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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。
In order to make the liquid fuel form atomized small droplets in the detonation chamber of a pulse detonation rocket engine and form a spatially homogeneous mixture with the gaseous oxidant, a gas-liquid-to-liquid Shaft shear injector. The effects of three injector structures on the operation of pulse detonation engine were experimentally studied. The results show that the pulse detonation engine with coaxial shear injector can generate stable, continuous and fully developed detonation wave at 20Hz. It is found in the experiment that there is an optimum area of the air outlet of the injector at the same time that the atomization is well and that the detonation chamber is filled uniformly. In the experimental study, the optimum diameter of the air outlet of the injector is about 12 mm.