Low hub-to-tip ratio fan for a turbofan gas turbine engine
US10408223B2 · kind B2 · utility
1Cited by
23References
19Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jun 7, 2017 |
| Grant date | Sep 10, 2019 |
| Priority date | — |
| Expiry date | Feb 12, 2038 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49245
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A fan for a turbofan gas turbine engine having a low hub-to-tip ratio is disclosed. The fan includes a rotor hub and a plurality of radially extending fan blades. Each fan blade defines a hub radius (RHUB), which is the radius of the leading edge at the hub relative to a centerline of the fan, and a tip radius (RTIP), which is the radius of the leading edge at a tip of the fan blade relative to the centerline of the fan. The ratio of the hub radius to the tip radius (RHUB/RTIP) is less than 0.29. In a particular embodiment, this ratio is between 0.25 and 0.29. In another particular embodiment, this ratio is less than 0.25.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.