Method for repairing a thermal barrier coating and repaired coating formed thereby

• US 6,413,578 B1
• Filed: 10/12/2000
• Issued: 07/02/2002
• Est. Priority Date: 10/12/2000
• Status: Expired due to Term

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Stowell, William R., Rentz, Thomas Walter, Begovich, Joseph Thomas, Ivkovich, Dainel P. Jr., Johnson, Robert A., Murphy, Jane Ann, Lee, Ching-Pang, Skoog, Andrew J.
• Primary Examiner(s): Beck, Shrive P.
• Assistant Examiner(s): Michener, Jennifer Kolb
• Application Number:
  US09/687,721
• Time in Patent Office: 628 Days
• Field of Search: 427/140, 427/142, 427/201, 427/226, 427/446, 427/453
• US Class Current: 427/142
• CPC Class Codes: C23C 24/08 by application of heat or pressure and heat C23C24/04 takes precedence
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft
• CPC Class Codes: Y10T 428/20 Patched hole or depression
• CPC Class Codes: Y10T 428/24479 including variation in thickness
• CPC Class Codes: Y10T 428/24521 with component conforming to contour of nonplanar surface
• CPC Class Codes: Y10T 428/25 Web or sheet containing structurally defined element or component and including a second component containing structurally defined particles
• CPC Class Codes: Y10T 428/252 Glass or ceramic [i.e., fired or glazed clay, cement, etc.] [porcelain, quartz, etc.]

Abstract

A method of repairing a thermal barrier coating on a component designed for use in a hostile thermal environment, such as turbine, combustor and augmentor components of a gas turbine engine. The method more particularly involves repairing a thermal barrier coating on a component that has suffered localized spallation of the thermal barrier coating. After cleaning the surface area of the component exposed by the localized spallation, a ceramic paste comprising a ceramic powder in a binder is applied to the surface area of the component. The binder is then reacted to yield a ceramic-containing repair coating that covers the surface area of the component and comprises the ceramic powder in a matrix of a material formed when the binder was reacted. The binder is preferably a ceramic precursor material that can be converted immediately to a ceramic or allowed to thermally decompose over time to form a ceramic, such that the repair coating has a ceramic matrix. The repair method can be performed while the component remains installed, e.g., in a gas turbine engine. Immediately after the reaction step, the gas turbine engine can resume operation during which the binder is further reacted/converted and the strength of the repair coating increases.

Claims

1. A method for repairing a thermal barrier coating on a component that has suffered localized spallation of the thermal barrier coating, the method comprising the steps of:

applying a ceramic paste on a surface area of the component exposed by the localized spallation, the ceramic paste comprising a ceramic powder in a binder, the ceramic powder comprising alumina and zirconia, the binder being chosen from the group consisting of ceramic precursor binders that thermally decompose to form a refractory material; and

then

heating the binder to yield a repair coating that covers the surface area of the component, the repair coating comprising the ceramic powder in a matrix that comprises the refractory material formed by reacting the binder.

2. A method according to claim 1, further comprising the step of cleaning the surface area of the component prior to the applying step so as to remove contaminants without removing any adherent residual fragments of the thermal barrier coating.

3. A method according to claim 1, wherein the ceramic powder further comprises at least one ceramic material chosen from the group consisting of hafnia, magnesia and silica.

4. A method according to claim 1, wherein the ceramic powder consists of about 5 to about 85 weight percent alumina, 0 to about 40 weight percent silica, up to about 60 weight percent zirconia, 0 to about 55 weight percent hafnia, 0 to about 55 weight percent magnesia and 0 to about 25 weight percent zinc titanate.

5. A method according to claim 1, wherein the ceramic powder comprises about 42 weight percent alumina and about 58 weight percent zirconia.

6. A method according to claim 1, wherein the binder is a silicone and constitutes up to about 45 weight percent of the ceramic paste.

7. A method according to claim 1, wherein the binder is a phosphate-based composition and constitutes up to about 20 weight percent of the ceramic paste.

8. A method according to claim 1, wherein the component is installed in a gas turbine engine.

9. A method according to claim 8, wherein the method is performed while the component remains installed in the gas turbine engine.

10. A method according to claim 1, wherein the gas turbine engine is operated after the reaction step during which the binder further reacts and the matrix consists of a ceramic material.

11. A method according to claim 1, wherein the thermal barrier coating is yttria-stabilized zirconia deposited on a metallic bond coat on the component by plasma spraying.

12. A method for repairing a thermal barrier coating on a component installed in a gas turbine engine and which has suffered localized spallation of the thermal barrier coating so as to expose a surface area defined at least in part by an oxide scale on the component, the method comprising the steps of:

without removing the component from the gas turbine engine, cleaning the surface area of the component exposed by the localized spallation so as to remove contaminants without damaging the oxide scale;

applying a ceramic paste on the surface area of the component, the ceramic paste comprising a ceramic powder in a ceramic precursor binder dissolved in a solvent, the ceramic powder comprising at last one ceramic material chosen from the group consisting of alumina, zirconia, hafnia, magnesia and silica, the binder being chosen from the group consisting of phosphate-based compositions;

evaporating the solvent and heating the ceramic paste to yield a ceramic-containing repair coating that covers the surface area of the component, the repair coating comprising the ceramic powder in a matrix consisting of a phosphate glass material formed by thermal decomposition of the binder; and

then

operating the gas turbine engine during which the phosphate glass material forms ceramic-to-ceramic bonds with the ceramic powder.

13. A method according to claim 12, herein the ceramic powder consists of about 5 to about 85 weight percent alumina, 0 to about 40 weight percent silica, 0 to about 60 weight percent zirconia, 0 to about 55 weight percent hafnia, 0 to about 55 weight percent magnesia and 0 to about 25 weight percent zinc titanate.

14. A method according to claim 12, wherein the ceramic powder consists of about 42 weight percent alumina and about 58 weight percent zirconia.

15. A method according to claim 12, wherein the ceramic powder comprises alumina and zirconia.

16. A method according to claim 12, wherein the binder constitutes up to about 20 weight percent of the ceramic paste.

17. A method according to claim 13, wherein the thermal barrier coating is yttria-stabilized zirconia deposited on a metallic bond coat on the component by plasma spraying.