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潜入式喷管背区空腔对压强振荡及旋涡运动影响的实验研究 被引量：4

Experimental study of influence of cavity formed by submerged nozzle on pressure oscillation and vortices motion
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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.
作者 吴亚可 何国强 刘佩进 陈晓龙 肖波 岳赟
机构地区 西北工业大学燃烧流动和热结构国家级重点实验室
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
分类号 V435 [航空宇航科学与技术—航空宇航推进理论与工程]
  • 相关文献

参考文献14

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二级参考文献48

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共引文献37

同被引文献31

  • 1李强,何国强,刘佩进,蔡体敏.模型固体火箭发动机内涡脱落过程的大涡模拟[J].推进技术,2005,26(6):481-484. 被引量：8
  • 2熊永亮,杨丹,郜冶,王革.固体火箭发动机燃烧室内声波振荡的数值研究[J].推进技术,2006,27(6):484-487. 被引量：6
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引证文献4

二级引证文献13

固体火箭技术
2010年 第6期

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