Methods of forming a passive strain indicator on a preexisting component

• US 10,126,119 B2
• Filed: 01/17/2017
• Issued: 11/13/2018
• Est. Priority Date: 01/17/2017
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (General Electric Company)
• Original Assignee: General Electric Company
• Inventors: Tollison, Brian Lee, Kottilingam, Srikanth Chandrudu, Cui, Yan, Germann, Bryan Joseph
• Primary Examiner(s): Decenzo, Shawn
• Application Number:
  US15/407,595
• Publication Number:
  US 20180202799A1
• Time in Patent Office: 665 Days
• Field of Search: None
• CPC Class Codes: G01B 11/002 for measuring two or more coordinates
• CPC Class Codes: G01B 11/165 by means of a grating deformed by the object
• CPC Class Codes: G01B 11/24 for measuring contours or curvatures
• CPC Class Codes: G01B 21/047 Accessories, e.g. for positioning, for tool-setting, for measuring probes
• CPC Class Codes: G01M 15/14 Testing gas-turbine engines or jet-propulsion engines

Abstract

A method of forming a passive strain indicator on a preexisting component includes directly depositing a plurality of fiducial markers on a portion of the outer surface of the preexisting component, the fiducial markers including a material that is compatible with the material of the outer surface. A method of evaluating a component includes initially scanning a plurality of fiducial markers on a portion of an outer surface of the component, subjecting the component to at least one duty cycle, subsequently scanning the plurality of fiducial markers after the at least one duty cycle, measuring a displacement of the plurality of fiducial markers by comparing the subsequent scan to the initial scan, and determining a remaining usable life of the component by looking up in a database a predetermined value of the remaining usable life of the component corresponding to the measured displacement of the plurality of fiducial markers.

Claims

1. A method of forming a passive strain indicator on a preexisting turbine component, the preexisting turbine component comprising an outer surface comprising a first material, the method comprising:

directing a flow of a carrier fluid towards a portion of the outer surface of the preexisting turbine component, the flow of carrier fluid carrying a powder, the powder comprising a second material that is different from and compatible with the first material;

emitting light in the form of a laser beam from a laser source;

directing the emitted laser beam towards the portion of the outer surface of the preexisting turbine component to melt the powder carried in the flow of the carrier fluid onto the outer surface of the preexisting turbine component at a first location within the portion of the outer surface of the preexisting turbine component, whereby a first fiducial marker of the passive strain indicator is formed at the first location;

directing the flow of carrier fluid towards a second location within the portion of the outer surface of the preexisting turbine component; and

directing the emitted laser beam towards the second location on the outer surface of the preexisting turbine component to melt the powder carried in the flow of the carrier fluid onto the outer surface of the component at the second location, whereby a second fiducial marker of the passive strain indicator is formed at the second location;

wherein the portion of the outer surface comprises an analysis region on the outer surface of the preexisting turbine component, the analysis region defines a gage length, and each of the first fiducial marker and the second fiducial marker has a maximum diameter of between one-tenth and one-twentieth of the gage length.

2. The method of claim 1, wherein the first fiducial marker and the second fiducial marker are formed on the preexisting turbine component while the preexisting turbine component is in a service position.

3. The method of claim 1, wherein the first location on the outer surface and the second location on the outer surface are spaced apart such that the method further comprises leaving bare portions of the outer surface between and around the first fiducial marker and the second fiducial marker.

4. The method of claim 1, wherein the first material is a superalloy and the second material is a different superalloy.

5. The method of claim 1, wherein the first material is a nickel-based superalloy and the second material is a cobalt-based superalloy.

6. A component, comprising:

an outer surface comprising a first material;

a plurality of fiducial markers on a portion of the outer surface, the fiducial markers comprising a second material that is different from and compatible with the first material, the portion of the outer surface comprising an analysis region on the outer surface of the component, the analysis region defines a gage length, and each fiducial marker of the plurality of fiducial markers has a maximum diameter of between one-tenth and one-twentieth of the gage length, wherein an area of the analysis region is less than about ten percent of the area of the outer surface.

7. The component of claim 6, wherein the area of the analysis region is less than about eight percent of the area of the outer surface.

8. The component of claim 6, wherein the area of the analysis region is less than about two and a half percent of the area of the outer surface.

9. The component of claim 6, wherein the plurality of fiducial markers are arranged in the analysis region in a matrix grid, the matrix grid having a preselected row spacing and a preselected column spacing.

10. The component of claim 9, wherein one of the preselected row spacing or the preselected column spacing is less than about seventy-five percent of the maximum diameter.

11. The component of claim 9, wherein one of the preselected row spacing or the preselected column spacing is less than about sixty percent of the maximum diameter.

12. The component of claim 6, wherein the first material is a first metallic material and the second material is a second metallic material.

13. The component of claim 6, wherein the component is a gas turbine component.

14. The component of claim 6, wherein the component is a hot gas path component of a gas turbine.

15. The component of claim 6, wherein the analysis region includes a life-limiting region of the component.