Protective coating systems for gas turbine engine applications and methods for fabricating the same
US10676403B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jan 16, 2014 |
| Grant date | Jun 9, 2020 |
| Priority date | — |
| Expiry date | Mar 17, 2036 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T428/26
- WIPO fieldMaterials, metallurgy
- WIPO sectorChemistry
Abstract
Protective coating systems for gas turbine engine applications and methods for fabricating such protective coating systems are provided. An exemplary protective coating system includes a substrate formed of a ceramic matrix composite material, a first coating layer formed directly on to the substrate and comprising an oxygen barrier material, a compliance material, or a bonding material and a second coating layer formed directly on to the first coating layer and comprising a thermal barrier material. The exemplary protective coating optionally includes a third coating layer partially formed directly on to the second coating layer and partially formed within at least some of the plurality of pores of the second coating layer.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.