METHOD AND SYSTEM FOR DETECTING A CRACK ON A TURBOMACHINE BLADE

• US 20110150626A1
• Filed: 12/22/2009
• Published: 06/23/2011
• Est. Priority Date: 12/22/2009
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (General Electric Company)
• Original Assignee: General Electric Company
• Inventors: Shieh, Chingwei M., Kinzie, Kevin W., Lee, Dongjai
• Granted Patent: US 8,074,499 B2
• Time in Patent Office: Days
• US Class Current: 415/1
• CPC Class Codes: G01H 1/003 of rotating machines G01H1/10 takes precedence
• CPC Class Codes: G01N 2291/2693 Rotor or turbine parts
• CPC Class Codes: G01N 29/14 using acoustic emission techniques echo of particles G01N29/046; measuring mechanical vibrations or acoustic waves in solids in general G01H1/00
• CPC Class Codes: G01N 29/4454 Signal recognition, e.g. specific values or portions, signal events, signatures
• CPC Class Codes: G01N 29/46 by spectral analysis, e.g. Fourier analysis or wavelet analysis spectral signal processing per se G06F17/14

Abstract

Embodiments of the present invention may provide real-time monitoring of a compressor section to determine the possibility of a crack forming on a rotating blade. The present invention does not require the shutdown of the machine. The present invention may be configured to automatically raise an alarm if the acoustic signature of the compressor changes in way that may be consistent with the cracking of a blade.

Claims

1. A method of detecting a possible crack on a blade located within a compressor section of a turbomachine, the method comprising:

providing a turbomachine comprising;

a compressor section, wherein the compressor section comprises a plurality of blades; and

an acoustic detection device configured for monitoring the compressor section as the turbomachine operates, wherein the acoustic detection device receives acoustic data relating to the plurality of blades;

utilizing the acoustic data to generate an acoustic signature corresponding to the plurality of blades; and

determining whether the acoustic signature is within an acceptable range;

wherein a determination that the acoustic signature is outside of the acceptable range indicates a likelihood of a crack on at least one of the plurality of blades.

2. The method of claim 1, wherein the acoustic detection device is located adjacent an inlet section of the compressor section.

3. The method of claim 1 further comprising the step of generating a notification on a result of the step of determining whether the acoustic signature is within an acceptable range.

4. The method of claim 1 further comprising the step of retrieving a related acoustic signature from a storage device.

5. The method of claim 1 further comprising the step of transmitting the acoustic signature to a remote monitoring and diagnostic center.

6. The method of claim 4 further comprising the step of comparing the acoustic signature with a related acoustic signature.

7. The method of claim 6, wherein the related acoustic signature derives from the turbomachine.

8. The method of claim 6, wherein the related acoustic signature derives from at least one different turbomachine.

9. A method of monitoring a turbomachine for a formation of a crack on a blade of the turbomachine, the method comprising:

providing a turbomachine comprising a plurality of blades; and

an acoustic detection device configured for monitoring the turbomachine during operation, wherein the acoustic detection device receives acoustic data relating to the plurality of blades;

utilizing the acoustic data to generate an acoustic signature corresponding to the plurality of blades;

comparing the acoustic signature with a related acoustic signature;

determining whether the acoustic signature is within an acceptable range; and

generating a notification on a result of determining whether the acoustic signature is within an acceptable range of the related acoustic signature;

wherein a determination that the acoustic signature is outside of the acceptable range indicates that a crack on at least one of the plurality of blades is possible.

10. The method of claim 9 further comprising multiple acoustic detection devices positioned about turbomachine.

11. The method of claim 9 further comprising the step of retrieving the related acoustic signature from a storage device.

12. The method of claim 11 further comprising the step of saving the acoustic signature in the storage device.

13. The method of claim 9 further comprising the step of transmitting the acoustic signature to a remote monitoring and diagnostic center.

14. The method of claim 9, wherein the related acoustic signature derives from the turbomachine.

15. The method of claim 9, wherein the related acoustic signature derives from at least one different turbomachine.

16. A system for detecting an existence of a crack on a blade within a gas turbine, the system comprising:

a gas turbine comprising a plurality of blades;

an acoustic detection device configured for monitoring operation of the gas turbine, wherein the acoustic detection device receives acoustic data relating to the plurality of blades and is located adjacent the compressor section;

a control system, wherein the control system performs the steps of;

utilizing the acoustic data to generate an acoustic signature corresponding to the plurality of blades; and

determining whether the acoustic signature is within an acceptable range.

17. The system of claim 16, wherein the control system performs the step of comparing the acoustic signature with a related acoustic signature.

18. The method of claim 17 wherein the control system generates a notification on a result on the step of comparing the acoustic signature with the related acoustic signature.

19. The system of claim 17, wherein the related acoustic signature derives from at least one of:

the gas turbine;

at least one different gas turbine;

or a fleet of gas turbines; and

wherein related acoustic signature data is received from a remote monitoring and diagnostics center.

20. The system of claim 16 further comprising a plurality of acoustic detection devices located about an inlet section of the compressor section.