入口气流参数对固体燃料超燃冲压发动机燃烧室性能的影响分析  

The Effect of Entrance Airflow Parameters on Solid Fuel Scramjet Combustor Performance

作　　者：王利和 武志文[1] 刘昶秀 陶欢[1] 魏志军[1] 王宁飞[1] 

机构地区：[1]北京理工大学宇航学院,北京100081

出　　处：《兵工学报》2014年第5期691-696,共6页Acta Armamentarii

基　　金：国家自然科学基金项目(51276020)

摘　　要：为了研究固体燃料超燃冲压发动机燃烧室入口气流参数对发动机性能的影响,将固体燃料燃面退移速率模型耦合到准一维流动方程中,提出了一种燃烧室的准一维设计和性能分析方法。利用该方法,在飞行条件一定的前提下,改变燃烧室入口气流参数总压、总温、马赫数,得出了各工况下的燃烧室初始型面尺寸并分析了其性能。研究结果表明:在设计飞行条件下,提高燃烧室入口气流的总压和总温均能提高燃烧室的性能,但总温对燃烧室性能的影响更大;燃烧室入口较低的马赫数可以减小燃烧室的加热损失,提高燃烧室的性能;在入口气流质量流量和台阶面积比一定的条件下,提高总温和总压、减小马赫数,能提高燃面推移速率,减小燃烧室的长度。In order to study the effect of entrance airflow parameters on the performance of combustor, a solid fuel regression rate model is coupled to the quasi-one-dimensional flow equations, and a quasi-onedimensional method of combustor design and analysis is proposed. The method is used to keep the parameters of flight environment invariable and change the the total pressure, total temperature and mach number at the entrance of combustor. The sizes and performance of combustor under different flow conditions are calculated by using the quasi-one dimensional design and analysis method. The result shows that the total pressure and total temperature of entrance airflow can be increased to improve the performance of combustor under the design flight condition, but the influence of the total temperature on its performance is more greater. Lower mach number can be used to reduce the heating loss and improve the performance of combustor. If the air mass flow rate and the step area ratio are constant, the total temperature and total pressure are increased and the Mach number is reduced to improve the fuel regression rate and reduce the combustion chamber length.

关 键 词：兵器科学与技术 超燃冲压发动机 固体燃料 燃烧室 入口气流参数 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]