| 发明名称 |
GAS TURBINE ENGINE SERPENTINE COOLING PASSAGE |
| 摘要 |
A gas turbine engine component includes a structure having a cooling passage providing upstream and downstream portions separated from one another by an inner wall and fluidly connected by a bend. The downstream portion includes an outer wall opposite the inner wall to provide a downstream region extending between the inner and outer walls. A turbulence promoter extends from the outer wall adjacent to the bend in the downstream portion. The turbulence promoter is absent from a stagnation region adjoining the inner wall adjacent to the bend in the downstream portion |
| 申请公布号 |
US2014219813(A1) |
申请公布日期 |
2014.08.07 |
| 申请号 |
US201213618178 |
申请日期 |
2012.09.14 |
| 申请人 |
Perez Rafael A.;Pietraszkiewicz Edward F.;Levine Jeffrey R.;Mongillo, JR. Dominic J. |
发明人 |
Perez Rafael A.;Pietraszkiewicz Edward F.;Levine Jeffrey R.;Mongillo, JR. Dominic J. |
| 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:
a structure having a cooling passage providing upstream and downstream portions separated from one another by an inner wall and fluidly connected by a bend, the downstream portion included an outer wall opposite the inner wall to provide a downstream region extending between the inner and outer walls; and a turbulence promoter extending from the outer wall adjacent to the bend in the downstream portion, the turbulence promoter absent from a stagnation region adjoining the inner wall adjacent to the bend in the downstream portion. |
| 地址 |
Arecibo PR US |
