| 发明名称 | Low hub-to-tip ratio fan for a turbofan gas turbine engine | ||
| 摘要 | 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. | ||
| 申请公布号 | US9303589(B2) | 申请公布日期 | 2016.04.05 |
| 申请号 | US201213687540 | 申请日期 | 2012.11.28 |
| 申请人 | PRATT & WHITNEY CANADA CORP. | 发明人 | Heikurinen Kari;Townsend Peter |
| 分类号 | F02K3/06;F04D29/02;F04D29/32;F01D5/30;F01D5/34;B23K20/12;F01D5/14 | 主分类号 | F02K3/06 |
| 代理机构 | Norton Rose Fulbright Canada LLP | 代理人 | Norton Rose Fulbright Canada LLP |
| 主权项 | 1. A fan for a turbofan gas turbine engine, the fan comprising a rotor hub and a plurality of fan blades arranged in a single blade row on the rotor hub, the fan blades radially extending from and being integral with the hub to form an integrally bladed rotor, each of the fan blades of the single blade row having a leading edge, 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, and wherein the ratio of the hub radius to the tip radius (RHUB/RTIP) is than 0.29. | ||
| 地址 | Longueuil CA | ||