不同排列方式多斜孔壁气膜冷却绝热温比研究  

AN INVESTIGATION ON FILM COOLING EFFECTIVENESS OF INCLINED-MUTIHOLE WALLS WITH DIFFERENT PATTERNS

作　　者：宋波[1] 林宇震[1] 刘高恩[1] 王华芳[1] 

机构地区：[1]北京航空航天大学

出　　处：《航空动力学报》1999年第1期91-94,共4页Journal of Aerospace Power

摘　　要：采用传热传质类比方法实验研究了４种孔阵排列方式（顺排、叉排、顺排＋复合角及叉排＋复合角）下多斜孔壁气膜冷却绝热温比。小孔与壁面夹角为３０°，复合角为４５°，孔阵排距比８．０，侧向间距比４．０，吹风比为１．９４。比较了各排列方式孔阵绝热温比的分布规律，得出了较优的孔阵排列方式。An experimental investigation on the film cooling effectiveness of the inclined-multihole walls with different patterns(In-line,Staggered,In-line+compound angle,Staggered+compound angle) was conducted by using the method of heat-mass transfer analogy.The holes were inclined with 30° to the wall surfaces and the compound angle was 45° to the mainstream.The multihole patterns were arranged with streamwise row-to-row spacings of eight hole diameters and spanwise hole pitch-to-diameter ratio of four.The superior mutihole pattern was found out from the experiments.

关 键 词：气膜冷却 绝热壁温 多斜孔壁 航空发动机 

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]