Gas turbine engine and test cell real-time diagnostic fault detection and corrective action system and method

• US 10,247,032 B2
• Filed: 03/28/2017
• Issued: 04/02/2019
• Est. Priority Date: 03/28/2017
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Gill, Christopher, Vedder, Curtis, Moeckly, Kevin
• Primary Examiner(s): Le, John H
• Application Number:
  US15/471,204
• Publication Number:
  US 20180283200A1
• Time in Patent Office: 735 Days
• Field of Search: 702 33, 702 35, 702113, 702182, 702189, 701100, 348143
• CPC Class Codes: F01D 21/003 Arrangements for testing or measuring for measuring vibrations G01H
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2260/80 Diagnostics
• CPC Class Codes: F05D 2260/83 Testing, e.g. methods, components or tools therefor
• CPC Class Codes: G01M 15/14 Testing gas-turbine engines or jet-propulsion engines

Abstract

A real-time diagnostic and fault detection system and method for a gas turbine engine under test in a test cell is disclosed. Sensor data from instrumentation coupled to the gas turbine engine are processed, using a physics-based component level aero-thermal model, to calculate a plurality of engine parameters at a plurality of non-instrumented locations within the gas turbine engine. The plurality of engine parameters are processed to detect when a fault exists and, when a fault does exist, an image is rendered that indicates at least a mostly likely cause for the fault and one or more corrective actions that can be taken to correct the fault. The model is also used to generate projections of engine performance at one or more selected test conditions, and to prognosticate, based on the projections, as to whether the gas turbine engine will actually pass at the one or more selected test conditions.

Claims

1. A real-time diagnostic and fault detection method for a gas turbine engine under test in a test cell, the method comprising:

supplying, to a processing system, sensor data from instrumentation coupled to the gas turbine engine that is under test in the test cell;

processing the sensor data, using a physics-based component level aero-thermal model of the gas turbine engine that is implemented in the processing system, to calculate a plurality of engine parameters at a plurality of different, non-instrumented locations within the gas turbine engine;

processing, in the processing system, the plurality of engine parameters to detect when a fault exists within the gas turbine engine; and

when a fault does exist within the gas turbine engine;

rendering, on a display device, an image that indicates at least a mostly likely cause for the fault,

generating one or more corrective actions that can be taken to correct the fault, and

at least selectively rendering, on the display device, the one or more corrective actions.

2. The method of claim 1, further comprising:

processing the sensor data, using the physics-based component level aero-thermal model of the gas turbine engine, to generate projections of performance of the gas turbine engine to one or more selected test conditions; and

prognosticating, based on the projections of performance, as to whether the gas turbine engine will actually pass at the one or more selected test conditions or test objectives.

3. The method of claim 2, wherein the one or more selected test conditions include one or both of one more environmental conditions and one or more engine loading conditions.

4. The method of claim 2, further comprising:

rendering, on the display device, an image field that indicates whether the gas turbine engine will pass or fail at the one or more selected test conditions.

5. The method of claim 1, further comprising:

comparing the plurality of engine parameters at the plurality of different, non-instrumented locations to expected engine parameters at the plurality of different, non-instrumented locations;

generating, based on the comparisons, a plurality of component diagnostic signatures; and

rendering, on the display device, at least a portion of the plurality of component diagnostic signatures.

6. The method of claim 5, further comprising:

comparing, in the processing system, the component diagnostic signatures to known signatures in a stored fault library.

7. The method of claim 1, wherein the step of rendering the image that indicates at least the mostly likely cause for the fault further comprises:

rendering an image that graphically depicts (i) a plurality of potential causes for the fault and (ii) a relative likelihood that each potential cause is the cause for the fault.

8. The method of claim 1, further comprising:

rendering image fields, on the display device, that specify at least the most likely cause for the fault and its magnitude.

9. The method of claim 1, further comprising:

rendering, on the display device, images of a plurality of parameters that summarize engine performance.

10. The method of claim 1, further comprising rendering, on the display device:

a reference documents selection field that provides a dropdown menu that allows one or more document types to be selected and, upon selection, viewed; and

an instrumentation field that provides a list of physical measurements that were evaluated in identifying the fault.

11. A real-time diagnostic and fault detection system for a gas turbine engine under test in a test cell, the system comprising:

a display device configured to render one or more images;

instrumentation adapted to be coupled to a gas turbine engine, the instrumentation configured, upon being coupled to the gas turbine engine, to supply sensor data;

a processing system coupled to the display device and further coupled to receive the sensor data supplied from the instrumentation, the processing system configured to implement a physics-based component level aero-thermal model of the gas turbine engine, the processing system further configured to;

process the sensor data, using the physics-based component level aero-thermal model, to calculate a plurality of engine parameters at a plurality of different, non-instrumented locations within the gas turbine engine,

process the plurality of engine parameters to detect when a fault exists within the gas turbine engine, and

upon determining that a fault does exist within the gas turbine engine;

(i) command the display device to render an image that indicates at least a mostly likely cause for the fault,

(ii) generate one or more corrective actions that can be taken to correct the fault, and

(iii) at least selectively command the display device to render the one or more corrective actions.

12. The system of claim 11, wherein the processing system is further configured to:

process the sensor data, using the physics-based component level aero-thermal model of the gas turbine engine, to generate projections of performance of the gas turbine engine to one or more selected test conditions; and

prognosticate, based on the projections of performance, as to whether the gas turbine engine will actually pass at the one or more selected test conditions.

13. The system of claim 12, wherein the one or more selected test conditions include one or both of one more environmental conditions and one or more engine loading conditions.

14. The system of claim 12, wherein the processing system is further configured to command the display device to render an image field that indicates whether the gas turbine engine will pass or fail at the one or more selected test conditions.

15. The system of claim 11, wherein the processing system is further configured to:

compare the plurality of engine parameters at the plurality of different, non-instrumented locations to expected engine parameters at the plurality of different, non-instrumented locations;

generate, based on the comparisons, a plurality of component diagnostic signatures;

compare the component diagnostic signatures to known signatures in a stored fault library; and

command the display device to render at least a portion of the plurality of component diagnostic signatures.

16. The system of claim 11, wherein the processing system is further configured to command the display device to render an image that graphically depicts (i) a plurality of potential causes for the fault and (ii) a relative likelihood that each potential cause is the cause for the fault.

17. The system of claim 11, wherein the processing system is further configured to command the display device to render image fields that specify at least the most likely cause for the fault and its magnitude.

18. The system of claim 11, wherein the processing system is further configured to command the display device to render images of a plurality of parameters that summarize engine performance.

19. The system of claim 11, wherein the processing system is further configured to command the display device to render:

a reference documents selection field that provides a dropdown menu that allows one or more document types to be selected and, upon selection, viewed; and

an instrumentation field that provides a list of physical measurements that were evaluated in identifying the fault.

20. A real-time diagnostic and fault detection system for a gas turbine engine under test in a test cell, the system comprising:

instrumentation adapted to be coupled to a gas turbine engine, the instrumentation configured, upon being coupled to the gas turbine engine, to supply sensor data;

a processing system coupled to receive the sensor data supplied from the instrumentation, the processing system configured to implement a physics-based component level aero-thermal model of the gas turbine engine, the processing system further configured to;

process the sensor data, using the physics-based component level aero-thermal model, to generate projections of performance of the gas turbine engine to one or more selected test conditions, and

prognosticate, based on the projections of performance, as to whether the gas turbine engine will actually pass at the one or more selected test conditions.