METHODS FOR PRODUCING PASSIVE STRAIN INDICATOR ON TURBINE COMPONENTS

• US 20170097234A1
• Filed: 12/22/2016
• Published: 04/06/2017
• Est. Priority Date: 05/30/2014
• Status: Active Grant

• Current Assignee: GE Infrastructure Technology, LLC (GE Vernova, Inc.)
• Original Assignee: General Electric Company
• Inventors: Ward, JR., John David, Germann, Bryan Joseph, Burnside, Jason Lee, Hovis, Gregory Lee
• Granted Patent: US 10,415,964 B2
• Time in Patent Office: Days
• CPC Class Codes: C23C 24/04 Impact or kinetic deposition of particles
• CPC Class Codes: C23C 4/11 Oxides
• CPC Class Codes: F01D 17/04 responsive to load
• CPC Class Codes: F05D 2230/31 Layer deposition
• CPC Class Codes: F05D 2260/80 Diagnostics
• CPC Class Codes: F05D 2260/83 Testing, e.g. methods, components or tools therefor
• CPC Class Codes: F05D 2270/808 Strain gauges; Load cells
• CPC Class Codes: G01B 11/165 by means of a grating deformed by the object
• CPC Class Codes: G01B 21/32 for measuring the deformation in a solid
• CPC Class Codes: G01L 1/2287 constructional details of the strain gauges adjustable resistors H01C10/00
• CPC Class Codes: G01M 15/14 Testing gas-turbine engines or jet-propulsion engines
• CPC Class Codes: G01M 5/0016 of aircraft wings or blades
• CPC Class Codes: G01M 5/0041 by determining deflection or stress

Abstract

Methods for manufacturing passive strain indicator on turbine components include providing a turbine component comprising an exterior surface, and, depositing a ceramic material onto a portion of the exterior surface to form a passive strain indicator comprising at least two reference points.

Claims

1. A method for manufacturing a passive strain indicator on a turbine component, the method comprising:

providing a turbine component comprising an exterior surface; and

,

depositing a ceramic material onto a portion of the exterior surface to form a passive strain indicator comprising at least two reference points.

2. The method of claim 1, wherein the at least two reference points are at least partially separated by an exposed portion of the exterior surface.

3. The method of claim 2, further comprising depositing a visually contrasting material in the exposed portion.

4. The method of claim 1, wherein the turbine component comprises a nickel or cobalt based superalloy.

5. The method of claim 1, wherein the ceramic material comprises yttria-stabilized zirconia.

6. The method of claim 1, wherein the ceramic material is deposited using an aerosol jet coater.

7. The method of claim 1, wherein the ceramic material is deposited into a near net shape of the passive strain indicator.

8. The method of claim 1, wherein depositing the ceramic material further comprises forming a unique identifier.

9. A method of monitoring a turbine component, the method comprising:

providing a turbine component comprising an exterior surface;

depositing a ceramic material onto a portion of the exterior surface to form a passive strain indicator comprising at least two reference points;

measuring a second distance between a first of the at least two reference points of the passive strain indicator and a second of the at least two reference points of the passive strain indicator at a second time internal; and

,

comparing the second distance to a first distance between the first of the at least two reference points of the passive strain indicator and the second of the at least two reference points of the passive strain indicator from a first time interval.

10. The method of claim 9, wherein the at least two reference points are at least partially separated by an exposed portion of the exterior surface.

11. The method of claim 10, further comprising depositing a visually contrasting material in the exposed portion prior to measuring the second distance.

12. The method of claim 9, further comprising utilizing the turbine component in a turbine between the first and second time intervals.

13. The method of claim 9, wherein the turbine component comprises a nickel or cobalt based superalloy.

14. The method of claim 9, wherein the ceramic material comprises yttria-stabilized zirconia.

15. A turbine component comprising:

an exterior surface; and

,

a passive strain indicator deposited on a portion of the exterior surface, the passive strain indicator comprising ceramic material and at least two reference points.

16. The turbine component of claim 15, wherein the turbine component comprises a nickel or cobalt based superalloy.

17. The turbine component of claim 15, wherein the turbine component comprises a hot gas path or combustion component.

18. The turbine component of claim 15, wherein the ceramic material comprises yttria-stabilized zirconia.

19. The turbine component of claim 15, wherein the at least two reference points are at least partially separated by an exposed portion of the exterior surface.

20. The turbine component of claim 15, wherein the at least two reference points are at least partially separated by visually contrasting material.