进气总压对连续旋转爆轰发动机爆轰影响的二维数值模拟  

Two-dimensional numerical simulation of the inlet stagnation pressure influence on the continuous rotating detonation engine

作　　者：李宝星[1] 翁春生[1] LI Bao-xing WENG Chun-sheng(National Key Lab of Transient Physics, Nanjing University of Science and Technology, Nanjing 210094, China)

机构地区：[1]南京理工大学瞬态物理国家重点实验室,南京210094

出　　处：《固体火箭技术》2016年第5期612-618,637,共8页Journal of Solid Rocket Technology

基　　金：国家自然科学基金(11472138);中央高校基本科研业务费专项基金(30920130112007);国防预研基金(9140c300202120c30)

摘　　要：为了研究两相连续旋转爆轰发动机爆轰特性,基于二维守恒元和求解元的方法,对汽油/富氧空气为燃料的发动机爆轰过程进行数值模拟,获得了燃烧室内部流场结构和爆轰波传播特性,对不同进气总压条件下发动机的爆轰性能进行了计算。结果表明,入口处流场随着爆轰波传播呈周期性变化;爆轰波前的预混燃料层是形成稳定连续旋转爆轰的关键,当进气总压过小时,点火后入口处不能形成有效预混燃料层,致使爆轰熄灭;出入口处的压力、温度、密度均受到进气总压的影响;发动机的比冲与进气总压成正比例关系。To study the detonation characteristics of two-phase continuous rotating detonation engine （ CRDE）, based on the method of two-dimensional Conservation Element and Solution Element, the detonation process of gasoline and oxygen-enriched air engine was simulated, the inner flow field of combustion chamber and the propagation characteristic of the detonation wave were ob- tained, and the detonation performance was calculated at different inlet stagnation pressure. The results show that the inlet flow field changes periodically with the propagation of detonation wave, and the premixed fuel layer of the front of detonation was the key to the formation of stable continuous rotating detonation, the effective premixed fuel layer could not be formed at entrance after ignition without enough inlet stagnation pressure ,resulting in the extinguish of detonation.The pressure, temperature, density at the inlet and exit were related to the inlet stagnation pressure, and the engine specific impulse was proportional to the inlet stagnation pressure.

关 键 词：气液两相 连续旋转爆轰发动机 内部流场 预混燃料层 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]