多通道涡轮级的流场/温度场非定常数值模拟  

Multipassage Unsteady Simulation of Flow and Temperature Fields in a Turbine Stage

作　　者：董素艳[1] 刘松龄[1] 朱惠人[1] 

机构地区：[1]西北工业大学航空动力与热力工程系,陕西西安710072

出　　处：《航空动力学报》2002年第1期29-34,共6页Journal of Aerospace Power

摘　　要：通过求解二维 N-S方程对多通道涡轮级进口有温度畸变时的流场和温度场进行了非定常数值模拟。相对于简化成单通道涡轮级的数值模拟得到更精确的结果 ,尤其是对温度场的模拟。改变热斑数与导叶通道数比会对动叶时均温度分布产生较大影响 ,动叶压力面温度分布所受的影响更大。A two dimensional Navier Stokes equation was solved to predict the unsteady,multipassage flow and temperature fields with hot streak in turbine inlet.Comparing with the results of single passage's simulation,the present multipassage simulation leads to more precise results,especially for temperature fields.Time averaged temperature distributions on rotor surface will greatly change with the hot streak/airfoil ratio,and the temperature distribution changes more on the pressure surface than that on the suction surface of the rotor.

关 键 词：流场 温度场 非定常数值模拟 多通道涡轮级 叶排通道比 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]