Thermal barrier coating systems including a rare earth aluminate layer for improved resistance to CMAS infiltration and coated articles
US8062759B2 · kind B2 · utility
18Cited by
2References
11Claims
0Family size
Assignee
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Key dates
| Filing date | Dec 27, 2007 |
| Grant date | Nov 22, 2011 |
| Priority date | — |
| Expiry date | Sep 20, 2030 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T428/12667
- WIPO fieldSurface technology, coating
- WIPO sectorChemistry
Abstract
Thermal barrier coating systems for use with hot section components of a gas turbine engine include an inner layer overlying a bond coated substrate and a top layer overlying at least a portion of the inner layer. The inner layer includes a thermal barrier material such as yttria-stabilized zirconia. The top layer includes a rare earth aluminate. The thicknesses and microstructures of the layers may be varied depending on the type of component to be coated. Articles incorporating the thermal barrier coating system exhibit improved resistance to CMAS infiltration.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.