| 发明名称 |
TURBINE AIRFOIL FILM COOLING HOLES |
| 摘要 |
A turbomachinery component includes an airfoil section with a cooling passage extending within the airfoil section. A wall is defined between the cooling passage and an exterior surface of the airfoil. At least one row of cooling holes is positioned along a cooling portion of the external wall proximate a leading edge of the airfoil for fluid communication between the cooling passage and the exterior surface of the airfoil. The cooling portion of the airfoil wall is thicker than an average adjacent airfoil wall thickness. |
| 申请公布号 |
US2016326886(A1) |
申请公布日期 |
2016.11.10 |
| 申请号 |
US201514707887 |
申请日期 |
2015.05.08 |
| 申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
Lewis Scott D. |
| 分类号 |
F01D5/18;F01D25/12;F01D25/30;F01D5/14;F01D9/04 |
主分类号 |
F01D5/18 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A turbomachinery component, comprising:
an airfoil section; a cooling passage extending within the airfoil section; a wall defined between the cooling passage and an exterior surface of the airfoil; and at least one row of cooling holes along a cooling portion of the external wall proximate a leading edge of the airfoil for fluid communication between the cooling passage and the exterior surface of the airfoil, wherein the cooling portion of the airfoil wall is thicker than an average adjacent airfoil wall thickness. |
| 地址 |
FARMINGTON CT US |
