Turbine engine part coated in a thermal barrier, and a method of obtaining it
US11466370B2 · kind B2 · utility
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10Claims
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Key dates
| Filing date | Oct 31, 2017 |
| Grant date | Oct 11, 2022 |
| Priority date | — |
| Expiry date | Apr 24, 2039 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R2900/00018
- WIPO fieldSurface technology, coating
- WIPO sectorChemistry
Abstract
A turbine engine part coated in at least a first ceramic layer forming a thermal barrier and including a ceramic material with first ceramic fibers dispersed in the first layer. The first layer may have a chemical composition gradient between a material for forming a thermal barrier and a material for providing protection against calcium and magnesium aluminosilicates, which is present at a greater content in an outer zone of the first layer, and/or the first layer may be porous and may present a porosity gradient such that an outer portion of the first layer presents lower porosity.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.