基于预爆轰点火方式的连续旋转爆轰发动机起爆过程分析

为深入了解预爆轰式连续旋转爆轰发动机点火起爆机理,基于连续旋转爆轰发动机试验平台进行了一系列预爆轰管点火试验和连续旋转爆轰发动机点火起爆试验研究,基于OpenFOAM开展了预爆轰管内初始爆轰波进入发动机环形燃烧室传播过程的数值模拟研究.结果表明:试验研究中,初始爆轰波进入环形燃烧室后波峰压力值迅速降低,爆轰波膨胀解耦并...

Analysis of Initiation Process of Continuous Rotating Detonation Engine Based on Pre-detonation Ignition

In order to deeply study the initiation process and detonating mechanism of the continuous rotating detonation engine(CRDE)based on pre-detonation ignition,a series of pre-detonation tube ignition tests and CRDE ignition tests were carried out based on the CRDE test platform.The numerical simulation of initial detonation wave propagating into the annular combustor was carried out based on OpenFOAM.The results show that the peak pressure decreases rapidly after the initial detonation wave enters the annular combustor,and the detonation wave decouples and decays into combustion wave.When the initial detonation wave enters the annular combustor,the rotating detonation wave does not form directly until a process of"initial detonation wave decoupling-deflagration to detonation transition(DDT)-triggering rotating detonation wave".When the total mass flow rate is about 380 g/s,the DDT time decreases rapidly from more than 20 ms to less than 2 ms as the equivalence ratio increases from 0.65 to 0.95.When the total mass flow rate drops to about 280 g/s,the rotating detonation wave propagates unsteadily.After entering the annular combustor,the initial detonation wave attenuates gradually and forms the first shock wave,and then after reflection at the inlet surface,a reflected shock wave forms and propagates with the first shock wave.The first shock wave is reflected at the inlet end of the combustor to form a reflected shock wave,and the reflected shock wave finally decays to disappear at about 90°circumferential direction.