发明名称 COOLING PASSAGE CONFIGURATION FOR TURBINE ENGINE AIRFOILS
摘要 An airfoil (10) includes at least one cooling passage (20) for delivering cooling fluid (CF) from a chamber (15) defined within the airfoil (10) to an outer surface (16) of the airfoil (10). The cooling passage(s) (20) includes an entrance portion (22) at an inner surface (14) of the airfoil (10) and a diffusion portion (28) that includes a plurality of diverging locations (50, 52, 54, 60, 62, 64) where walls (32, 34, 36, 38) defining the diffusion portion (28) diverge from one another. The cooling fluid passage(s) (20) promotes a flow of cooling fluid (CF) out of an outlet (30) to provide film cooling for the outer surface (16) of the airfoil (10).
申请公布号 WO2016068860(A1) 申请公布日期 2016.05.06
申请号 WO2014US62513 申请日期 2014.10.28
申请人 SIEMENS AKTIENGESELLSCHAFT 发明人 LIANG, GEORGE
分类号 F01D5/18 主分类号 F01D5/18
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