Rotor blade an axial-flow engine
US6358003B2 · kind B2 · utility
20Cited by
4References
10Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Mar 3, 2000 |
| Grant date | Mar 19, 2002 |
| Priority date | — |
| Expiry date | Mar 3, 2020 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A rotor blade airfoil of an axial-flow turbomachine, for a fan or a compressor high-pressure stage of a gas turbine system, configured in the tip area to improve supersonic performance. The blade afflux edge has a forward-back sweep. The tip region of the blade efflux edge can be designed essentially similar to the blade afflux edge, with the tip region extending across the outer 15% to 25% of the blade span.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.