用不同化学反应模型对煤油超声速燃烧的数值分析  

Numerical analysis of supersonic combustion with kerosene using two different chemical reaction models

作　　者：蔡元虎[1] 刘欧子[1] 胡欲立[1] 刘敬华[2] 凌文辉[2] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072 [2]北京动力机械研究所,北京100074

出　　处：《航空动力学报》2006年第4期642-646,共5页Journal of Aerospace Power

基　　金：国家自然科学基金资助(50086002);西北工业大学博士论文创新基金资助(200219)

摘　　要：采用单步不可逆有限速率化学反应模型,同时结合离散液滴模型、概率密度函数紊流燃烧模型的混合分数平衡化学反应模型,对煤油在双模态燃烧室内的燃烧进行了数值分析。通过比较数值计算结果与实验结果,说明计算所采用的模型是有效的。在给定的计算条件下,与单步不可逆有限速率化学反应模型相比,结合了离散液滴模型的混合分数化学反应模型更能准确地预测煤油在双模态燃烧室内的喷雾燃烧,并且集燃料喷射、混合及火焰稳定为一体的凹槽火焰稳定器增强了燃料的混合和燃烧,使燃烧效率在燃烧室出口达0.880 6。Numerical analysis of supersonic combustion with kerosene was carried out using two chemical reaction models. One is the one-step irreversible finite rate chemical reaction, and the other is the mixture-fraction equilibrium chemical reaction model combined with the discrete droplet model and probability density function at the same time to describe the interaction of turbulence and combustion. Compared the numerical results with the experimental data validated the models used in the numerical simulation. In the assumed computation conditions, compared with the irreversible finite rate chemical reaction model, the mixture-fraction equilibrium chemical reaction model combined with other models can predict exactly kerosene spray combustion in the dual-mode supersonic combustor. The integrated cavity flame holder, fuel injector, mixer and flame holder together can improve mixing and combustion of the liquid kerosene and air mixture. The combustion efficiency is 0. 880 6 measured at the combustor exit.

关 键 词：航空 航天推进系统 化学反应模型 双模态 亚声速燃烧 超声速燃烧 数值分析 

分 类 号：V312.1[航空宇航科学与技术—航空宇航推进理论与工程]