| 发明名称 | Low radius ratio fan for a gas turbine engine | ||
| 摘要 | A fan blade for a gas turbine engine includes: a straight axial dovetail, an airfoil, and a transition section disposed between the dovetail and the airfoil, the fan blade having opposed pressure and suction sides, and further including at least one shoulder protruding from a nominal surface of a selected one of the pressure and suction sides, wherein the at least one shoulder includes a boss defining a side face, and an upper section extending radially outward from the boss and tapering inward to join a nominal surface of the selected side. | ||
| 申请公布号 | US9239062(B2) | 申请公布日期 | 2016.01.19 |
| 申请号 | US201213608754 | 申请日期 | 2012.09.10 |
| 申请人 | General Electric Company | 发明人 | Lamboy Jorge Orlando;Kray Nicholas Joseph;Pauley Gerald Alexander;Li Qiang;Wilkin, II Daniel Allen;Davis Tod Winton |
| 分类号 | F04D29/32;F01D5/14;F01D5/30;F01D11/00 | 主分类号 | F04D29/32 |
| 代理机构 | General Electric Company | 代理人 | General Electric Company ;Andes William Scott |
| 主权项 | 1. A fan blade for a gas turbine engine, comprising: a straight axial dovetail, an airfoil, and a transition section disposed between the dovetail and the airfoil, the fan blade having opposed pressure and suction sides, and further including at least one shoulder protruding from a nominal surface of a selected one of the pressure and suction sides, wherein the at least one shoulder includes a boss defining a side face, and an upper section extending radially outward from the boss and tapering inward to join a nominal surface of the selected side, wherein the dovetail, airfoil, and transition section are formed as a composite layup comprising a plurality of layers of fibers embedded in a matrix. | ||
| 地址 | Schenectady NY US | ||