致密孔阵气膜冷却绝热温比和对流换热系数的数值研究  

Numerical study on adiabatic wall cooling effectiveness and convective heat transfer coefficient of effusion cooling

作　　者：谢浩[1,2] 张靖周[2] 

机构地区：[1]南京师范大学动力工程学院,南京210042 [2]南京航空航天大学能源与动力学院,南京210016

出　　处：《航空动力学报》2009年第6期1229-1235,共7页Journal of Aerospace Power

基　　金：航空科学基金(03C52019)

摘　　要：采用数值模拟方法研究了气膜孔叉排方式下孔间距和吹风比对致密孔阵气膜冷却绝热温比和对流换热系数的影响.结果表明:减小相邻孔间距与孔径比或增加吹风比,平均壁面温度就越低,且温度分布更为均匀,绝热温比提高,热侧壁面平均换热系数也随之增大;相对于增加气膜孔阵的密集程度而言,吹风比的增加所带来的绝热温比改善和对流换热系数增加幅度略有减弱.特别是当吹风比大于1以后,吹风比的影响程度比较微弱.The influences of the adjacent holes spacing and blowing ratio on the adiabatic wall cooling effectiveness and convective heat transfer coefficient of effusion cooling with the film holes in staggered arrangement were numerically investigated. The results show that, with the decrease of adjacent holes spacing or the increase of blowing ratio, the average temperature in the film holes region reduces and the temperature distribution uniformity is improved for all the calculated cases, so that the adiabatic wall cooling effectiveness increases along with the convective heat transfer coefficient. In relation to the decrease of adiabatic holes spacing, the influence of blowing ratio increase is not obvious, especially when the blowing ratio is greater than 1, the influence becomes very weaker.

关 键 词：气膜冷却 绝热温比 对流换热 数值模拟 

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]