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李仁凤,陈帅,胡晓磊.两级喷管喉径比对燃气蒸汽弹射参数的影响[J].航空动力学报,2019,34(11):2458~2465
两级喷管喉径比对燃气蒸汽弹射参数的影响
Influence of throat diameter ratio of two-stage nozzle on gas-steam ejection parameters
投稿时间:2019-05-13  
DOI:10.13224/j.cnki.jasp.2019.11.018
中文关键词:  燃气蒸汽弹射  喉径比  多相流  内流场  内弹道
英文关键词:gas-steam ejection  throat diameter ratio  multiphase flow  internal flow field  interior ballistics
基金项目:河南省高等学校重点科研项目(20A460025)
作者单位
李仁凤 郑州航空工业管理学院 航空工程学院,郑州 450046 
陈帅 中国电子科技集团公司 第二十七研究所,郑州 450047 
胡晓磊 安徽工业大学 机械工程学院,安徽 马鞍山 243002 
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中文摘要:
      针对两级喷管不同的喉径比参数,建立了耦合弹体运动和气液多相汽化的多相流模型,研究改变喉径比对燃气蒸汽弹射流场参数、弹射装置载荷和弹体内弹道的影响。结果表明:在一定范围内增大或者减小喉径比,均会导致弹射装置流场参数和发射稳定性变差。当喉径比增加过多时,将不能建立满足工作条件的喷水压差;喉径比过小时,激波上移最终会导致燃气发生器工作异常。喉径比为1.46时,尾罩压强差最小,发射稳定性能最优,温度最大值控制在设计值800K内,内弹道参数均满足设计要求。
英文摘要:
      The multi-phase flow models coupling with projectile motion and vaporization were established respectively under different conditions of throat diameter ratio. What’s more, the influence of throat diameter ratio on gas-steam ejection flow field, ejection device load and interior ballistics was studied. Results showed that increasing or decreasing the throat diameter ratio within a certain range led to the deterioration of ejection device flow field and launch stability. When the throat diameter ratio increased too large, the spray pressure difference meeting the working conditions could not be established. When the throat diameter ratio was too small, the shock wave upward movement eventually led to abnormity of the gas generator. When the throat diameter ratio was 1.46, the pressure difference of tail cover was the smallest and the launch stability was the best. The maximum temperature of launch tube was controlled within the design value of 800K, and the interior ballistic parameters could satisfy the design requirements.
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