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.
出处
《汽轮机技术》
北大核心
2006年第4期269-271,320,共4页
Turbine Technology
关键词
气膜冷却
数值模拟
涡轮静叶
绝热效率
film-cooling
numerical simulation
turbine stator blades
adiabatic effectiveness
