| 发明名称 |
GAS TURBINE ENGINE AIRFOIL |
| 摘要 |
An airfoil of a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a stagger angle and span position that defines a curve with a stagger angle that is greater than 35° from 0% span to at least 50% span. |
| 申请公布号 |
US2016348691(A1) |
申请公布日期 |
2016.12.01 |
| 申请号 |
US201515114922 |
申请日期 |
2015.02.12 |
| 申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
Gallagher Edward J.;Brilliant Lisa I.;Straccia Joseph C.;Balamucki Stanley J.;Stephens Mark A.;Hudon Kate |
| 分类号 |
F04D29/38;F01D25/24;F02K3/06;F04D29/32;F02C3/04;F02C7/36 |
主分类号 |
F04D29/38 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. An airfoil of a turbine engine comprising:
pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position, wherein the airfoil has a relationship between a stagger angle and span position that defines a curve with a stagger angle that is greater than 35° from 0% span to at least 50% span. |
| 地址 |
Hartford CT US |
