| 发明名称 |
COMPONENT FOR A GAS TURBINE ENGINE |
| 摘要 |
A component for a gas turbine engine includes a first surface and a second surface. The component additionally includes one or more layers of ceramic matrix composite material extending between the first and second surfaces. A thermal void extends between a first end and a second end. The second end of the thermal void is a terminal end embedded in the component between the first and second surfaces. |
| 申请公布号 |
US2017122109(A1) |
申请公布日期 |
2017.05.04 |
| 申请号 |
US201514926294 |
申请日期 |
2015.10.29 |
| 申请人 |
General Electric Company |
发明人 |
Bunker Ronald Scott;Gallier Kirk D.;Frey David Alan |
| 分类号 |
F01D5/18;F01D9/04;F04D29/54;F01D5/28;F04D29/38;F01D5/14;F01D25/12 |
主分类号 |
F01D5/18 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A component for a gas turbine engine defining a first surface and a second surface, the component comprising:
one or more layers of a ceramic matrix composite material extending between the first and second surfaces, wherein the component defines a thermal void extending between a first end and a second end, the second end of the thermal void being a terminal end embedded in the component between the first surface and the second surface. |
| 地址 |
Schenectady NY US |
