Thermal barrier coating, manufacturing method thereof, turbine part and gas turbine
US7354663B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Apr 2, 2004 |
| Grant date | Apr 8, 2008 |
| Priority date | — |
| Expiry date | Apr 2, 2024 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T428/12618
- WIPO fieldSurface technology, coating
- WIPO sectorChemistry
Abstract
A thermal barrier coating enabling to prevent peeling of layer in a high temperature use and still having a high thermal barrier effect, a turbine part coated by this thermal barrier coating and a gas turbine comprising this turbine part are provided. The thermal barrier coating comprises a base material 21 of high temperature heat resistant alloy and a ceramics layer 23 formed on the base material 21. The ceramics layer 23 comprises ZrO2 added with Yb2O3 as stabilizer and is laminated on the base material via a bond coat layer 22 laminated as a metallic bond layer. A plurality of cracks 23A are preferably introduced in the ceramics layer 23. The turbine part is constructed having its surface coated with the above thermal barrier coating.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.