Method for repairing a thermal barrier coating and repaired coating formed thereby
US6413578B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Oct 12, 2000 |
| Grant date | Jul 2, 2002 |
| Priority date | — |
| Expiry date | Oct 12, 2020 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T428/252
- WIPO fieldSurface technology, coating
- WIPO sectorChemistry
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/c…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.