Optical measurement system for detecting turbine blade lockup

Patent metadata

Field	Value
Publication number	US-9803492-B2
Application number	US-201414576919-A
Country	US
Kind code	B2
Filing date	Dec 19, 2014
Priority date	Dec 19, 2014
Publication date	Oct 31, 2017
Grant date	Oct 31, 2017

Abstract

An optical measurement system for detecting at least one locked blade assembly in a gas turbine. The system includes at least one light source for emitting light that impinges on a blade surface of each blade in a row of blade assemblies. The system also includes a video device for imaging the blades as the blades rotate about the center axis. Further, the system includes a controller for controlling operation of the light source and video device. The controller detects a pixel intensity associated with each blade and a spacing between each pixel intensity wherein a change in spacing between consecutive pixel intensities indicates that a distance between consecutive blades has changed relative to the first distance thereby indicating at least one locked blade assembly.

First claim

What is claimed is:

1. An optical measurement system for detecting at least one locked blade assembly that becomes locked during a turning gear operation for a gas turbine wherein the gas turbine includes a plurality of blade assemblies arranged in rows about a center axis wherein each blade assembly includes a blade and wherein adjacent blades in a row are separated by a first distance forming a space between adjacent blades to orient each blade in a first position, comprising:
at least one light source for emitting light that impinges on a blade surface of each blade in a row of blades;
at least one video device for capturing images of the blades as the blades rotate about the center axis; and
a controller for controlling operation of the light source and video device wherein the controller detects a pixel intensity associated with each blade surface and a spacing between each pixel intensity wherein the first distance is measured from a first blade that is not deflected from the first position during the turning gear operation and a change in spacing between consecutive pixel intensities indicates that a distance between the first blade and an adjacent blade has changed relative to the first distance thereby indicating at least one locked blade assembly.

2. The system according to claim 1 , wherein the change in spacing includes an increase in spacing between pixel intensities.

3. The system according to claim 1 , wherein the change in spacing includes a decrease in spacing between pixel intensities.

4. The system according to claim 1 , wherein each detected pixel intensity is a peak pixel intensity.

5. The system according to claim 4 , wherein each peak pixel intensity corresponds to a trailing edge of a blade.

6. The system according to claim 1 , wherein the gas turbine includes light and video ports and the light source and video device are attached to the light and video ports, respectively.

7. The system according to claim 6 , wherein the light and video ports are located on an outer diffuser of the gas turbine.

8. The system according to claim 7 , wherein the light port is oriented such that the light impinges on a row of blades located adjacent an exhaust cylinder section of the gas turbine.

9. A method for detecting at least one locked blade assembly that becomes locked during a turning gear operation for a gas turbine wherein the gas turbine includes a plurality of blade assemblies arranged in rows about a center axis wherein each blade assembly includes a blade and wherein adjacent blades in a row are separated by a first distance forming a space between adjacent blades to orient each blade in a first position, comprising:
emitting light that impinges on a blade surface of each blade in a row of blades;
imaging the blades as the blades rotate about the center axis; and
detecting a pixel intensity for each blade surface and a spacing between each pixel intensity wherein the first distance is measured from a first blade that is not deflected from the first position during the turning gear operation and a change in spacing between consecutive pixel intensities relative to other pixel intensities indicates that a distance between the first blade and an adjacent blade has changed relative to the first distance thereby indicating at least one locked blade assembly.

10. The method according to claim 9 , wherein the change in spacing includes an increase in spacing between pixel intensities.

11. The method according to claim 9 , wherein the change in spacing includes a decrease in spacing between pixel intensities.

12. The method according to claim 9 , wherein each detected pixel intensity is a peak pixel intensity.

13. The method according to claim 12 , wherein each peak pixel intensity corresponds to a trailing edge of a blade.

14. The method according to claim 9 , wherein the gas turbine includes light and video ports and the light source and video device are attached to the light and video ports, respectively.

15. The method according to claim 14 , further including orienting the light port such that the light impinges on a row of blades located adjacent an exhaust cylinder section of the gas turbine.

16. A method for detecting at least one locked blade assembly that becomes locked during a turning gear operation for a gas turbine wherein the gas turbine includes a plurality of blade assemblies arranged in rows about a center axis wherein each blade assembly includes a blade and wherein adjacent blades in a row are separated by a first distance forming a space between adjacent blades to orient each blade in a first position, comprising:
emitting light that impinges on a blade surface of each blade in a row of blades located adjacent an exhaust cylinder section of the gas turbine;
imaging the blades as the blades rotate about the center axis; and
detecting a peak pixel intensity for each blade surface and a frame count indicating a spacing between peak pixel intensities wherein the first distance is measured from a first blade that is not deflected from the first position during the turning gear operation and a substantial change in a frame count between consecutive peak pixel intensities relative to other peak pixel intensities indicates that a distance between the first blade and an adjacent blade has changed relative to the first distance thereby indicating at least one locked blade assembly.

17. The method according to claim 16 , wherein the change in the frame count includes an increase in the frame count between pixel intensities.

18. The method according to claim 16 , wherein the change in the frame count includes a decrease in the frame count between pixel intensities.

19. The method according to claim 16 , wherein a substantial change in frame count includes an increase in the frame count to 71 frames.

20. The method according to claim 16 , wherein each peak pixel intensity corresponds to a trailing edge of a blade.

Assignees

• Siemens Energy Inc

Inventors

• Ruhge Forrest R
• Hatcher Jr Clifford

Classifications

• F01D5/30

  Fixing blades to rotors; Blade roots {; Blade spacers} · CPC title

• F01D21/003

  Arrangements for testing or measuring (for measuring vibrations G01H) · CPC title

• F01D5/12

  Blades ({specially adapted for radial flow machines or engines F01D5/04}; blade roots F01D5/30; rotors with blades adjustable in operation F01D7/00; stator blades F01D9/02) · CPC title

• F05D2260/80

  Diagnostics · CPC title

• F05D2220/32

  in gas turbines · CPC title