Ceramic-coated blade of gas turbine and method of producing same
US6042951A · kind A · utility
Assignees
Inventors
Key dates
| Filing date | Feb 2, 1998 |
| Grant date | Mar 28, 2000 |
| Priority date | — |
| Expiry date | Feb 2, 2018 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T428/12618
- WIPO fieldSurface technology, coating
- WIPO sectorChemistry
Abstract
A ceramic-coated blade of a gas turbine and a method of producing the same, in which the thickening of an Al.sub.2 O.sub.3 layer at the interface between a ceramic layer and a primary layer is sufficiently prevented for a long period of time, thereby positively suppressing the separation of the ceramic layer. Using powder of MCrAlY alloy (Co-32% Ni-21% Cr-8% Al-0.5% Y), a primary layer (alloy coating layer) is formed on a surface of a substrate made of a heat-resistant Ni base alloy (Rene'-80). Further, a heat-resistant ceramic layer, comprising a mixture of ion-conductive ZrO.sub.2 -8 wt. % Y.sub.2 O.sub.3 ceramic and insulative ceramic (e.g. Al.sub.2 O.sub.3), is formed on the alloy coating layer. This mixture has a columnar structure in which columnar crystals are grown by a gas phase in a direction of a thickness of the coating, or a porous structure in which flattened particles brought about from molten particles caused to fly at high velocity are laminated.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.