Gas turbine engine fan blade
US10473112B2 · kind B2 · utility
2Cited by
5References
20Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Feb 12, 2018 |
| Grant date | Nov 12, 2019 |
| Priority date | — |
| Expiry date | Jun 9, 2038 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A fan blade is provided with an aerofoil portion for which, at radii between 20% and 40% of the blade span, the location of the position of maximum thickness along the camber line is at less than a defined percentage of the total length of the camber line. For all cross-sections through the aerofoil portion at radii greater than 70% of the blade span, the location of the position of maximum thickness along the camber line is at more than a defined percentage of the total length of the camber line. The geometry of the fan blade may result in a lower susceptibility to flutter.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.