| 发明名称 |
TURBINE VANE COOLING ARRANGEMENT |
| 摘要 |
A vane includes a pair of airfoils that have a plurality of film cooling holes that extend through an exterior surface of the airfoils. Each plurality of film cooling holes break through the exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Table 1. Each geometric coordinates is measured from a reference point on a leading edge rail of a platform of the vane. |
| 申请公布号 |
US2015211376(A1) |
申请公布日期 |
2015.07.30 |
| 申请号 |
US201514590317 |
申请日期 |
2015.01.06 |
| 申请人 |
United Technologies Corporation |
发明人 |
Riley Sarah;Anderson Kristopher K. |
| 分类号 |
F01D9/02 |
主分类号 |
F01D9/02 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A vane comprising:
a pair of airfoils having a plurality of film cooling holes that extend through an exterior surface of said airfoils, wherein each of said plurality of film cooling holes break through said exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Table 1, wherein each of said geometric coordinates is measured from a reference point on a leading edge rail of a platform of the vane. |
| 地址 |
Hartford CT US |
