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.
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)
