| 发明名称 |
GAS TURBINE ENGINE AIRFOIL |
| 摘要 |
An airfoil of a turbine engine according to an example of the present disclosure includes, among other things, pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a gap/chord ratio and span position that defines a curve with a gap/chord ratio having a portion with a negative slope. |
| 申请公布号 |
US2016069187(A1) |
申请公布日期 |
2016.03.10 |
| 申请号 |
US201514626130 |
申请日期 |
2015.02.19 |
| 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 |
F01D5/14;F02C7/36;F02C3/107;F01D5/02;F01D15/12 |
主分类号 |
F01D5/14 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. An airfoil arrangement of a turbine engine comprising:
adjacent airfoils including pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position, wherein the airfoils have a relationship between a gap/chord ratio and span position that defines a curve with a gap/chord ratio having a portion with a negative slope, the adjacent airfoils are blades, and the gap/chord ratio is less than 1.0 at 100% span. |
| 地址 |
Hartford CT US |
