超声速气流中喷射角度对射流混合特性的影响研究  

Numerical Study of Injection Angle Effect on Fuel Mixing Characteristics in Supersonic Flow

作　　者：肖隐利[1] 宋文艳[1] 赵志[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《世界科技研究与发展》2008年第4期436-439,共4页World Sci-Tech R&D

基　　金：西北工业大学博士论文创新基金资助项目(W016107)

摘　　要：本文采用AUSMPW格式,求解全NS方程加SST双方程湍流模型,研究了超音速气流中横向喷射的流场。数值模拟给出了流场中由于射流喷射引起的附面层分离、马赫盘等现象,计算结果的壁面压力分布和试验结果吻合较好。在此基础上重点分析了喷射压力和喷射角度对燃料混合特性的影响。In this paper,the two dimensional flow field of transverse sonic injection into supersonic flow is investigated. The present numerical results predict the prominent feature including the boundary layer separation and Mach disk that forms as a result of the coalescing of com- pression waves. To make the comparisons ,wall pressures for a range of injection pressure ratios are compared with experimental results. Furthermore,the injection pressure and angle effect on fuel mixing characteristics is studied.

关 键 词：超音速燃烧室 燃料喷射 喷射角度 数值模拟 

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]