凹槽火焰稳定器结构对煤油超声速燃烧的影响  

Effect of the geometry configuration of cavity flame holder on kerosene combustion in supersonic air stream

作　　者：刘欧子[1] 蔡元虎[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]航天科工集团公司31所,北京100074

出　　处：《推进技术》2005年第4期354-359,共6页Journal of Propulsion Technology

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

摘　　要：采用混合分数平衡化学反应模型和离散液滴模型,研究了不同长深比和后缘倾角的凹槽在液体煤油双模态燃烧中的火焰稳定特性。结果表明,集燃料喷射、混合及火焰稳定为一体的凹槽,在所模拟的工作过程中增强了燃料与空气的混合和燃烧;并得到最优的凹槽结构;混合分数平衡化学反应模型和离散液滴模型能准确地预测煤油在双模态燃烧室内的喷雾燃烧。The flame holding characteristic of the cavities with different length to depth ratio and aft ramp angle was numerically investigated in kerosene dual-mode supersonic combustion with the mixture-fraction equilibrium chemistry model at same time combined the discrete droplet model. The cavities integrated fuel injector, mixer and flame holder can improve mixing and combustion of the liquid kerosene and air. The cavity with the ratio of length to depth 5 and the aft ramp angle 30° is regarded as the optimum flame holder because it can hold the flame, enhance the combustion and the total pressure loss is least. The mixture-fraction equilibrium chemistry model and discrete droplet model can predict correctly kerosene spray supersonic combustion.

关 键 词：航空发动机 燃烧室 超音速燃烧 双模态 火焰稳定性 超声速燃烧 火焰稳定器 槽结构 煤油 凹槽 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程] TS733.8[轻工技术与工程—制浆造纸工程]