摘要
概述了国内外针对大型分段固体火箭发动机中由于声涡耦合而引起的压强振荡现象的实验研究,包括轴向供气和径向供气的冷流实验以及大量的缩比发动机点火试验。一方面,这些实验用来确定和验证定义涡脱落频率的Strouhal数值,其可在一定程度上解释全尺寸发动机振荡出现的时刻和频率的变化;另一方面,研究了绝热环的高度、厚度、材料、位置以及绝热环间距等参数对振荡幅值的影响,为被动控制提供思路。同时发现,头部、段间和潜入式喷管处空腔对压强振荡也有很大影响。
Experimental researches on pressure oscillations in large segmented solid rocket motors due to vortex-acoustic coupling phenomenon were overviewed,including cold flow setups with air injected axially and radially,as well as lots of subscale motors hot fires.One side,the values of Strouhal number used to define the vortex shedding frequency were determined and verified,which can explain the time when instabilities occur and the paths of frequencies in a full-size motor.On the other side,effects of the height,thickness,material,locations of inhibitors on amplitudes of oscillations were investigated,which provides some ideas for passive control.Besides,head cavity,intersegment cavity and cavity at submerged nozzle also have a great impact on amplitudes of oscillations.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2012年第6期726-731,共6页
Journal of Solid Rocket Technology
关键词
固体火箭发动机
声涡耦合
实验研究
综述
solid rocket motor
vortex-acoustic coupling
experimental study
overview
