| 发明名称 |
GAS TURBINE ENGINE AIRFOIL TURBULATOR FOR AIRFOIL CREEP RESISTANCE |
| 摘要 |
A gas turbine engine component includes spaced apart walls that extend in a load direction and provide a cooling passage. The cooling passage provides a tortuous passage having a generally straight portion that extends in the load direction and a bend transverse to the load direction. Elongated turbulators protrude from at least one of the walls and extend substantially in the load direction. The elongated turbulators are substantially within the generally straight portion. |
| 申请公布号 |
US2016208620(A1) |
申请公布日期 |
2016.07.21 |
| 申请号 |
US201414915455 |
申请日期 |
2014.08.27 |
| 申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
Thistle Charles;Thornton Lane |
| 分类号 |
F01D5/18 |
主分类号 |
F01D5/18 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A gas turbine engine component comprising:
spaced apart walls extending in a load direction and providing a cooling passage, the cooling passage providing a tortuous passage having a generally straight portion extending in the load direction and a bend transverse to the load direction; and elongated turbulators protruding from at least one of the walls and extending substantially in the load direction, the elongated turbulators substantially within the generally straight portion. |
| 地址 |
Hartford CT US |
