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流场不均匀对液体火箭发动机纵向振荡燃烧影响及控制

李龙飞 杨宝庆 葛树宏 刘佩进 刘新华

李龙飞, 杨宝庆, 葛树宏, 等. 流场不均匀对液体火箭发动机纵向振荡燃烧影响及控制[J]. 航空动力学报, 2022, 37(12):1-7 doi: 10.13224/j.cnki.jasp.20210356
引用本文: 李龙飞, 杨宝庆, 葛树宏, 等. 流场不均匀对液体火箭发动机纵向振荡燃烧影响及控制[J]. 航空动力学报, 2022, 37(12):1-7 doi: 10.13224/j.cnki.jasp.20210356
LI Longfei, YANG Baoqing, GE Shuhong, et al. Influence and control of non-uniform flow field on longitudinal combustion instability of liquid rocket engines[J]. Journal of Aerospace Power, 2022, 37(12):1-7 doi: 10.13224/j.cnki.jasp.20210356
Citation: LI Longfei, YANG Baoqing, GE Shuhong, et al. Influence and control of non-uniform flow field on longitudinal combustion instability of liquid rocket engines[J]. Journal of Aerospace Power, 2022, 37(12):1-7 doi: 10.13224/j.cnki.jasp.20210356

流场不均匀对液体火箭发动机纵向振荡燃烧影响及控制

doi: 10.13224/j.cnki.jasp.20210356
基金项目: 民用航天重点基础研究(D010201)
详细信息
    作者简介:

    李龙飞(1977-),男,研究员,博士生,研究领域为液体火箭发动机喷雾燃烧与燃烧不稳定性。E-mail:13809153816@163.com

  • 中图分类号: V434.1

Influence and control of non-uniform flow field on longitudinal combustion instability of liquid rocket engines

  • 摘要:

    针对常温推进剂发动机推力室再生冷却和撞击式喷注器结构,分析了推力室身部与喷注器对接部位的流场特性,对流场均匀性进行了实验测量。结果表明:推力室身部再生冷却通道出口压力存在约0.15 MPa周向不均匀。身部出口节流显著提高局部流速,使喷注器面氧化剂湍流度和不均匀性增加,进而改变燃烧特性。通过撞击喷注单元雾化试验,获得了18 m/s的推进剂入口边界流速。基于喷注器流场均匀性,提出控制推进剂流速,降低不均匀性,进而抑制纵向高频燃烧不稳定性的控制方法。发动机热试结果表明,采用15±1 m/s的推进剂入口流速,控制方法抑制了纵向高频燃烧不稳定性。

     

  • 图 1  试验条件下的振动加速度曲线

    Figure 1.  Curves of vibration acceleration under test conditions

    图 2  稳态和外部扰动条件下直流自击式喷注单元的雾化场

    Figure 2.  Atomization field of impinging jet injector under steady state and external disturbance conditions

    图 3  推力室局部结构图

    Figure 3.  Partial structure diagram of thrust chamber

    图 4  推力室压力测点分布示意图

    Figure 4.  Schematic diagram of pressure measuring point distribution in thrust chamber

    图 5  推力室不同测点的流体压力

    Figure 5.  Fluid pressure at different measuring points in thrust chamber

    图 6  推力室P7测点横截面压力与P8测点横截面速度

    Figure 6.  Pressure of P7 and velocity of P8 at different cross-sections of the thrust chamber

    图 7  热试验后喷注器表面积碳的比较

    Figure 7.  Comparison of carbon deposit on injector surface after thermal test

    图 8  热试验期间轴向、径向和切向的RMS振动曲线

    Figure 8.  RMS vibration curves of axial,radial and tangential directions during thermal test

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出版历程
  • 收稿日期:  2021-07-08
  • 网络出版日期:  2022-09-30

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