Life management system and method for gas turbine thermal barrier coatings

• US 8,510,060 B2
• Filed: 06/07/2010
• Issued: 08/13/2013
• Est. Priority Date: 06/07/2010
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Hardwicke, Canan Uslu, Pandey, Achalesh Kumar, Vittal, Sameer, Singh, Jagmeet, Nanda, Subrat
• Primary Examiner(s): Kundu, Sujoy
• Assistant Examiner(s): BETSCH, REGIS J
• Application Number:
  US12/795,089
• Publication Number:
  US 20110296810A1
• Time in Patent Office: 1,163 Days
• Field of Search: 702/34, 702/113, 60/390.91
• US Class Current: 702/34
• CPC Class Codes: F01D 21/003 Arrangements for testing or measuring for measuring vibrations G01H
• CPC Class Codes: F01D 21/14 responsive to other specific conditions
• CPC Class Codes: F05D 2270/11 to prolong engine life
• CPC Class Codes: G05B 23/0283 Predictive maintenance, e.g. involving the monitoring of a system and, based on the monitoring results, taking decisions on the maintenance schedule of the monitored system; Estimating remaining useful life [RUL] preventive maintenance, i.e. planning maintenance according to the available resources without monitoring the system G06Q10/06

Abstract

A method, system and computer program product for life management and monitoring of a high temperature gas turbine including components having a thermal barrier coating is disclosed. The method, system and computer program product uses design, monitoring and diagnostics, and inspection data to determine the cumulative damage and remaining useful life of gas turbine components and unit risk and classification probability to determine thermal barrier coating damage probability, remaining useful life, and inspection recommendations.

Claims

1. A life management system for predicting the remaining useful life of a thermal barrier coating (TBC) of turbine hot gas and combustion components of a gas turbine unit, comprising:

a non-transitory computer-readable storage medium comprising a series of computer instructions, for determining a cumulative damage of at least one component using operational data including temperature, the computer instructions comprising at least one damage transfer function based upon a physics model;

the computer-readable storage medium further configured for determining a gas turbine unit risk and a classification probability; and

a data fusion module that receives the cumulative damage of the at least one component and the gas turbine unit risk and classification probability, the data fusion module configured to calculate at least one life parameter including a thermal barrier coating parameter;

wherein the at least one component comprises a thermal barrier coating.

2. The system of claim 1, wherein the at least one life parameter comprises a thermal barrier coating damage probability.

3. The system of claim 1, wherein the at least one life parameter comprises a remaining useful life prediction.

4. The system of claim 1, wherein the at least one component life parameter comprises an inspection recommendation.

5. The system of claim 1, wherein the computer-readable storage medium for determining the cumulative damage comprises a monitoring and diagnostics database, means for determining a median metal temperature, mean metal temperature or direct metal temperature and a temperature location, and a means for calculating damage of the at least one component for at least one cycle.

6. The system of claim 1, wherein the computer-readable storage medium for determining the gas turbine unit risk and classification probability comprise a reliability database.

7. The system of claim 1, wherein the data fusion module comprises a data fusion methodology selected from the group comprising a logic based method, a Dampster Schafer method, a Fuzzy Reasoning method, Artificial Intelligence, fusion of monitoring and diagnostics data with damage accumulation, fallout and unplanned models and a Bayesian method.

8. A method for determining a life parameter of a thermal barrier coating (TBC) of hot gas and combustion components of a gas turbine, comprising the steps of:

providing a computer and a non-transitory computer-readable storage medium comprising a series of computer instructions executable by the computer, and a database on the storage medium for storing a monitoring and diagnostics (M&

D) data for a gas turbine component;

determining a cumulative damage of at least one component using operational data including temperature;

determining a gas turbine unit risk and classification probability; and

providing the cumulative damage, the gas turbine unit risk and classification probability to a data fusion module to generate a life parameter including a thermal barrier coating parameter;

wherein the technical effect of performing the steps is to generate an inspection schedule;

wherein determining a cumulative damage is based upon a physics model;

and wherein the life parameter comprises a thermal barrier coating damage probability.

9. The method of claim 8, wherein the life parameter comprises a remaining useful life prediction of a thermal barrier coating.

10. The method of claim 8, wherein the life parameter comprises an inspection recommendation.

11. The method of claim 8, wherein determining the cumulative damage comprises analyzing monitoring and diagnostics data and unit inspection data.

12. The method of claim 8, wherein the computer-readable storage medium for determining the gas turbine unit risk and classification probability comprises a reliability database.

13. A computer program product comprising a non-transitory machine-readable medium storing instructions operable to cause one or more machines to perform operations comprising:

determining a cumulative damage of a thermal barrier coating of a gas turbine component using operational data including temperature based on at least one damage transfer function, the damage transfer function comprising a physics model;

determining a gas turbine unit risk and classification probability; and

using the cumulative damage and gas turbine unit risk and classification probability to calculate a life parameter including a thermal barrier coating parameter;

wherein the technical effect of performing the operations is to generate an inspection schedule.

14. The product of claim 13, wherein the life parameter comprises a thermal barrier coating damage probability.

15. The product of claim 13, wherein the life parameter comprises a remaining useful life prediction.

16. The product of claim 13, wherein the life parameter comprises an inspection recommendation.

17. The product of claim 13, wherein determining the cumulative damage comprises analyzing monitoring and diagnostics data to determine a median metal temperature, mean metal temperature or direct metal temperature and a temperature location, and calculating a damage for each cycle.

18. The product of claim 13, wherein the computer-readable storage medium for determining the gas turbine unit risk and classification probability comprises a reliability database.