某型冲压燃烧室火焰稳定器布局数值优化研究  

Numerical optimization study on flame-holder layout for a ramjet combustor

作　　者：丁兆波[1] 栾叶君[1] 孙纪国 

机构地区：[1]北京航天动力研究所,北京100076

出　　处：《火箭推进》2009年第6期9-13,共5页Journal of Rocket Propulsion

摘　　要：为了研究不同火焰稳定器布局对燃烧室流场特征和燃烧性能的影响,对某型亚燃冲压发动机燃烧室的三维湍流燃烧流场进行了数值模拟。文中采用守恒标量的PDF模型处理扩散燃烧问题,喷雾采用离散相模型,在全流场中用拉格朗日方法跟踪离散液滴的运动和输运。计算结果表明,内外圈稳定器轴向间距取1倍槽宽时出口温度分布最均匀,取2倍槽宽时温升效率最高;等槽负荷原则设计具有最优的出口温度均匀性、温升效率和流阻系数。计算结果定性合理,可用于预估不同条件下的燃烧室性能,用于燃烧室优化设计,指导燃烧试验。In order to study the influence of the flameholder layout on the outlet temperature distribution, combustion efficiency and total pressure loss, the numerical simulation of combustion flow field for a ramjet combustor was completed. The PDF combustion model is used to deal with the turbulent combustion. Results of numerical simulation show that the axial relative distance of flameholder has obvious effect on combustor performance. The equivalent wide design has the best performance. The results of computation are qualitatively reasonable. It was aimed at predicting the performance characteristics of ramjet combustor through numerical simulation, and giving guidance to modification design of combustor or combustion experiments.

关 键 词：冲压燃烧室 火焰稳定器 燃烧流场 数值模拟 

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]