Application of dense vertically cracked and porous thermal barrier coating to a gas turbine component
US8511993B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Aug 14, 2009 |
| Grant date | Aug 20, 2013 |
| Priority date | — |
| Expiry date | Oct 8, 2031 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2230/90
- WIPO fieldSurface technology, coating
- WIPO sectorChemistry
Abstract
A configuration for coating a turbine component such as a blade or vane with various forms of thermal barrier coating to provide enhanced temperature capability and increased strain tolerance is disclosed. A gas path surface of the platform, airfoil and airfoil fillet region are first coated with a bond coating. A dense vertically cracked (DVC) thermal barrier coating is then applied to at least the gas path surface of the platform and can be applied to the fillet region. A porous thermal barrier coating is then applied to at least the airfoil. The porous thermal barrier coating can also be applied over the DVC thermal barrier coating if desired.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.