某超燃冲压发动机尾喷管的三维流场特性  

Three Dimensional Flow Characteristics of a Scramjet Nozzle

作　　者：王建明 齐晓航 栾思琦 王成军 陈宝岭 WANG Jian-ming;QI Xiao-hang;LUAN Si-qi;WANG Cheng-jun;CHEN Bao-ling(Liaoning Key Lab of Advanced test Technology for Aeropropulsion System, College of Aeroengine, Shenyang Aerospace University, Shenyang 110136, China;Shenyang Aerospace Xinle Co. Ltd., Shenyang 110034, China)

机构地区：[1]沈阳航空航天大学航空发动机学院,辽宁省航空推进系统先进测试技术重点实验室,沈阳110136 [2]沈阳航天新乐有限责任公司,沈阳110034

出　　处：《科学技术与工程》2021年第14期6063-6068,共6页Science Technology and Engineering

摘　　要：超燃冲压发动机结构简单,推重比大,应用前景广阔。但其流场结构十分复杂,研究超燃冲压发动机三维流场结构具有重要的意义。采用计算流体力学软件对某超燃冲压发动机尾喷管的三维流场进行数值模拟,先后得到了流场的密度、马赫数、涡量及速度矢量线图。结果表明:喷管内及侧壁面出口处存在膨胀波。各个壁面出口处附近的流场存在羽流激波和剪切层,内喷管出口周围的羽流激波和剪切层呈环状分布在流场周围,上壁面尾部受羽流激波的影响产生一道由压强决定的管内斜激波。内喷管出口及上壁面尾部处也均存在流向涡结构。Scramjet has the advantages of simple structure,large thrust to weight ratio and wide application prospect.But its flow field structure is very complex,so it is of great significance to study the three-dimensional flow field structure of scramjet.The three-dimensional flow field of a scramjet nozzle was simulated by computational fluid dynamics software.The density,Mach number,vorticity and velocity vector lines of the flow field were obtained successively.The results show that there are expansion waves in the nozzle and at the exit of the side wall.The results show that there are plume shock wave and shear layer in the flow field near the exit of each wall.The plume shock wave and shear layer around the exit of the inner nozzle distribute in a ring shape around the flow field.The tail of the upper wall is affected by the plume shock wave and produces an oblique shock wave in the tube which is determined by the pressure.There are also streamwise vortices at the exit of the inner nozzle and the tail of the upper wall.

关 键 词：超燃冲压发动机 膨胀波 激波 剪切层 流向涡 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]