摘要
通过转角涡脱落二维缩比实验器的冷流实验,验证了声-涡耦合机理,即当转角涡脱落频率与声腔固有频率接近时将引起压强振荡,并通过改变潜入式喷管背区空腔体积,研究了空腔体积大小对压强振荡以及旋涡运动的影响。实验结果表明,实验器中压强振荡的振幅随着潜入式喷管背区空腔体积的减小而降低,当背区空腔体积为0时,压强振荡消失。通过高速流场显示技术,获得了不同背区空腔体积时的旋涡运动情况。分析表明,随着空腔体积的逐渐减小,旋涡脱落变得杂乱而没有规则,无法与实验器声腔耦合,从而不能产生压强振荡。
Pressure oscillation induced by corner vortex shedding and acoustics in a scaled experimental facility was studied.The influence of the cavity volume formed by submerged nozzle on pressure oscillation and vortices motion was also investigated experimentally.The experimental data indicate that the amplitude of pressure oscillation descends with the decrease of the cavity volume formed by submerged nozzle.The vortices motion was studied by the high speed visualization.The decrease of the cavity volume tends to strengthen the vortices motion in the cavity zone,which disturbs the vortex shedding to prevent its couple with acoustics,therefore the pressure oscillation disappears.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2010年第6期621-625,共5页
Journal of Solid Rocket Technology
关键词
固体火箭发动机
潜入式喷管
涡脱落
压强振荡
高速摄影
solid rocket motor
submerged nozzle
vortex shedding
pressure oscillation
high speed visualization
作者简介
吴亚可（1984-），男，博士生，主要从事固体火箭发动机总体设计。E-mail：wuyake@sina.com.cn
