多斜孔壁气膜冷却绝热温比传热传质类比实验研究  

AN EXPERIMENTAL INVESTIGATION OF ADIABATICEFFECTIVENESS OF INCLINED MULTIHOLE WALL FULL-COVERAGE FILM COOLINGWITH HEAT-MASS TRANSFER ANALOGY METHOD

作　　者：方韧[1] 李彬[1] 林宇震[1] 刘高恩[1] 

机构地区：[1]北京航空航天大学

出　　处：《航空动力学报》1998年第1期65-68,共4页Journal of Aerospace Power

摘　　要：采用传热传质类比的方法，对多斜孔壁气膜冷却的绝热温比进行了实验研究。多斜孔为规则的叉排形式，小孔与平板表面在主流方向上夹角α均为３０°。在吹风比为１．０～４．０的范围内，研究了具有不同展向间距比ｐ／ｄ，流向排距比ｓ／ｄ的实验板绝热温比分布；对实验数据进行分析比较，得出了孔距与排距的最佳比值，以及吹风比对绝热温比的影响。Using the method of heat-mass transfer analogy,experimental research was carried on to investigate adiabatic film effectiveness of inclined multi-hole full-coverage film cooling.The hole configurations were regular patterns of staggered discrete circular holes,and holes inclined at an angle of 30 deg to the surface of experimental plate. Spanwise hole-to-hole spacing range is from 60 mm to 90 mm,streamwise row-to-row spacing from 45 mm to 18 mm,and hole diameter from 1.0 to 20 mm.Within the range of blowing ratio from 1.0 to 4.0,the experimental results of the adiabatic film effectiveness distribution for five plates were compared and analyzed.Finally,the optimum number of hole spacing and row spacing as well as the influences ofblowing ratio on the adiabatic film effectiveness were obtained.

关 键 词：冷却 多孔壁 航空发动机 传热传质 气膜冷却 

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]