摘要
针对超燃燃烧室中的燃料掺混问题,采用基于雷诺平均Navier-Stokes的数值模拟方法分析了考虑来流边界层条件下的燃料横向射流流场特征及其掺混特性.研究发现:对于确定的来流边界层,燃料喷射存在一个临界动压比.当动压比低于该临界动压比时,增大来流边界层能明显提高燃料的穿透深度和掺混效率.而当动压比大于该临界动压比时,来流边界层厚度对燃料的穿透深度和掺混效率几乎没有影响.对于所研究的流动状态,该临界动压比约为0.900.在相同动压比下,所选厚来流边界层条件下的总压恢复系数仅约为薄来流边界层的0.93倍.其中,来流边界层内的摩擦损失是造成超燃燃烧室低总压恢复的主要因素,而改变来流边界层厚度对喷流及下游流场总压损失造成的影响相对较小.
Effects of incoming boundary layer on flow field characteristics and mixing performance of transverse jet in a scramjet combustor were numerically investigated by using Reynolds-averaged Navier-Stokes.Results indicate that there is a critical dynamic pressure ratio for every specific flow status.Only when the injection dynamic pressure ratio is less than that value,increasing incoming boundary layer thickness could effectively improve the jet penetration depth and mixing efficiency.Otherwise,variation of incoming boundary layer rarely affects the jet penetration depth and mixing efficiency.For the cases studied,the critical dynamic pressure ratio was around 0.900.At the same dynamic pressure ratio condition,the thick incoming boundary layer cases were only 0.93 times the total pressure recovery coefficient of the thin cases.The friction loss of imcoming boundary layer is the dominant factor affecting the total pressure recovery of the scramjet combustor,and variation of incoming boundary layer thickness makes little influence on total pressure recovery induced by the jet and its downstream flow field features.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2016年第6期1351-1358,共8页
Journal of Aerospace Power
基金
国家自然科学基金(91441128
51276151)
基础科研项目(B1420133058)
航空科学基金(20155768007)
关键词
来流边界层
超燃燃烧室
动压比
掺混效率
穿透深度
总压恢复
incoming boundary layer
scramjet combustor
dynamic pressure ratio
mixing efficiency
penetration depth
total pressure recovery
作者简介
周驯黄（1993-），男，海南乐东人，硕士生，主要从事高超声速推进技术研究．
通讯作者：黄玥（1983-），男，安徽巢湖人，助理教授，博士，主要从事超燃冲压发动机研究．E—mail：huangyue@xmu．edu．cn
