不同倾斜角多斜孔壁冷却方式绝热温比研究  

INVESTIGATION OF ADIABATIC WALL EFFECTIVENESS OF THE INCLINED MULTIHOLE WALL FILM COOLING WITH DIFFERENT ANGLES TO THE WALL SURFACE

作　　者：林宇震[1] 宋波[1] 李彬 刘高恩[1] 

机构地区：[1]北京航天航空大学热动力工程研究所

出　　处：《航空学报》1999年第3期201-204,共4页Acta Aeronautica et Astronautica Sinica

摘　　要：对具有不同倾斜角多斜孔壁冷却方式绝热温比进行了研究。研究方法为传热传质类比实验方法。多斜孔壁由多斜孔试验板模拟。多斜孔试验板中小孔方向与主流夹角为０°，小孔与板表面夹角分别为３０°，４５°及１５０°。各多斜孔板的孔排距比与孔间距比保持一致。实验结果反映了不同孔倾斜角对多斜孔壁冷却方式气膜绝热温比的影响。并讨论了在航空发动机中采用多斜孔壁冷却方式时选择孔倾角的考虑。An investigation of adiabatic wall effectiveness of the inclined multihole wall with different angles to the wall surface was conducted using the experimental method of heat mass transfer analogy.The inclined multihole walls are simulated by the inclined multihole testing plate.The inclined holes of all plates are angled 0° to the mainstream and 30°,45° and 150° to the surface respectively. The ratio of hole spacing to the hole diameter and the ratio of row spacing to the hole diameter are equal in all testing plates. The experimental results revealed the influence of different angles to the wall surface on the adiabatic wall film effectiveness of the inclined multihole wall. And the considerations of the selection of the hole angle to the surface are discussed when the inclined multihole wall cooling is utilized in the combustion chamber of the aeroengine.

关 键 词：航空发动机 燃烧室 冷却 多斜孔壁 绝热温比 

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] V235.113