| 发明名称 |
ENGINE COMPONENT HAVING SUPPORT WITH INTERMEDIATE LAYER |
| 摘要 |
Disclosed is a gas turbine engine component, and a method for forming the component. The component includes a first portion, a second portion formed separately from the first portion, and an intermediate layer provided between the first portion and the second portion. |
| 申请公布号 |
US2016040539(A1) |
申请公布日期 |
2016.02.11 |
| 申请号 |
US201414782014 |
申请日期 |
2014.04.01 |
| 申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
McCaffrey Michael G. |
| 分类号 |
F01D5/30;B28B1/30;F01D5/02;F02C3/04;F01D5/14;F01D9/04 |
主分类号 |
F01D5/30 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A gas turbine engine, comprising:
a compressor section, a combustor section, and a turbine section, the turbine section including a stationary stage and a rotating stage; a component provided in one of the stationary stage and the rotating stage, the component including a first portion, a second portion formed separately from the first portion, and an intermediate layer provided between the first portion and the second portion. |
| 地址 |
Hartford CT US |
