| 发明名称 | Gas turbine engine airfoil | ||
| 摘要 | An airfoil for a turbine engine includes an airfoil having pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a leading edge dihedral and a span position. The leading edge dihedral is negative from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning, and a negative dihedral corresponds to pressure side-leaning. | ||
| 申请公布号 | US9353628(B2) | 申请公布日期 | 2016.05.31 |
| 申请号 | US201514624025 | 申请日期 | 2015.02.17 |
| 申请人 | UNITED TECHNOLOGIES CORPORATION | 发明人 | Gallagher Edward J.;Monzon Byron R.;Liu Ling;Li Linda S.;Whitlow Darryl;Ford Barry M. |
| 分类号 | F01D5/06;F01D5/14 | 主分类号 | F01D5/06 |
| 代理机构 | Carlson, Gaskey & Olds, P.C. | 代理人 | Carlson, Gaskey & Olds, P.C. |
| 主权项 | 1. An airfoil for a turbine engine comprising: an airfoil having pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, wherein the airfoil has a relationship between a leading edge dihedral and a span position, the leading edge dihedral negative from the 0% span position to the 100% span position, wherein a positive dihedral corresponds to suction side-leaning, and a negative dihedral corresponds to pressure side-leaning. | ||
| 地址 | Hartford CT US | ||