System for on-line assessment of the condition of thermal coating on a turbine vane

• US 7,123,031 B2
• Filed: 12/20/2004
• Issued: 10/17/2006
• Est. Priority Date: 12/20/2004
• Status: Active Grant

• Current Assignee: Siemens Energy Incorporated (Siemens AG)
• Original Assignee: Siemens Power Generation, Inc.
• Inventors: Twerdochlib, Michael
• Primary Examiner(s): Deb, Anjan
• Assistant Examiner(s): NGUYEN, HOAI AN D
• Application Number:
  US11/018,771
• Publication Number:
  US 20060132149A1
• Time in Patent Office: 666 Days
• Field of Search: 324/693, 324/691, 324/649, 324/600, 324/667, 324/378, 324/664, 324/421, 324/525, 324/158.1, 324/76.11, 324/71.1, 324/715, 324/716, 324/718, 324/722, 324/724, 324/71.2, 342/118, 340/679, 340/680
• US Class Current: 324/693
• CPC Class Codes: G01B 7/18 using change in resistance
• CPC Class Codes: G01N 2203/0664 using witness specimens

Abstract

Aspects of the invention relate to a system for assessing the condition of a thermal barrier coating on a turbine vane during engine operation. According to embodiments of the invention, one or more wires can be passed along the airfoil portion of the vane. The wires can extend over, within, or beneath the thermal coating. An electrical current can be passed along the wires, and electrical resistance can be measured across the wires. Thus, if a portion of the thermal coating becomes damaged, then the wires located in that area may break. A disconnect in the wires can lead to an increase in resistance across the wires, which can alert an operator to a problem. Some assessment systems can provide a general indication of the magnitude of damage and whether the damage is spreading.

Claims

1. A system for monitoring the condition of a coating on a turbine engine component comprising:

the turbine engine component;

the coating applied aver at least a portion of the turbine engine component;

a plurality of assessment wires extending about at least a portion of the component such that at least a portion of each assessment wire is in contact with the coating, wherein the plurality of assessment wires includes a first group of assessment wires and a second group of assessment wires, and wherein the first group of wires and the second group of wires are angled relative to each other such that each wire from the first group of wires crosses at least one wire from the second group of wires;

a power source electrically connected to the plurality of assessment wires, wherein an electrical current is passed along the plurality of assessment wires; and

a measuring device operatively associated with the plurality of assessment wires so as to determine the electrical resistance across plurality of assessment wires, whereby increases in resistance across the plurality of assessment wires indicate a disconnect in the at least one of the plurality of assessment wires which further indicates possible damage to the coating.

2. The system of claim 1 wherein the turbine engine component is an airfoil.

3. The system of claim 1 wherein the coating is a thermal barrier coating.

4. The system of claim 1 wherein the plurality of assessment wires is embedded within the coating.

5. The system of claim 1 further including a thermocouple provided in contact with at least the coating, wherein the thermocouple measures the temperature of at least the coating, whereby the temperature of the coating is used to discount changes in electrical resistance attributed to a change in temperature.

6. A system for monitoring the condition of a coating on an airfoil comprising:

the airfoil having a radially inner end and a radially outer end, the airfoil defining an outer peripheral surface;

a thermal coating substantially covering the outer peripheral surface of the airfoil;

a plurality of assessment wires extending about at least a portion of the airfoil, wherein at least a portion of each assessment wire is in contact with the thermal coating;

a power source electrically connected with the plurality of assessment wires, wherein an electrical current is passed along the plurality of assessment wires;

a measurement device operatively associated with the plurality of assessment wires so as to determine the electrical resistance across the assessment wires, whereby increases in resistance across the assessment wires can provide information as to the size and growth of possible damage to the thermal coating.

7. The system of claim 6 further including:

a first wire and a second wire operatively associated with the power source, wherein each of the plurality of assessment wires is electrically connected at one end to the first wire and at the other end to the second wire, wherein the first wire delivers the electrical current to each of the plurality of assessment wires and the second wire receives current from each of the assessment wires.

8. The system of claim 6 wherein the plurality of assessment wires is embedded in the thermal coating.

9. The system of claim 6 wherein the plurality of assessment wires is disposed beneath the thermal coating.

10. The system of claim 6 wherein the plurality of assessment wires is disposed over she thermal coating.

11. The system of claim 6 wherein at least one of the plurality of assessment wires is electrically insulated from the rest of the plurality of assessment wires.

12. The system of claim 6 wherein the plurality of wires is substantially equally spaced.

13. The system of claim 6 wherein the plurality of wires extends from near one radial end of the airfoil to near the opposite radial end of the airfoil.

14. The system of claim 6 wherein the plurality of wires extends substantially about the leading edge of the airfoil.

15. The system of claim 6 wherein the plurality of wires includes at least a first group of wires and a second group of wires, the first group of wires and the second group of wires are angled relative to each other such that each wire from the first group of wires crosses at least one wire from she second group of wires.

16. The system of claim 15 wherein the first and second groups of wires are electrically connected at at least some of the crossing points therebetween.

17. A method of on-line evaluation of the condition of a coating on an airfoil comprising:

providing a turbine engine including the airfoil with an outer peripheral surface that is at least partially covered with a thermal coating, wherein at least one assessment wire extends about at least a portion of the outer peripheral surface of the airfoil such that at least a portion of each assessment wire is in contact with the coating;

providing a power source that is operatively connected to the at least one assessment wire, wherein the at least one assessment wire continuously receives the electrical current from the power source;

determining resistance across the at least one assessment wire; and

monitoring changes in resistance across the at least one assessment wire, whereby an increase in the resistance across the at least one assessment wire indicates a general assessment of the condition of the, thermal coating.

18. The method of claim 17 wherein the step of determining is conducted on a substantially continuous basis.

19. The method of claim 17 wherein the and at least one assessment wire continuously receives the electrical current during engine operation wherein the determining step is performed during engine operation.