods for calculating and evaluating turbine temperatures and health

• US 9,317,249 B2
• Filed: 12/06/2012
• Issued: 04/19/2016
• 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
• Primary Examiner(s): Algahaim, Helal A
• Assistant Examiner(s): Han, Charles J
• Application Number:
  US13/707,174
• Publication Number:
  US 20140163838A1
• Time in Patent Office: 1,230 Days
• Field of Search: 701/99, 701/100, 701/101, 703/8
• US Class Current: 1/1
• 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;

a predictive model unit coupled to the engine-specific model unit and configured to evaluate the turbine inlet temperature information, wherein the predictive model unit is configured to generate prognostic indicators of components of the turbine based on turbine inlet temperature information; 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, 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, wherein the remaining useful life calculation unit is further configured to generate the remaining useful life based on rotation speed of the engine and cooling air flow temperature information paired with the turbine inlet temperature information.

5. The operations support system of claim 4, 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.

6. 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.

7. 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, and wherein the engine-specific model unit is further configured to generate turbine inlet temperature information based on engine operating conditions that are monitored and summed over time intervals to produce total time-at-temperature.

8. 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.

9. 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 at a specific rating condition of engine temperature, altitude, power, and installation configuration.

10. 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.

11. The operations support system of claim 10, wherein the thermodynamic model is an engine-specific model.

12. The operations support system of claim 11, wherein at least a portion of the scalars represent erosion within the engine.

13. 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 at a specific rating condition of engine temperature, altitude, power, and installation configuration;

evaluating the turbine inlet temperature information with a predictive model unit coupled to the engine-specific model unit, including generating prognostic indicators of components of the turbine based on turbine inlet temperature information; and

storing the turbine inlet temperature information.

14. The method of claim 13, further comprising displaying the turbine inlet temperature information on a graphical user display.

15. The method of claim 13, wherein the generating step includes generating remaining useful life of the components of the turbine based on the turbine inlet temperature information.

16. The method of claim 15, further comprising

generating scalars from the engine data using the thermodynamic model;

and

adjusting the thermodynamic model based on the scalars.

17. The method of claim 16, wherein the calculating step includes continuously calculating a remaining useful life of the components of the engine.