利用等离子体气动激励提高气膜冷却效果的数值研究  

Numerical Simulation of Improving Film Cooling Effectiveness by Plasma Aerodynamic Actuation

作　　者：代胜吉[1] 何立明[1] 丁未[2] 金涛[1] 张玉敏[1] 

机构地区：[1]空军工程大学航空航天工程学院,西安710051 [2]空军工程大学训练部,西安710051

出　　处：《科学技术与工程》2013年第18期5234-5239,共6页Science Technology and Engineering

基　　金：国家自然科学基金(51276196)资助

摘　　要：为揭示等离子体气动激励对气膜冷却效果的影响机理,采用数值模拟方法研究了不同吹风比下的冷却气流流场分布、垂直主流截面的局部速度矢量分布和温度分布情况,并与常规气膜冷却结果作对比。结果表明,等离子体气动激励能有效诱导冷却气流偏转,提高气膜贴壁效果,延缓主流和冷却气流的掺混,壁面冷却效果显著增大;在不同吹风比下,沿流动方向等离子体启动激励气膜冷却效率的变化趋势相同;在激励器表面处壁面温度略有增大,但不影响冷却效率的提高。To show the basic mechanism of film cooling effect by plasma aerodynamic actuation,the flow field of cooling air,the distribution of velocity vector and temperature were analyzed by numerical simulation.And these distributions were compared with distributions of baseline holes.The results show that cooling air is deflexed effectively by the plasma aerodynamic actuation.The entrainment of main air and cooling air is delayed,thus film cooling effectiveness is improved significantly.The variation trends of film cooling effectiveness in different M along field direction are the same.Temperature augmentation of the actuator surface doesn’t affect improving cooling effectiveness.

关 键 词：介质阻挡放电 等离子体气动激励 数值仿真 气膜冷却 冷却效率 

分 类 号：V233.93[航空宇航科学与技术—航空宇航推进理论与工程]