分段式固体火箭发动机内部流动不稳定性数值分析  

Numerical Analysis of Flow Instability in Segmented SRM

作　　者：王健儒[1] 何国强[1] 李强[1] 晁侃 

机构地区：[1]西北工业大学航天学院,陕西西安710072 [2]西安航天动力技术研究所,陕西西安710025

出　　处：《推进技术》2013年第1期95-100,共6页Journal of Propulsion Technology

摘　　要：采用大涡模拟技术,针对某分段式固体火箭发动机开展了发动机燃面退移0mm,160mm和280mm三个时刻下发动机燃烧室内部流动不稳定现象的数值分析,获得了三个典型时刻燃烧室内压强可能的振荡特性。计算结果表明,在发动机点火初期燃烧室内流动不稳定性主要由表面涡脱落导致;随着燃面的退移,端面限燃层暴露在燃气中,由于端面包覆结构残余的影响,燃烧室内流动不稳定性主要由障碍涡脱落决定,且与点火初期相比,压强振荡的频率逐步减小。In order to investi cal analyses based on LES（large gate the flow instability in a segmented SRM （solid rocket motor） , numeri- eddy simulation） were carried out for a potential pressure oscillation char- acteristics in the chamber when the burning surface regression was at 0 mm, 160 mm and 280 mm,respec- tively. The numerical results indicate that initial stage flow instability is mostly caused by the parietal vor- tex-shedding in the chamber shortly after the motor firing. As the burning surface regresses continuously, the restrictors expose to the hot gases. The chamber flow instability is mostly induced by the obstacle vortex- shedding generated due to the effects of the residual annular thermal protection. Correspondingly, the fre- quency of pressure oscillation is decreased gradually as compared with that of initial stage.

关 键 词：分段发动机 大涡模拟 流动不稳定 涡脱落 

分 类 号：V435.23[航空宇航科学与技术—航空宇航推进理论与工程]