喷管超声段壁面冷却热态试验研究  

Hot-air experimental investigation of cooling applicable to exhaust nozzles

作　　者：额日其太[1] 王强[1] 吴寿生[1] 魏福清[1] 

机构地区：[1]北京航空航天大学热动力工程研究所,北京100083

出　　处：《推进技术》2001年第4期322-325,共4页Journal of Propulsion Technology

摘　　要：在高温条件下 ,对三种轴对称收 扩喷管超声段壁面排气引射冷却方案 (缝隙式气膜冷却、离散孔气膜冷却和冲击 气膜组合冷却 )进行了试验研究。得到了不同冷却方案的壁面压力分布、壁面温度分布和红外辐射特性 ,以及冷却气流量对这些性能的影响。结果表明 :采用排气引射冷却技术可以大幅度降低喷管的壁温和红外信号特征 ,其中缝隙式气膜冷却的应用前景最好 ,离散孔式气膜冷却值得深入研究 ,冲击The hot-air experimental results of three cooling methods applicable to axisymmetric convergent-divergent exhaust pumping nozzle with cooling on divergent wall were presented. The three methods include slot film cooling, discrete hole film cooling, and impact-film cooling. To each scheme, the influence of cooling air flow rate on the distributions of wall pressure distribution and wall temperature and infrared radiation characteristics of nozzles were also investigated. The results reveal that the ejector pumping nozzle concept has significant potential to meet the challenges of reducing exhaust system hot-parts temperature and infrared radiation.

关 键 词：轴对称收-扩喷管超声段壁面 冷却试验 喷管排气引射冷却方案 红外辐射 缝隙式气膜冷却方案 离散孔式气膜冷却 冲击-气膜组合 热态试验 军用飞机排气系统 

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] V271.4