Gas turbine engine fan blade
US10577937B2 · kind B2 · utility
1Cited by
3References
18Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Feb 12, 2018 |
| Grant date | Mar 3, 2020 |
| Priority date | — |
| Expiry date | Oct 22, 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, for cross-sections through the aerofoil portion at radii between 15% and 25% of the blade span from the root radius, the average leading edge thickness is greater than the leading edge thickness at the tip. 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.