Abradable coating in a gas turbine engine
US5472315A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Nov 9, 1993 |
| Grant date | Dec 5, 1995 |
| Priority date | — |
| Expiry date | Nov 9, 2013 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T428/31721
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An abradable coating is provided for use on a composite substrate which has a coefficient of thermal expansion substantially similar to that of the substrate and which is formed with a matrix resin of the same type of resin used to form the substrate. In particular, with a composite substrate formed from carbon or graphite fibers impregnated with a polyimide resin, an abradable coating formed from carbon or glass microballoons in a polyimide resin matrix has been found to avoid delamination as a result of thermal cycling between -65.degree. F. and 500.degree. F. Accordingly, that abradable coating is particularly suitable for use with composite compressor shrouds in gas turbine engines and aircraft auxiliary power units.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.