发明名称 |
Shroud with aero-effective cooling |
摘要 |
A turbine shroud section includes a cooling passage that bleeds cooling air through an opening in a surface. The cooling passage forms an angle relative to an expected fluid flow direction. The angle defines an angular component in a circumferential direction, which is aligned with the expected fluid flow direction to reduce momentum energy loss of fluid flow through the engine.
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申请公布号 |
US7334985(B2) |
申请公布日期 |
2008.02.26 |
申请号 |
US20050247812 |
申请日期 |
2005.10.11 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
LUTJEN PAUL M.;ROMANOV DMITRIY;DRAKE JEREMY;GROGG GARY;REINHARDT GREGORY E. |
分类号 |
F03B11/00 |
主分类号 |
F03B11/00 |
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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