涡轮叶栅前缘气膜冷却数值模拟  

Numerical Simulation of Leading Edge Film-Cooling in a Turbine Cascade

作　　者：颜培刚[1] 王松涛[1] 韩万金[1] 王仲奇[1] 

机构地区：[1]哈尔滨工业大学能源科学与工程学院,黑龙江哈尔滨150001

出　　处：《航空动力学报》2003年第5期623-628,共6页Journal of Aerospace Power

基　　金：国家科技部973资助项目(G1999022307)

摘　　要：采用具有三阶精度TVD性质的有限差分格式及多区网格技术,对某型前缘带有两排冷气孔的涡轮叶栅的气膜冷却流场进行了全三维N-S方程数值求解,分析了在前缘滞止区域附近两排孔的冷气射流各自的运动规律、温度分布以及不同吹风比情况下前缘区域气膜冷却绝热效率的分布特点。结果表明,冷气孔的位置、排列方式以及冷气喷射率的变化对叶片前缘区域的绝热效率分布的影响是非常明显的。A finite difference scheme with threeorder precision and TVD property and a multiblock grid technique are adopted.The leadingedge filmcooling flow field in a turbine with two rows of coolant holes is numerically simulated based on the threedimensional NS equation solver.The characteristics of the flow and temperature fields,including the coolant trajectory,the interaction of two rows of coolant jets and the complicated distribution of filmcooling adiabatic effectiveness in the region of leading edge are all expounded under different blowing ratios,injection angles and locations of coolant holes.The results show that the influences of different positions of coolant holes,their arrangement and the blowing ratios on the adiabatic effectiveness are obvious and complicated in the leading edge.

关 键 词：前缘气膜冷却 绝热效率 数值模拟 燃气涡轮 叶栅 

分 类 号：TK401[动力工程及工程热物理—动力机械及工程]