Abradable component for a gas turbine engine
US8038388B2 · kind B2 · utility
8Cited by
45References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Mar 5, 2007 |
| Grant date | Oct 18, 2011 |
| Priority date | — |
| Expiry date | Sep 9, 2029 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2230/90
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine component includes an airfoil having a radial outward end and a radial inward end. A seal member is positioned adjacent to the radial inward end of the airfoil. A tip of the radial inward end of the airfoil is coated with an abradable material. The seal member is coated with an abrasive material.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.