超燃冲压发动机带凹槽的燃烧室流场振荡研究  

A Study on Flow Oscillation in Scramjet Combustor with Cavity

作　　者：王西耀[1,2] 杨顺华[1,2] 乐嘉陵[1,2] 

机构地区：[1]中国空气动力研究与发展中心高超声速冲压发动机技术重点实验室,四川绵阳621000 [2]中国空气动力研究与发展中心吸气式高超声速技术研究中心,四川绵阳621000

出　　处：《推进技术》2013年第5期651-657,共7页Journal of Propulsion Technology

摘　　要：为了分析闭式凹槽的流场振荡现象,结合试验和二维非定常数值模拟方法,开展了三种条件下的非定常研究。通过实验发现,长深比较大的凹槽作为超燃冲压发动机火焰稳定装置时,凹槽的冷流流场存在强烈的振荡现象。结合二维非定常数值模拟方法,初步分析了振荡机理:振荡的主要原因是燃烧室入口气流马赫数的大小,马赫数2.0条件下,流场周期振荡;马赫数3.0条件下,流场可以稳定存在。根据分析结果给出了流场特征与马赫数的定性依赖关系。通过增加隔离段长度的方法对分析结果进行了验证。To analyze the flow oscillation of closed cavity in scramjet combustor with cavity,three unsteady fields were studied by experiment and unsteady CFD method.It is discovered from experiment that intensive oscillation exists in cold field of scramjet if cavity with large L/D ratio is used as a flame holder.The mechanism of oscillation was analyzed with 2D unsteady CFD method.The entrance Mach number of scramjet combustor is the key parameter that dominates the oscillation.For Mach number 2.0 the field is oscillatory.While for Mach 3.0,the field is stabilized.From the analysis the qualitative variation of field with Mach number was given.Finally,the analysis results with longer isolator were verified.

关 键 词：超燃发动机 凹槽 流场振荡 非定常计算 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]