Component with repaired thermal barrier coating
US6919121B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | May 23, 2002 |
| Grant date | Jul 19, 2005 |
| Priority date | — |
| Expiry date | Nov 9, 2022 |
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 (16) on a component (10) 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 (16) on a component (10) that has suffered localized spallation (20) of the thermal barrier coating (16). After cleaning the surface area (22) of the component (10) exposed by the localized spallation (20), a ceramic paste (24) comprising a ceramic powder in a binder is applied to the surface area (22) of the component (10). The binder is then reacted to yield a ceramic-containing repair coating (26) 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 (26) has a ceramic matrix. The repair method can be performed while the component (10) remains installed, e.g., in a gas turbine engine. Immediately after the reaction step, the gas turbi…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.