双脉冲固体火箭发动机压强振荡特性研究  

Research on the pressure oscillation characteristics of double pulse solid rocket motor

作　　者：刘伟凯[1] 何国强[1] 王春光[2] 

机构地区：[1]西北工业大学航天学院燃烧热结构与内流场重点实验室,西安710072 [2]中国航天科技集团公司航天动力技术研究院西安航天动力技术研究所,西安710025

出　　处：《航空动力学报》2015年第10期2553-2560,共8页Journal of Aerospace Power

摘　　要：为了研究隔舱消融对双脉冲发动机中燃烧室的压强振荡影响规律,选择隔舱消融几个典型时刻进行研究,运用大涡模拟(LES)方法,对Ⅱ脉冲工作时的发动机流场稳定性进行数值模拟.最后得到了各工况下的压强时间曲线及其快速傅氏变换(FFT)结果.分析表明:由于Ⅱ脉冲工作初期隔舱暴露在流场中产生额外扰动,以及隔舱级间通道形成狭窄通道的加速作用,是导致边界层分离而引起障碍涡脱落的主要因素.点火初期,双脉冲发动机易发生轻微压强振荡.随隔舱消融,整个流场在发动机工作中、后期逐渐趋于平稳.In order to reveal the relationship between the melting of pulse separation de- vice （PSD） and the pressure oscillation, several melting moments were selected for research. Large eddy simulation （LES） was carried out for the numerical simulation of II pulse flow field, and the pressure-time curve and fast Fourier transformation （FFT） results were ob- tained successfully. The analysis results show that the additional disturbance in the flow field generated by opening PSD when the Ⅱ pulse is working, and the acceleration of inter- stage narrow channel, are the main factors to obstacle vortex shedding caused by boundary layer separation. In the early ignition, the double pulse motor （DPM） is prone to slight pressure oscillation. With the PSD melting, the whole flow field becomes more and morestabilized.

关 键 词：双脉冲发动机 隔舱 压强振荡 突收突扩 大涡模拟 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]