双排簸箕形孔气膜冷却效率及其叠加算法  

Film cooling and superposition method for double row dust-pan shaped holes

作　　者：朱惠人[1] 郭涛[1] 许都纯[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《航空动力学报》2006年第5期814-819,共6页Journal of Aerospace Power

摘　　要：对双排错排簸箕形孔气膜冷却效率进行了实验研究,测出了孔排下游的局部冷却效率的分布。对比研究了单排孔与双排孔气膜冷却效率分布的特点及双排孔气膜冷却效率的叠加算法。结果表明,在单排孔条件下所确定的最佳吹风比,在多排孔喷射时是不适用的。在较高吹风比下,如采用传统的气膜冷却效率的叠加算法,根据单排孔冷却效率计算双排孔冷却效率会产生很大的偏差,其计算结果远低于试验值。给出了双排错排的簸箕形孔的喷射时,冷却效率的叠加计算关系式。Film cooling effectiveness for injection from single row and double row dustpan shaped holes has been studied experimentally. The differences of cooling performance between single row and double row holes were described. Results show that the optimal blowing ratio of injection from double row holes is higher than that of injection from single row holes. In the case of higher blowing ratio, the traditional superposition calculation method under-predicts the film cooling effectiveness of double row injection based on that of single row hole injection. The modified superposition calculation method is given in the present paper.

关 键 词：航空 航天推进系统 簸箕形孔 气膜冷却 叠加算法 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]