| 发明名称 |
GAS TURBINE ENGINE TURBINE BLADE TIP COOLING |
| 摘要 |
A gas turbine engine component includes a structure having a surface configured to be exposed to a hot working fluid. The surface includes a recessed pocket that is circumscribed by an overhang. At least one cooling groove is provided by the overhang. |
| 申请公布号 |
US2016265366(A1) |
申请公布日期 |
2016.09.15 |
| 申请号 |
US201415032736 |
申请日期 |
2014.10.10 |
| 申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
Snyder Brooks E.;Slavens Thomas N. |
| 分类号 |
F01D5/18;B22D25/02;B22F3/105;B23K15/00;B23K26/342 |
主分类号 |
F01D5/18 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A gas turbine engine component comprising:
a structure having a surface configured to be exposed to a hot working fluid, the surface includes a recessed pocket that is circumscribed by an overhang, and at least one cooling groove provided by the overhang. |
| 地址 |
Farmington CT US |
