高速热喷流条件下二元收扩喷管扩张段壁面冷却的初步试验研究  

Preliminary Experimental Investigation on the Divergent Wall Cooling of Two Dimensional C-D Nozzles at High Speed and Hot Jet Conditions

作　　者：额日其太[1] 王志杰[1] 吴寿生[1] 

机构地区：[1]北京航空航天大学动力系,北京100083

出　　处：《航空动力学报》2002年第1期40-44,共5页Journal of Aerospace Power

摘　　要：在高速热喷流条件下 ,对二元收扩喷管超音段壁面的冷却进行了初步试验研究。采用的冷却方案共有3种 ,分别是缝隙式、离散孔式和波纹板式气膜冷却方案。得到了各冷却方案喷管的壁面压力分布、壁温分布和红外辐射特性。结果表明 :冷却气流对喷管壁面压力分布影响较大 ,不同冷却结构的壁面压力分布特点不同。通过冷却 ,各喷管的壁温和红外辐射强度明显降低。At high speed and hot exhaust flow conditions,a preliminary experimental investigation on the divergent wall cooling of Two Dimensional C D Nozzle had been conducted.There were three film cooling schemes used,namely,slot,discrete hole and wiggle strip.In the experiment,the infrared radiation and axial distribution of wall temperature and near wall flow pressure were measured with and without film cooling.The results showed:The cooling had significant influence on the near wall flow pressure,and the influence was different with cooling schemes.The infrared radiation and wall temperature were obviously decreased by cooling.There were better benefits through cooling by slot and wiggle strip film cooling.

关 键 词：二元收扩喷管 气膜冷却 红外辐射 扩张段 高速热喷流 试验研究 

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]