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.
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 代理人
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