| 发明名称 |
COOLING CONFIGURATIONS FOR TURBINE BLADES |
| 摘要 |
A blade in a turbine of a gas turbine engine that includes: an outer surface bending along an edge at an angle greater than about 120° so to define a first outer surface to a first side of the edge and a second outer surface to a second side of the edge; an internal flow passage; and a forked cooling channel configured so to fluidly connect the internal flow passage to a first film cooling port and a second film cooling port formed to each side of the edge. |
| 申请公布号 |
US2016186577(A1) |
申请公布日期 |
2016.06.30 |
| 申请号 |
US201414585854 |
申请日期 |
2014.12.30 |
| 申请人 |
General Electric Company |
发明人 |
Willett, JR. Fred Thomas |
| 分类号 |
F01D5/18;F01D9/04;F01D25/12;F01D5/14 |
主分类号 |
F01D5/18 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A blade for a turbine of a gas turbine engine, the blade comprising:
an outer surface sharply bending along an edge so to define on each side of the edge a first outer surface and a second outer surface; an internal flow passage; and a forked cooling channel configured so to fluidly connect the internal flow passage to a first film cooling port formed through the first outer surface and a second film cooling port formed through the second outer surface; wherein the first film cooling port and the second film cooling port each comprises a shallow discharge angle. |
| 地址 |
Schenectady NY US |
