Low hub-to-tip ratio fan for a turbofan gas turbine engine
US9303589B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Nov 28, 2012 |
| Grant date | Apr 5, 2016 |
| Priority date | — |
| Expiry date | Dec 3, 2034 |
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, the fan comprising a rotor hub and a plurality of radially extending fan blades integral with the hub to form an integrally bladed rotor. Each fan blade defines a leading edge. A hub radius (RHUB) is the radius of the leading edge at the hub relative to a centerline of the fan. A tip radius (RTIP) 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 at least 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 or equal to 0.25.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.