气膜冷却涡轮导向叶片流场数值模拟  

Numerical Simulation of Flow Field in a Turbine Stator with Film Cooling

作　　者：曾军[1] 王彬[1] 康勇[1] 

机构地区：[1]中国燃气涡轮研究院,四川成都610500

出　　处：《燃气涡轮试验与研究》2006年第4期16-19,34,共5页Gas Turbine Experiment and Research

摘　　要：本文采用三维定常数值方法计算了某气膜冷却涡轮导向叶片流场。叶片的气膜冷却流动运用了源项模拟方法,将每排气膜孔用槽缝代替。计算的导叶能量损失系数和出口气流角与试验数据吻合良好。In this paper steady three-dimenslonat numerical calculation was performed in order to investigate the effects of film cooling on turbine stator flow fields. A row of cooling holes was modeled as a slot. Using source terms simulated film cooling flow in the stator. The effects of film cooling on the aerodynamic loss in terms of energy loss coefficient and the outlet flow angle were analyzed. The simulation results were agreed well with the experimental results,

关 键 词：CFD 涡轮 静子 气膜冷却 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]