横向槽深度对气膜孔冷却性能影响数值研究  

Numerical Simulation of the Influence of the Depth of Transverse Slot on Film Hole Cooling Performance

作　　者：左红[1] 王鹏 武卫[3] 于锦禄[3] 

机构地区：[1]空军驻上海地区军事代表室,上海200233 [2]驻上海胶带股份有限公司军事代表室,上海200233 [3]空军工程大学工程学院,西安710038

出　　处：《机械科学与技术》2008年第9期1252-1255,1260,共5页Mechanical Science and Technology for Aerospace Engineering

基　　金：国家自然科学基金项目(50276070)资助

摘　　要：应用数值模拟的方法,研究了带横向槽的气膜孔冷却结构的槽深度变化对其平均冷却效率的影响规律。在吹风比分别为0.5,1.0,1.5和2.0的条件下,对深度分别为0.5D,0.75D,1.0D和不开槽的4种气膜冷却结构进行了数值模拟,得出了气膜孔出口开槽深度变化对平均冷却效率的影响规律。同时给出了吹风比为1.0时,气膜孔中心线温度场二维轮廓示意图及近壁面的冷却效果示意图,并分析了槽深度对平均冷却效率的影响机理。This paper investigated the influence of different slot depths on the average cooling effectiveness of a cooling structure with transverse slot by numerical simulation. Four cases with slot depth of 0. 5 D ,0. 75 D, 1.0 D and standard cylindrical hole were studied under the condition of blowing ratio 0. 5, 1. 0, 1.5, and 2. 0. The influence law of slot depths on the average cooling effectiveness is determined. We also give out the picture of film hole centedine 2D temperature contours and the cooling effectiveness picture of near surface. Finally, the slot depth cooling mechanism was analyzed.

关 键 词：气膜冷却 吹风比 横向槽 数值模拟 

分 类 号：V211.4[航空宇航科学与技术—航空宇航推进理论与工程]