不同偏角多斜孔壁气膜冷却绝热温比研究  

INVESTIGATION OF ADIABATIC WALL FILM EFFECTIVENESS OF INCLINED MULTIHOLE WALL FILM COOLING WITH DIFFERENT DEELECTED ANGLE

作　　者：林宇震[1] 宋波[1] 李彬 刘高恩[1] 

机构地区：[1]北京航空航天大学热动力研究所

出　　处：《推进技术》1998年第5期43-46,共4页Journal of Propulsion Technology

摘　　要：用传热传质类比实验的方法，研究了不同偏角多斜孔壁气膜冷却绝热温比，多斜孔壁由多斜孔实验板模拟。多斜孔实验板中，孔排列方式均为叉排，小孔与板表面夹角均为３０°，偏角从０°变化至５０°，孔排距比与孔间距比基本相等。研究结果揭示了不同孔偏角对多斜孔壁气膜冷却绝热温比的影响。An investigation of the adiabatic wall film effectiveness of the inclined multihole wall with different deflected angle was performed using the experimental method of heat mass transfer analogy.The inclined multihole walls were simulated by the inclined multihole test plates.The holes of all the test plate are arranged into staggered pattern and angled 30° to the surface,with the deflected angle of the holes varying from 0° to 50°.The pitch to diameter ratios of the holes are nearly equal to the row spacing to diameter ratios of the holes of all test plates.The experimental results reveal the influence of different deflected angles on the adiabatic wall film effectiveness of the inclined multihole wall

关 键 词：燃气涡轮发动机 多孔壁 薄膜冷却 绝热温比 

分 类 号：V235.113[航空宇航科学与技术—航空宇航推进理论与工程] V231.1