脉冲爆震火箭发动机同轴喷注器实验研究

Experimental Investigation on Coaxial Injector of Pulse Detonation Rocket Engines

为了使液态燃料在脉冲爆震火箭发动机爆震室内形成雾化均匀的小液滴,并且与气态氧化剂掺混后形成空间分布均匀的混合气,设计了适用于脉冲爆震火箭发动机的气液同轴剪切式喷注器。实验研究了三种喷注器结构对脉冲爆震发动机工作过程的影响,结果表明,采用同轴剪切式喷注器的脉冲爆震发动机在20Hz能够产生稳定、连续和充分发展的爆震波。实验中发现,在同时满足雾化良好以及爆震室填充均匀的条件下,喷注器的出气口存在一个最佳面积,实验研究中喷注器出气口的最佳直径在12mm左右。

A new type of coaxial shearing injector used in the pulse detonation rocket engines was designed to obtain uniform atomized droplets and evenly distributed mixture after mixing with gaseous oxidizer in the detonation chamber. The effects of three types of injectors on the operating process of the pulse detonation rocket engines( PDREs) were experimentally investigated. The experimental results show that,fullydeveloped detonation wave is achieved in PDRE with coaxial shearing injectors at 20Hz. It is discovered that there is an optimal area of gas orifice of injector on condition that atomization is good and detonation chamber fills uniformly. The optimal gas orifice diameter is about 12 mm in the experimental study.