Abrasive ceramic matrix turbine blade tip and method for forming
US5952110A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Dec 24, 1996 |
| Grant date | Sep 14, 1999 |
| Priority date | — |
| Expiry date | Dec 24, 2016 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T428/12944
- WIPO fieldSurface technology, coating
- WIPO sectorChemistry
Abstract
An abrasive coating suitable for forming an abrasive blade tip of a gas turbine engine. The coating is characterized as being capable of abrading a ceramic shroud at elevated temperatures during the in-service operation of the engine, and being resistant to oxidation and hot corrosion within the engine environment. The abrasive coating includes an MCrAl alloy layer, a ceramic layer overlying the alloy layer so as to form an outer surface of the abrasive coating, and abrasive particles dispersed between the alloy layer and the ceramic layer so that at least some of the abrasive particles are partially embedded in the alloy layer and also partially embedded in the ceramic layer. In addition, at least some of the abrasive particles project above the outer surface of the abrasive coating formed by the ceramic layer.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.