带凹腔的超声速燃烧室燃烧流场数值模拟  

Numerical Simulation of Combustion Flow Field of Supersonic Combustor with Cavity

作　　者：杨事民[1] 唐豪[1] 黄玥[1] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《航空发动机》2008年第3期35-38,共4页Aeroengine

基　　金：国家863基金资助(2004AA723020)

摘　　要：对带凹腔结构的燃烧室二维甲烷燃烧流场进行了数值模拟。采用迎风3阶精度MUSCL格式求解二维含组分守恒N-S方程,湍流模型采用剪切修正的RNG k-e湍流模型,分别分析了凹腔不同的长深比和导流槽结构对燃料燃烧的影响;对喷甲烷燃烧工况进行了计算研究。结果表明:凹腔可以提高燃烧效率,却使总压恢复系数降低;凹腔的长深比越高,燃烧效率越高,总压恢复系数越低;在总压恢复系数较高的情况下,采用导流槽可进一步提高燃烧效率。The numerical simulation of two - dimensional combustion flow field for the methane combustor with cavity was performed. Two - dimensional element - conservation N - S equation was solved by using three order up - wind ac- curacy MUSCL form. The turbulent model used RNG k - e turbulent model of shear correction, the effect of different length to depth ratios and different slot structures on the fuel combustion were analyzed. The operating condition of com- bustion was calculated. The conclusions are as follows ： the combustion efficiency was enhanced with the cavity, but the total pressure recovery factor was reduced; the bigger length to depth ratio is, the higher the combustion efficiency and the lower the total pressure recovery factor; the combustion efficiency is improved withslot at high total pressure recovery factor.

关 键 词：超燃冲压发动机 燃烧室 数值模拟 凹腔结构 导流型凹槽 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程] TV131.4[水利工程—水力学及河流动力学]