System and method for inspection of stator vanes

• US 8,602,722 B2
• Filed: 02/26/2010
• Issued: 12/10/2013
• Est. Priority Date: 02/26/2010
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (General Electric Company)
• Original Assignee: General Electric Company
• Inventors: George, Sheri, Jammu, Vinay Bhaskar, Kumar, Vinod Padmanabhan, Mitra, Chayan, Goray, Kunal Ravindra, Pandey, Achalesh Kumar, Babu, Ravi Yoganatha, Keely, Bhasker Rao, Inamdar, Munish Vishwas
• Primary Examiner(s): Look, Edward
• Assistant Examiner(s): MCDOWELL, LIAM J
• Application Number:
  US12/714,207
• Publication Number:
  US 20110211940A1
• Time in Patent Office: 1,383 Days
• Field of Search: 415/118, 415/121.3, 415/232, 416/5, 416/61, 416/62
• US Class Current: 415/118
• CPC Class Codes: F01D 21/003 Arrangements for testing or measuring for measuring vibrations G01H
• CPC Class Codes: F01D 25/285 Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
• CPC Class Codes: F05D 2260/80 Diagnostics
• CPC Class Codes: F05D 2270/8041 Cameras
• CPC Class Codes: G01N 2021/8887 based on image processing techniques
• CPC Class Codes: G01N 21/954 Inspecting the inner surface of hollow bodies, e.g. bores
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

Embodiments of the invention include an inspection system to inspect internal components of a compressor of a gas turbine engine. The inspection system includes an image recording assembly having one or more image recording devices, light sources, storage devices, and power supplies. The image recording assembly may be inserted into a compressor without removal of the compressor housing or disassembly of the compressor. The image recording assembly may be removably coupled to a rotary component of the compressor, e.g., a rotor blade, and used to record images of stationary components, e.g., stator vanes, of the compressor. The images may be inspected to identify wear and/or defects in the stationary components, e.g., stator vanes.

Claims

1. A method, comprising:

removably coupling an image recording assembly to a rotary component of a compressor of a gas turbine engine such that a plurality of cameras disposed within the image recording assembly are oriented in different directions from each other relative to a length of the rotary component;

rotating the image recording assembly around a shaft of the gas turbine engine; and

recording images of stationary components disposed circumferentially around the shaft, without removal of a housing of the compressor.

2. The method of claim 1, comprising storing images in a storage device of the image recording assembly.

3. The method of claim 1, wherein the rotary component comprises a rotor blade.

4. The method of claim 1, wherein the stationary components comprise stator vanes.

5. The method of claim 1, wherein rotating an image recording assembly comprises rotating the shaft of the gas turbine engine.

6. The method of claim 1, wherein recording images of the stationary components comprises recording images using at least one camera of the image recording assembly.

7. The method of claim 1, comprising downloading images from the image recording assembly to an image processing system.

8. The method of claim 1, wherein downloading images comprises downloading images via a wireless communication device of the image recording assembly.

9. The method of claim 8, comprising illuminating the stationary components via a light source of the image recording assembly.

10. The method of claim 1, wherein the plurality of cameras comprise a plurality of pin-hole cameras.

11. A system, comprising:

an image recording assembly for a compressor of a gas turbine engine, comprising;

a plurality of cameras for recording images of stator vanes of the compressor as a rotor blade of the compressor rotates;

a light source; and

a storage device, wherein each camera of the plurality of cameras is oriented in a different direction from each other camera relative to a length of the rotor blade, and;

a coupling mechanism for coupling the image recording assembly to the rotor blade.

12. The system of claim 11, wherein the light source comprises a light emitting diode.

13. The system of claim 11, wherein the storage device comprises a flash memory device.

14. The system of claim 11, further comprising an image processing system, wherein the image recording assembly further comprises an interface for communication with the image processing system.

15. The system of claim 11, wherein the image recording assembly further comprises a power supply configured to provide power to the plurality of cameras, the light source, the storage device, or any combination thereof.

16. The system of claim 11, wherein the plurality of cameras comprise a plurality of pin-hole cameras.

17. A method, comprising:

inserting a camera assembly comprising a plurality of cameras into a compressor housing of a gas turbine engine such that each camera of the plurality of cameras is oriented in a different direction from each other camera relative to a length of a rotor blade;

coupling the camera assembly to the rotor blade; and

determining defects in an internal component of the compressor from images recorded by the camera assembly.

18. The method of claim 17, comprising removing the camera assembly from the compressor housing of the gas turbine engine.

19. The method of claim 17, wherein inserting the camera assembly comprises inserting the camera assembly through a borescope hole of the compressor housing.

20. The method of claim 17, wherein determining defects comprises determining defects in stator vanes of the compressor from images recorded by the camera assembly.