固体火箭技术2016，Vol.39Issue(5)：612-618,637,8.DOI:10.7673/j.issn.1006-2793.2016.05.003
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
摘要
Abstract
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Key words
gas-liquid two-phase/continuous rotating detonation engine/inner flow field/premixed fuel layer分类
航空航天引用本文复制引用
李宝星,翁春生..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[J].固体火箭技术,2016,39(5):612-618,637,8.基金项目
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）。 （）
