Methods, systems and apparatus for detecting material defects in rotor blades of combustion turbine engines

• US 8,636,462 B2
• Filed: 01/10/2011
• Issued: 01/28/2014
• Est. Priority Date: 01/10/2011
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Kraemer, Gilbert Otto, Ghosh, Dullal, Atchuta, Bhaskara Rao
• Primary Examiner(s): Kershteyn, Igor
• Application Number:
  US12/987,365
• Publication Number:
  US 20120177491A1
• Time in Patent Office: 1,114 Days
• Field of Search: 415/1, 415/118, 416/1, 416/61, 324/700
• US Class Current: 415/1
• CPC Class Codes: F01D 21/10 responsive to unwanted deposits on blades, in working-fluid conduits or the like
• CPC Class Codes: F01D 21/14 responsive to other specific conditions
• CPC Class Codes: F01D 5/288 Protective coatings for blades
• CPC Class Codes: G01N 27/20 Investigating the presence of flaws
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A system for detecting defects in a turbine rotor blade of a combustion turbine engine. The system may include: a turbine rotor blade that includes an insulator coating; a first electrode that is electrically connected to the turbine rotor blade; a second electrode that resides in proximity to the turbine rotor blade; means for inducing a voltage across the first electrode and the second electrode; and means for detecting current flowing between the first electrode and the second electrode.

Claims

1. A system for detecting defects in a turbine rotor blade of a combustion turbine engine while the combustion turbine engine operates, the system comprising:

a turbine rotor blade that includes an insulator coating;

a first electrode that is electrically connected to the turbine rotor blade;

a second electrode that resides in proximity to the turbine rotor blade;

means for inducing a voltage across the first electrode and the second electrode; and

means for detecting current flowing between the first electrode and the second electrode.

2. The system according to claim 1, wherein the first electrode is connected to a rotor wheel into which the turbine rotor blade is attached;

wherein the connection of the first electrode to the rotor wheel comprises one of;

a) a slip ring connection to a rotating part; and

b) a connection to a non-rotating bearing surface; and

wherein the second electrode is connected to a turbine casing.

3. The system according to claim 1, wherein the second electrode is connected to stationary structure just downstream of a row of turbine blades in which the turbine rotor blade is included;

wherein the second electrode is exposed to the hot-gas flowpath of the combustion turbine engine; and

wherein the insulator coating comprises a thermal barrier coating.

4. The system according to claim 1, further comprising a control unit;

wherein the control unit comprises a voltage source that is configured to apply a predetermined level of voltage across the first electrode and the second electrode; and

wherein the control unit comprises an amp meter that is configured to detect current flowing between the first electrode and the second electrode.

5. The system according to claim 4, wherein the control unit comprises an amp meter that is configured to detect a level of current flowing between the first electrode and the second electrode;

and

wherein the control unit is configured to determine whether the detected current level between the first electrode and the second electrode exceeds a threshold current level.

6. The system according to claim 5, wherein the first electrode, the second electrode, and the control unit are configured such that when the insulator coating comprises a desired level of coverage over the surface of the turbine rotor blade, the predetermined voltage level applied across the first electrode and the second electrode fails to induce the detected current level between the first electrode and the second electrode to exceed the threshold current level.

7. The system according to claim 5, wherein the first electrode, the second electrode, and the control unit are configured such that:

during a first operating condition, the detected current level between the first electrode and the second electrode does not exceed the threshold current level; and

during a second operating condition, the detected current level between the first electrode and the second electrode exceeds the threshold current level;

wherein the second operating condition comprises an operating conditioning in which a defect is present in the insulator coating.

8. The system according to claim 7, wherein the defect comprises an exposed area of a predetermined size on the turbine rotor blade, the exposed area comprising an area that is substantially no longer covered by the insulator coating;

and

wherein the predetermined size of the exposed area corresponds to an area of exposure at which the predetermined voltage level induces the detected current level to exceed the threshold current level.

9. The system according to claim 7, wherein the defect comprises one of spallation of the insulator coating and crack formation within the turbine rotor blade.

10. The system according to claim 7, wherein the first operating condition comprises an operating condition in which a desired portion of the surface of the turbine rotor blade that would be exposed to the hot-gas flowpath of the combustion turbine engine is covered by the insulator coating;

and

wherein the control unit is configured to issue a warning notification when the second operating condition occurs.

11. The system according to claim 10, wherein:

the insulator coating comprises an electrical conductivity that is less than the electrical conductivity of the turbine rotor blade;

the insulator coating comprises an electrical conductivity that is less than the approximate electrical conductivity of the hot-gas flowpath during operation between the turbine rotor blade and the second electrode; and

the desired portion comprises substantially all of the surface area of the turbine rotor blade that would be exposed to the hot-gas flowpath of the combustion turbine engine.

12. The system according to claim 1, wherein, during operation, the hot-gas flowpath of the combustion turbine engine comprises an electrically conductive doping agent;

and

wherein the electrically conductive doping agent is injected into the hot-gas flowpath at predetermined testing intervals.

13. A method for detecting defects in a turbine rotor blade of a combustion turbine engine while the combustion turbine engine is operating, the method comprising the steps of:

providing a first electrode that is electrically connected to the turbine rotor blade;

providing a second electrode that resides in proximity to the turbine rotor blade;

applying a voltage across the first electrode and the second electrode; and

detecting current flowing between the first electrode and the second electrode.

14. The method according to claim 13, further comprising the steps of coating the turbine rotor blade with an insulator coating;

wherein;

the insulator coating comprises an electrical conductivity that is less than the electrical conductivity of the turbine rotor blade; and

the insulator coating comprises an electrical conductivity that is less than the approximate electrical conductivity of the combustion gases of hot-gas flowpath between the turbine rotor blade and the second electrode during operation of the combustion turbine engine.

15. The method according to claim 14, wherein the second electrode is connected to stationary structure just downstream of a row of turbine blades in which the turbine rotor blade is included;

and

wherein the second electrode is positioned such that the second electrode is exposed to the combustion gases of the hot-gas flowpath during operation of the combustion turbine engine.

16. The method according to claim 14, further comprising the steps of:

detecting a level of current flowing between the first electrode and the second electrode; and

determining whether the detected current level exceeds a threshold current level.

17. The method according to claim 16, wherein the threshold current level corresponds to a threshold above which detected current levels comprise a high probability of being caused by a defect in the insulator coating.

18. The method according to claim 17, wherein the defect comprises an exposed area of predetermined size on the turbine rotor blade, the exposed area comprising an area that is substantially no longer covered by the insulator coating;

and

wherein the predetermined size of the exposed area corresponds to a size at which the predetermined voltage level induces the detected current level to exceed the threshold current level.

19. The method according to claim 17, wherein detected current levels that do not exceed the threshold current level correspond to current levels that occur when a desired portion of the surface area of the turbine rotor blade that would be exposed to the combustion gases of the hot-gas flowpath remains covered by the insulator coating;

further comprising the step of issuing a warning notification when the detected current level exceeds the threshold current level.

20. The method according to claim 13, further comprising the step of injecting an electrically conductive doping agent into the hot-gas flowpath at a position in the hot-gas flowpath that is upstream from the turbine rotor blade.

21. The method according the claim 20, wherein the electrically conductive doping agent is configured to increase the electrical conductivity of the combustion gases flowing through the hot-gas flowpath during operation of the combustion turbine engine.

22. The method according to claim 21, wherein the electrically conductive doping agent is injected periodically, the periods of injection corresponding to a desired testing schedule.