| 发明名称 |
AIRFOIL COOLING APPARATUS |
| 摘要 |
An airfoil for a gas turbine engine, the airfoil includes a wall that has a leading edge and a trailing edge and at least partially defining a boundary of a leading edge cavity radially along the leading edge. A cooling jet structure is operatively associated with a portion of the wall proximate the leading edge and is configured to direct a cooling fluid tangent to the portion of the wall. |
| 申请公布号 |
US2016024938(A1) |
申请公布日期 |
2016.01.28 |
| 申请号 |
US201514804865 |
申请日期 |
2015.07.21 |
| 申请人 |
United Technologies Corporation |
发明人 |
Slavens Thomas N.;Snyder Brooks E.;Burdick Andrew D. |
| 分类号 |
F01D5/18 |
主分类号 |
F01D5/18 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. An airfoil for a gas turbine engine, the airfoil comprising:
a wall having a leading edge and a trailing edge, and at least partially defining a boundary of a leading edge cavity radially along the leading edge; and a cooling jet structure operatively associated with a portion of the wall proximate the leading edge and configured to direct a cooling fluid tangent to the portion of the wall. |
| 地址 |
Hartford CT US |
