发明名称 |
BLADE OUTER AIR SEAL COOLING PASSAGE |
摘要 |
A gas turbine engine component includes a structure including a first wall and a second wall that provide a cooling passage. The cooling passage extends a length from a first end to a second end. A cluster of impingement inlet holes is provided in the second wall at the first end. An outlet is provided at the second end. |
申请公布号 |
US2016319698(A1) |
申请公布日期 |
2016.11.03 |
申请号 |
US201415104092 |
申请日期 |
2014.12.10 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
Romanov Dmitriy A. |
分类号 |
F01D25/12;F01D11/08 |
主分类号 |
F01D25/12 |
代理机构 |
|
代理人 |
|
主权项 |
1. A gas turbine engine component comprising:
a structure including a first wall and a second wall that provide a cooling passage, the cooling passage extends a length from a first end to a second end, a cluster of impingement inlet holes is provided in the second wall at the first end, and an outlet is provided at the second end. |
地址 |
Hartford CT US |