比较研究多种气膜冷却模型的冷却效果  

Study on Cooling Effectiveness of Various Film Coolings

作　　者：张小英[1] 王先炜[1] 

机构地区：[1]北京航空航天大学动力系,北京100083

出　　处：《航空动力学报》2002年第4期475-479,共5页Journal of Aerospace Power

摘　　要：计算并比较了高性能航空燃气发动机尾喷管扩张调节片采用以下几种气膜冷却结构的冷却效果 :缝槽气膜冷却、离散小孔气膜冷却、缝槽 /小孔复合气膜冷却 ,发展了用单排孔和缝槽气膜的有效温比计算多排孔和缝槽 /小孔复合气膜有效温比的公式 ,计算了考虑喷管内高温燃气辐射和气膜冷却作用下喷管壁面的温度分布 ,为高性能航空燃气发动机高温部件冷却结构的选型提供了有益的参考。The cooling effectiveness of following film cooling types for expansion regulating parts of high performance aeroengine nozzle has been calculated and compared:slot film cooling,full coverage film cooling,and compound slot and full coverage film cooling.The method to calculate the film cooling effectiveness for multi-row of holes and for compound slot and full coverage is developed on the basis of film cooling effectiveness for single row of holes film and for slot.The temperature distribution when taking into account the effect of high temperature gas radiation and film cooling is calculated,the result provides beneficial references to selecting film cooling type for nozzle of high performance aeroengine nozzle.

关 键 词：比较研究 气膜冷却模型 冷却效果 绝热温比 航空发动机 

分 类 号：V233.5[航空宇航科学与技术—航空宇航推进理论与工程]