| 发明名称 | Gas turbine engine fan blade airfoil profile | ||
| 摘要 | A fan blade for a gas turbine engine includes an airfoil that includes leading and trailing edges joined by pressure and suction sides to provide an exterior airfoil surface that extends in a radial direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate scaled by a local axial chord. A circumferential coordinate is scaled by the local axial chord, and a span location. The local axial chord corresponds to a width of the airfoil between the leading and trailing edges at the span location. | ||
| 申请公布号 | US8997494(B2) | 申请公布日期 | 2015.04.07 |
| 申请号 | US201213664647 | 申请日期 | 2012.10.31 |
| 申请人 | United Technologies Corporation | 发明人 | Chuang Sue-Li;Dong Yuan;Hingorani Sanjay S.;Prasad Dilip |
| 分类号 | F02C1/00;F02G3/00;F04D29/38;F01D5/14 | 主分类号 | F02C1/00 |
| 代理机构 | Carlson, Gaskey & Olds, P.C. | 代理人 | Carlson, Gaskey & Olds, P.C. |
| 主权项 | 1. A fan blade for a gas turbine engine comprising: an airfoil including leading and trailing edges joined by pressure and suction sides to provide an exterior airfoil surface extending in a radial direction to a tip; and wherein the external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by the local axial chord, and a span location, wherein the local axial chord corresponds to a width of the airfoil between the leading and trailing edges at the span location. | ||
| 地址 | Hartford CT US | ||