发明名称 |
Turbomachinery blade having a platform relief hole, platform cooling holes, and trailing edge cutback |
摘要 |
A method is disclosed that includes providing a turbomachinery blade having an airfoil connected to a platform in a root region of the turbomachinery blade. The airfoil has a trailing edge extending from the root region to a tip distal from the root region. The method further includes forming a blind relief hole in the platform proximate the trailing edge of the airfoil, and forming a plurality of cooling holes in the platform.
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申请公布号 |
US8579590(B2) |
申请公布日期 |
2013.11.12 |
申请号 |
US20100763422 |
申请日期 |
2010.04.20 |
申请人 |
NADVIT GREGORY M.;WILLIAMS ANDREW D.;TESSARINI LEONE J.;ARNAL MICHEL P.;WOOD GROUP HEAVY INDUSTRIAL TURBINES AG |
发明人 |
NADVIT GREGORY M.;WILLIAMS ANDREW D.;TESSARINI LEONE J.;ARNAL MICHEL P. |
分类号 |
F01D5/08 |
主分类号 |
F01D5/08 |
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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