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; SU Wan-xing; LI Shi-peng; ZHANG Qiao; ZHAO Yan-dong; YE Qing-qing; WANG Ning-fei

主办：中国航空学会北京航空航天大学

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首页 > 过刊浏览>2013年第28卷第10期 >2013,28(10):2376-2383

某固体火箭发动机工作末期不稳定燃烧

Combustion instability at end of burning in a solid rocket motor

发布日期：2013-10-24

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[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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[Abstract]

Based on a solid rocket motor (SRM),numerical simulation with linear prediction was carried out to study the pressure oscillation at the end of burning.Acoustic modes and natural acoustic frequencies of combustor chamber were obtained by finite element analysis (FEA) method.The results indicate that the first and second axial acoustic frequencies first decrease and then increase with the regression of the burning surface.The flow-field and pressure oscillation characteristics of the combustor were analyzed via large eddy simulation (LES) method.The oscillation frequency was well consistent with the experimental value,confirming that the SRM presented fundamental acoustic combustion instability.Then the damping effect of the motor was analyzed.It shows that the total damping continuously decrease with the regression of the burning surface.Finally,the pressure oscillation mechanism at the end of burning was explained via linear combustion instability theory.The decrease of the throat-to-port area ratio is a key factor that makes the SRM turn from linear stable state to linear unstable state.

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国家自然科学基金(51076015)

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