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 |
WO2015130380(A2) |
申请公布日期 |
2015.09.03 |
申请号 |
WO2014US69570 |
申请日期 |
2014.12.10 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
ROMANOV, DMITRIY A. |
分类号 |
F02C7/18;F01D11/08;F01D25/12 |
主分类号 |
F02C7/18 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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