旋转带肋回转通道流动换热数值模拟  

Numerical Predictions of Flow and Heat Transfer for Rotating Internal Cooling Channels with Rib Turbulators

作　　者：赵曙[1] 朱惠人[1] 郭涛[1] 张丽[1] 孙瑞嘉[2] 

机构地区：[1]西北工业大学动力与能源学院,西安710072 [2]中国航空动力机械研究所,湖南株洲412002

出　　处：《西安交通大学学报》2014年第2期125-130,共6页Journal of Xi'an Jiaotong University

基　　金：国家重点基础研究发展计划资助项目(2013CB035702)

摘　　要：为进一步了解涡轮动叶旋转内冷通道的流动换热规律,选取动叶内通道的相似放大模型进行实验和数值模拟研究。通道进口雷诺数为17 000,3个出口的流量分配比为1∶2∶1,旋转半径与水力直径比为46.4,旋转数分别为0和0.09。静止实验测量了沿程静压系数和努赛尔数(Nu)分布,三维数值模拟了旋转通道内部涡结构对流动换热的影响。结果表明:旋转造成通道涡偏移,改变了速度场分布,使哥氏力指向的壁面附近流速增加;旋转离心力使径向出流沿程静压系数逐渐增加,径向入流沿程静压系数迅速降低;肋扰流涡使沿程展向平均Nu呈多波峰状分布;转弯回流涡使得转弯下游通道的Nu不对称分布;旋转促使内通道的流体偏向哥氏力指向的壁面,增加了径向出流压力面和径向入流吸力面的Nu。To investigate flow and heat transfer in a rotating internal channel of the moving blade, experiments and numerical simulations for a similarly amplified channel model with 90°ribs are conducted. The inlet Reynolds number, flow rate distribution ratio and geometric dimensionless ratio are taken as 17 000, 1 ： 2 ： 1 and 46.4 respectively, the rotating number is considered as 0 and 0.09. The heat transfer coefficient distribution and static pressure coefficient are examined by experiments. The effects of vortex on flow and heat transfer in rotating internal cooling passage are achieved with 3-D numerical simulation. The results show that vortex shift in rotating channel changes velocity field, and the static pressure coefficient increases along radial outflow and decreases along radial inflow due to centrifugal force. The laterally averaged Nu distributes in multiple-peak form as the result of secondary flow induced by rib turbulators. The Nu distribution down stream of turning area gets asymmetric due to turning eddy. The fluid shift tends toward the wall that the Coriolis force points to. Consequently, the Nu on the radial outflow pressure surface and radial inflow suction surface increases.

关 键 词：涡轮叶片 带肋通道 旋转 对流传热 数值计算 

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]