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某固体火箭发动机工作末期不稳定燃烧

苏万兴 李世鹏 张峤 赵艳栋 叶青青 王宁飞

苏万兴, 李世鹏, 张峤, 赵艳栋, 叶青青, 王宁飞. 某固体火箭发动机工作末期不稳定燃烧[J]. 航空动力学报, 2013, 28(10): 2376-2383.
引用本文: 苏万兴, 李世鹏, 张峤, 赵艳栋, 叶青青, 王宁飞. 某固体火箭发动机工作末期不稳定燃烧[J]. 航空动力学报, 2013, 28(10): 2376-2383.
SU Wan-xing, LI Shi-peng, ZHANG Qiao, ZHAO Yan-dong, YE Qing-qing, WANG Ning-fei. Combustion instability at end of burning in a solid rocket motor[J]. Journal of Aerospace Power, 2013, 28(10): 2376-2383.
Citation: SU Wan-xing, LI Shi-peng, ZHANG Qiao, ZHAO Yan-dong, YE Qing-qing, WANG Ning-fei. Combustion instability at end of burning in a solid rocket motor[J]. Journal of Aerospace Power, 2013, 28(10): 2376-2383.

某固体火箭发动机工作末期不稳定燃烧

基金项目: 国家自然科学基金(51076015)

Combustion instability at end of burning in a solid rocket motor

  • 摘要: 针对某固体火箭发动机工作末期出现的压力振荡现象开展了数值研究与线性预估.通过有限元方法得到了燃烧室空腔的声模态及固有声振频率,轴向1阶与2阶声振频率随燃面退移先减小后增大;利用大涡模拟方法分析了燃烧室内的流场特性及压力振荡特性,振荡频率与试验结果一致,判定该发动机出现了以轴向1阶声振频率为主导的不稳定燃烧;其次分析了发动机内阻尼特性,其阻尼随燃面退移不断减小;最后通过不稳定燃烧线性理论解释了该发动机工作末期出现压力振荡的机理,表明燃面退移过程中喉通比下降是导致发动机由线性稳定转向线性不稳定状态的关键因素.

     

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出版历程
  • 收稿日期:  2012-10-17
  • 刊出日期:  2013-10-28

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