Optical imaging system for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-10697317-B2
Application number	US-201615072647-A
Country	US
Kind code	B2
Filing date	Mar 17, 2016
Priority date	Mar 17, 2016
Publication date	Jun 30, 2020
Grant date	Jun 30, 2020

Abstract

A gas turbine engine having an optical imaging system with a housing configured for mounting to a wall of the turbine engine, a hollow probe extending from the housing and having a longitudinal axis, and an image receiving device at an end of the hollow probe configured to receive at least one of a perspective or image.

First claim

What is claimed is:

1. An optical imaging system, comprising:
a housing configured for mounting to a wall of a turbine engine;
a hollow probe extending from the housing and having a longitudinal axis;
an image receiving device at an end of the hollow probe;
a rigid guide tube having a first end and a second end and defining an interior receiving at least a portion of the hollow probe wherein at least one of the first end or the second end include curved portions; and
a spring positioned between the guide tube and the housing arranged to bias the guide tube axially along the longitudinal axis away from the housing and allow a rocking movement of the guide tube.

2. The optical imaging system of claim 1 wherein both the first end and the second end include curved portions such that the guide tube can pivot at those curved portions.

3. The optical imaging system of claim 1 further comprising a camera communicably coupled with image receiving device.

4. The optical imaging system of claim 3 wherein the camera is at least one of a pyrometer camera or an infrared camera.

5. The optical imaging system of claim 3 wherein the camera is configured to sense a temperature of a surface in an interior of the turbine engine.

6. The optical imaging system of claim 3 wherein the camera is configured to visually inspect a set of turbine blades.

7. The optical imaging system of claim 6 wherein the camera is configured to visually inspect a set of turbine blades as the set of turbine blades rotate past the image receiving device.

8. The optical imaging system of claim 6 wherein the image receiving device is configured to enable the camera to view an image substantially normal to the longitudinal axis.

9. The optical imaging system of claim 1 wherein the hollow probe is spaced from an interior surface defining the interior of the guide tube.

10. The optical imaging system of claim 1 , further comprising a cap operably coupling an end of the hollow probe to the second end of the guide tube.

11. The optical imaging system of claim 1 wherein at least one of the hollow probe or the guide tube comprises a set of cooling grooves configured to flow a cooling medium to cool the hollow probe.

12. The optical imaging system of claim 1 wherein the image receiving device includes at least one of a lens, mirror, or prism.

13. The optical imaging system of claim 1 wherein the spring comprises multiple springs.

14. The optical imaging system of claim 1 , further comprising an optical element at an end of the hollow probe, opposite the image receiving device.

15. The optical imaging system of claim 14 wherein the spring includes an optics spring configured to force the optical element toward the second end.

16. The optical imaging system of claim 14 wherein the optics spring is configured to allow at least a portion of movement of the optical element relative to the hollow probe.

17. The optical imaging system of claim 1 wherein the spring includes a hollow probe spring configured to at least partially retain the hollow probe relative to the guide tube.

18. The optical imaging system of claim 17 wherein hollow probe spring is configured to force the hollow probe toward the second end.

19. The optical imaging system of claim 17 wherein the hollow probe spring is configured to allow at least a portion of movement of the hollow probe relative to the guide tube.

20. A gas turbine engine, comprising:
a radial wall defining an interior and an exterior of the gas turbine engine and having an aperture;
a set of turbine blades located in the interior and configured to rotate about a shaft; and
an optical imaging system, comprising:
a housing configured for mounting to the radial wall;
a hollow probe extending from the housing and having a longitudinal axis;
an image receiving device at an end of the hollow probe where the image receiving device is located adjacent a hot gas path within the interior;
a rigid guide tube having a first end and a second end and defining an interior receiving at least a portion of the hollow probe wherein at least one of the first end or the second end include curved portions configured to allow for a rocking movement of the guide tube at the curved portions; and
a spring between the guide tube and the housing adjacent the first end of the guide tube, to bias the guide tube away from the housing towards the second end and allow for axial and rocking movement of the guide tube.

21. The gas turbine engine of claim 20 wherein the optical imaging system is configured to image at least a portion of the interior of the gas turbine engine while the gas turbine engine is operating.

22. The gas turbine engine of claim 20 wherein the at least a portion of the first end comprises a spherical portion.

23. A guide tube assembly, comprising a rigid hollow guide tube having a first end, a second end configured to be housed adjacent a portion of a gas turbine, and an interior surface defining an interior and wherein at least a portion of the second end includes a curved surface allowing it to rock against the portion of the gas turbine; and
a spring adjacent the first end of the guide tube and arranged to bias the guide tube towards the second end and allow a rocking movement of the guide tube.

24. The guide tube assembly of claim 23 wherein the at least a portion of the second end comprises a spherical portion.

Assignees

• Gen Electric

Inventors

• Bailey Jeremy Clyde
• Nirmalan Nirm Velumylum
• Sakami Mohamed
• Mathias Christopher Dale
• Wang Guanghua
• Ferree Jr Ronald W

Classifications

• F05D2220/30

  in turbines · CPC title

• F01D5/10

  Anti- vibration means {(specially adapted for radial flow machines or engines F01D5/04)} · CPC title

• G02B23/2476 Primary

  Non-optical details, e.g. housings, mountings, supports · CPC title

• F01D25/04

  Antivibration arrangements · CPC title

• G01J3/0291

  Housings; Spectrometer accessories; Spatial arrangement of elements, e.g. folded path arrangements · CPC title