Repair of gas turbine engine component coated with a thermal barrier coating
US5972424A · kind A · utility
66Cited by
32References
7Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | May 21, 1998 |
| Grant date | Oct 26, 1999 |
| Priority date | — |
| Expiry date | May 21, 2018 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49318
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine component coated with a thermal barrier coating that includes a metallic bond coat and a ceramic top coat is repaired by removing the ceramic top coat from an engine-run gas turbine engine component and inspecting the component. A metallic flash coat is applied to at least a portion of the component. A ceramic top coat is then applied over predetermined portions of the component, including the portion to which the metallic flash coat was applied.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.