METHOD FOR DETECTING A COMPROMISED COMPONENT

• US 20160003068A1
• Filed: 04/08/2014
• Published: 01/07/2016
• Est. Priority Date: 04/08/2013
• Status: Abandoned Application

• Current Assignee: Raytheon Technologies Corporation d/b/a RTX (Rtx Corporation)
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Greenberg, Michael D., Zelesky, Mark F.
• Application Number:
  US14/769,034
• Publication Number:
  US 20160003068A1
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: C23C 28/3215 at least one MCrAlX layer
• CPC Class Codes: C23C 28/34 including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
• CPC Class Codes: C23C 28/3455 with a refractory ceramic layer, e.g. refractory metal oxide, ZrO2, rare earth oxides or a thermal barrier system comprising at least one refractory oxide layer
• CPC Class Codes: C23C 4/073 containing MCrAl or MCrAlY alloys, where M is nickel, cobalt or iron, with or without non-metal elements
• CPC Class Codes: C23C 4/18 After-treatment
• CPC Class Codes: F01D 21/003 Arrangements for testing or measuring for measuring vibrations G01H
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F01D 5/288 Protective coatings for blades
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2260/202 by film cooling
• CPC Class Codes: F05D 2260/80 Diagnostics
• CPC Class Codes: G01J 5/48 Thermography; Techniques using wholly visual means
• CPC Class Codes: G01N 21/8803 Visual inspection measuring projectors G01B9/08
• CPC Class Codes: G01N 21/95 characterised by the material or shape of the object to be examined G01N21/89 - G01N21/91, G01N21/94 take precedence

Abstract

A method for providing visually detectable changes to a surface that has been subjected to a temperature in excess of a predetermined temperature. A coating is applied to the surface, wherein the coating will melt when the predetermined temperature has been reached. Centrifugal forces acting on the melted coating will cause it to be displaced such that the disturbed surface is visibly detectable upon inspection after solidifying.

Claims

1. A method for determining if a component having a coating thereon has been compromised, the method comprising the steps of:

a) visually inspecting the coating; and

b) determining that the component has been compromised if the coating is displaced.

2. The method of claim 1, wherein the coating comprises a metallic coating.

3. The method of claim 2, wherein the metallic coating comprises NiCoCrAlY.

4. The method of claim 2, wherein the metallic coating comprises more than one layer.

5. The method of claim 1, wherein the component comprises an turbine blade in a turbine engine.

6. The method of claim 5, wherein the component comprises a high pressure turbine blade in a turbine engine.

7. The method of claim 1, further comprising the step of:

c) determining that the component should be serviced if it is determined at step (b) that the component has been compromised.

8. The method of claim 1, wherein the displaced coating is rumpled.

9. The method of claim 1, wherein the displaced coating exhibits evidence of having flowed.

10. The method of claim 2, wherein the metallic coating is at least partially covered by a thermal barrier coating.

11. The method of claim 1, wherein the component includes at least one cooling hole formed therein and the displaced coating has flowed into at least one of the at least one cooling holes.

12. A method for determining if a component has been operated above a predetermined temperature, the method comprising the steps of:

a) applying a coating to the component;

b) visually inspecting the coating; and

c) determining that the component has been operated above the predetermined temperature if the coating is displaced.

13. The method of claim 12, wherein step (a) further comprises:

a) applying the coating in a pattern to the component.

14. The method of claim 12, wherein step (a) further comprises:

a) applying the coating in multiple layers.

15. The method of claim 13, wherein the pattern comprises letters forming a message.

16. The method of claim 15, wherein the message comprises “

WARRANTY VOIDED”

.

17. The method of claim 12, wherein the component comprises a turbine blade in a turbine engine.

18. The method of claim 17, wherein the component comprises a high pressure turbine blade in a turbine engine.

19. The method of claim 12, wherein the displaced coating is rumpled.

20. The method of claim 12, wherein the displaced coating exhibits evidence of having flowed.

21. The method of claim 12, wherein the coating comprises a metallic coating.

22. The method of claim 21, wherein the metallic coating comprises NiCoCrAlY.

23. The method of claim 21, where in the metallic coating is applied using one of a low pressure plasma spray, an air plasma spray or high velocity oxy-fuel spraying.

24. The method of claim 12, wherein the component includes at least one cooling hole formed therein and the displaced coating has flowed into at least one of the at least one cooling holes.

25. The method of claim 21, wherein the coating is at least partially covered by a thermal barrier coating.