High temperature component with thermal barrier coating and gas turbine using the same
US7901790B2 · kind B2 · utility
Assignees
Inventors
Key dates
| Filing date | Sep 23, 2005 |
| Grant date | Mar 8, 2011 |
| Priority date | — |
| Expiry date | Sep 23, 2025 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T428/12944
- WIPO fieldSurface technology, coating
- WIPO sectorChemistry
Abstract
There is provided a high temperature component with a thermal barrier coating, which can be used as a high temperature component for a gas turbine, an aircraft gas turbine engine, or the like. A top coat is formed of a ceramic on a bond coat, the bond coat being formed on a heat resistant alloy substrate composed mainly of at least one element of nickel and cobalt, wherein the bond coat contains at least one of nickel and cobalt, chromium and aluminum, and further contains at least one selected from a group consisting of tantalum, cesium, tungsten, silicon, platinum, manganese and boron in a range of 0 to 20 wt %. The high temperature component according to the present invention has very high durability of a thermal-insulating ceramic layer, and is less susceptible to spalling damage.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.