Methods and apparatus for assessing gas turbine engine damage

• US 20040172187A1
• Filed: 02/28/2003
• Published: 09/02/2004
• Est. Priority Date: 02/28/2003
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Wiseman, Matthew William
• Granted Patent: US 6,892,127 B2
• Time in Patent Office: Days
• US Class Current: 701/100
• CPC Class Codes: G05B 23/0218 characterised by the fault detection method dealing with either existing or incipient faults

Abstract

A method and apparatus for assessing damage to machine components is provided. The method includes calculating an expected parameter value based on a first parameter value indicator, calculating an estimate of an actual parameter value based on a second parameter value indicator, the second parameter value indicator being different than the first parameter value indicator, determining if the calculated expected parameter value is different than the calculated estimate of the actual parameter value by a predefined limit, and generating a damage flag based on a result of the comparison. The apparatus includes a computing device including a processor and a memory communicatively coupled to the processor, the processor programmed to execute a software product code segment that includes a detection boundary module, an estimator, and a comparator wherein the computing device is programmed to assess damage within an engine.

Claims

1. A method of assessing damage to machine components, said method comprising:

calculating an expected parameter value based on a first parameter value indicator wherein the first parameter value indicator is responsive to a damage symptom;

calculating an estimate of an actual parameter value based on a second parameter value indicator wherein the second parameter value indicator is different than the first parameter value indicator;

determining if the calculated expected parameter value is different than the calculated estimate of the actual parameter value by a predefined limit; and

generating a damage flag based on a result of the comparison.

2. A method in accordance with claim 1 wherein calculating an estimate of an actual parameter value comprises calculating an estimate of an actual parameter value based on a plurality of parameter value indicators.

3. A method in accordance with claim 1 wherein the machine includes a gas turbine engine that includes a variable area exhaust nozzle, and wherein calculating an expected parameter value comprises calculating a maximum expected value of effective exhaust nozzle area.

4. A method in accordance with claim 3 wherein calculating an estimate of an actual parameter value comprises calculating an estimate of an actual effective nozzle area based on engine cycle data inputs.

5. A method in accordance with claim 4 wherein calculating an estimate of an actual effective nozzle area comprises calculating an estimate of an actual effective nozzle area based on at least one of rotor speed, gas pressure, and exhaust temperature.

6. A method in accordance with claim 5 wherein calculating an estimate of an actual effective nozzle area comprises calculating an estimate of an actual effective nozzle area using an estimator that computes at least one of a linear function of the engine cycle data inputs, a neural network function of the engine cycle data inputs, and a nonlinear function of the engine cycle data inputs.

7. A method in accordance with claim 6 further comprising training the estimator using at least one of real engine data from an undamaged engine, real engine data from a damaged engine and simulated engine data from an undamaged engine, and simulated engine data from an undamaged engine.

8. A method in accordance with claim 6 wherein calculating an estimate of an actual effective nozzle area using an estimator comprises calculating an estimate of an actual effective nozzle area using an estimator that includes a physics-based model of effective nozzle area that includes upstream parameter value indicators as inputs.

9. Apparatus for detecting damage in a gas turbine engine, said apparatus comprising a computing device comprising a processor and a memory communicatively coupled to said processor, said processor programmed to execute a software product code segment comprising a detection boundary module, an estimator, and a comparator, said computing device programmed to assess damage within an engine.

10. Apparatus in accordance with claim 9 wherein said detection boundary module is configured to:

receive exhaust nozzle position feedback sensor data; and

determine an expected value of effective nozzle area.

11. Apparatus in accordance with claim 9 wherein said estimator is configured to:

receive engine cycle data; and

estimate an actual effective nozzle area using said engine cycle data.

12. Apparatus in accordance with claim 9 wherein said comparator is configured to:

receive an expected value of effective nozzle area;

receive an estimate an actual effective nozzle area; and

compare said expected value of effective nozzle area to said estimate of the actual effective nozzle area.

13. Apparatus in accordance with claim 12 wherein said comparator is further configured to generate a damage flag based on said comparison.

14. Apparatus in accordance with claim 13 wherein said comparator is further configured to generate a hole damage flag when said expected value of effective nozzle area is less than said estimate of the actual effective nozzle area.

15. Apparatus in accordance with claim 13 wherein said comparator is further configured to generate a blockage damage flag when said expected value of effective nozzle area is greater than said estimate of the actual effective nozzle area.

16. A gas turbine assembly comprising:

a variable area exhaust nozzle comprising an inlet side, and an outlet side; and

a computing device comprising a processor and a memory communicatively coupled to said processor, said processor programmed to execute a software product code segment comprising a detection boundary module, an estimator, and a comparator, said computing device programmed to assess damage within the gas turbine assembly.

17. A gas turbine assembly in accordance with claim 16 wherein said detection boundary module is configured to:

receive exhaust nozzle position feedback sensor data; and

determine an expected value of effective nozzle area.

18. A gas turbine assembly in accordance with claim 16 wherein said estimator is configured to:

receive engine cycle data; and

estimate an actual effective nozzle area using said engine cycle data.

19. A gas turbine assembly in accordance with claim 16 wherein said comparator is configured to:

receive an expected value of effective nozzle area;

receive an estimate an actual effective nozzle area; and

compare said expected value of effective nozzle area to said estimate of the actual effective nozzle area.

20. A gas turbine assembly in accordance with claim 19 wherein said comparator is further configured to generate a damage flag based on said comparison.