涡轮静叶前缘气膜冷却数值模拟  

Numerical Simulation of Leading Edge Film-Cooling of Turbine Stator Blades

作　　者：杨凡[1] 曹辉[2] 郑洪涛 李智明 

机构地区：[1]哈尔滨工程大学动力与核能工程学院,哈尔滨150001 [2]海军驻上海江南造船(集团)有限责任公司军事代表室,上海200011

出　　处：《汽轮机技术》2006年第4期269-271,320,共4页Turbine Technology

摘　　要：对某新型燃机带6排前缘气膜冷却的第1级静叶叶栅进行了全三维N-S方程数值模拟,描述了叶片前缘绝热效率的分布和冷却射流的流动特征。结果表明,前缘的冷却射流运动相当复杂,各排气膜孔沿径向绝热效率的分布有较大的差异。前缘叶背侧的冷却效果明显好于叶盆侧。冷却空气的流动特征和冷却孔开设的位置直接影响到冷却效果的分布。The leading-edge film-cooling flow field in a turbine with six rows of coolant holes is numerically simulated based on the three-dimensional N - S equation solver. The characteristics of film-cooling of the coolant are displayed as well as the formation of film-cooling adiabatic effectiveness. The result shows that the transportation of rows of coolants is complicated. There is much difficult for the formation of film-cooling adiabatic effectiveness distributes in radial. The leading edge film- cooling effectiveness on the side of blade suction surface is better than pressure surface. The film-cooling adiabatic effectiveness＇ s distributing is directly affected by the characteristics of the coolant trajectory and the location of wholes.

关 键 词：气膜冷却 数值模拟 涡轮静叶 绝热效率 

分 类 号：TK473.91[动力工程及工程热物理—动力机械及工程]