Gas turbine engine component with an abrasive coating
US10465536B2 · kind B2 · utility
1Cited by
6References
8Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Apr 22, 2016 |
| Grant date | Nov 5, 2019 |
| Priority date | — |
| Expiry date | Sep 7, 2037 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2300/6032
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine component includes a rotor blade having a squealer tip comprising a projecting lip, the rotor blade further having a raised rim running along both edges of each projecting kip of the squealer tip, and an abrasive coating formed of hard particles embedded in a retaining matrix covering a tip region of the rotor blade within an area bounded by the raised rim. The raised rim has a height of between 50% and 75% of a mean diameter of the hard particles.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.