向心涡轮喷嘴出口气流角的数值研究  

Numerical Study on Nozzle Exit Flow Angle for Radial Turbine

作　　者：刘莹[1] 马国玲 葛炜[1] 佟鼎[1] 王晓春[1] 杨磊[1] 黄磊[1] 白军爱[1] 蒋婧[3] 

机构地区：[1]中国北方发动机研究所(天津) [2]大同北方天力增压技术有限公司 [3]中国人民解放军96627部队

出　　处：《车用发动机》2014年第4期7-11,共5页Vehicle Engine

基　　金：国防重点实验室基金资助项目(9140C330104120C33119);国防基础科研计划资助(B0920110003)

摘　　要：针对一种普通增压器涡轮,采用数值模拟的方法对喷嘴出口气流角的分布进行了研究,掌握了此涡轮的效率和流量特性,通过与试验结果比较获得了可信的计算模型,掌握了膨胀比、转速以及喷嘴位置对喷嘴出口气流角分布的影响,为涡轮箱的设计提供了技术依据。For a turbine of a turbocharger ,the distribution of nozzle exit flow angle was analyzed by utilizing the numerical simulation ,the efficiency and flow characteristics of turbine were grasped and the credible calculated model was acquired by comparing with the experiment results .The influences of expansion ratio ,rotation speed and nozzle position on nozzle exit flow angle distribution were determined ,which provided the technical reference for turbine housing design .

关 键 词：涡轮 喷嘴出口气流角 数值模拟 

分 类 号：TK423.5[动力工程及工程热物理—动力机械及工程]