发明名称 Methods and apparatus for cooling gas turbine rotor blades
摘要 A turbine blade is provided. The turbine blade includes a blade platform having an airfoil portion and a root portion extending therefrom, an undercut formed in a first side of the platform and a purge slot formed in a second side of the platform.
申请公布号 GB0423869(D0) 申请公布日期 2004.12.01
申请号 GB20040023869 申请日期 2004.10.27
申请人 GENERAL ELECTRIC COMPANY 发明人
分类号 F01D5/18;F01D5/14;F01D5/30;F02C7/16 主分类号 F01D5/18
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