| 发明名称 |
COOLING PASSAGES FOR A GAS TURBINE ENGINE COMPONENT |
| 摘要 |
A gas turbine engine component includes a wall which includes a first surface and a second surface opposing the first surface. A plurality of cooling passages extends between the first surface and the second surface each including a metering portion and a diffusion portion. The diffusion portion includes a cast or as-consolidated surface. |
| 申请公布号 |
US2016298462(A1) |
申请公布日期 |
2016.10.13 |
| 申请号 |
US201514682207 |
申请日期 |
2015.04.09 |
| 申请人 |
United Technologies Corporation |
发明人 |
Thornton Lane;Slavens Thomas N. |
| 分类号 |
F01D5/18;F02C3/00;F01D25/12;F02C7/18;F01D9/04;F01D11/08 |
主分类号 |
F01D5/18 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A gas turbine engine component comprising:
a wall including a first surface and a second surface opposing the first surface; and a plurality of cooling passages extending between the first surface and the second surface each including a metering portion and a diffusion portion, wherein the diffusion portion includes a cast or as-consolidated surface. |
| 地址 |
Hartford CT US |
