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过渡型凹腔超声速燃烧流动振荡抑制方法

蔡建华 田野 肖保国 邢建文

蔡建华, 田野, 肖保国, 等. 过渡型凹腔超声速燃烧流动振荡抑制方法[J]. 航空动力学报, 2023, 38(3):578-587 doi: 10.13224/j.cnki.jasp.20210495
引用本文: 蔡建华, 田野, 肖保国, 等. 过渡型凹腔超声速燃烧流动振荡抑制方法[J]. 航空动力学报, 2023, 38(3):578-587 doi: 10.13224/j.cnki.jasp.20210495
CAI Jianhua, TIAN Ye, XIAO Baoguo, et al. Suppressing oscillation method of supersonic combustion and flow in transitional cavity[J]. Journal of Aerospace Power, 2023, 38(3):578-587 doi: 10.13224/j.cnki.jasp.20210495
Citation: CAI Jianhua, TIAN Ye, XIAO Baoguo, et al. Suppressing oscillation method of supersonic combustion and flow in transitional cavity[J]. Journal of Aerospace Power, 2023, 38(3):578-587 doi: 10.13224/j.cnki.jasp.20210495

过渡型凹腔超声速燃烧流动振荡抑制方法

doi: 10.13224/j.cnki.jasp.20210495
基金项目: 中国空气动力研究与发展中心基础和前沿技术研究基金(PJD20190073)
详细信息
    作者简介:

    蔡建华(1993-),男,助理研究员,硕士,主要从事超声速燃烧流动研究。E-mail:caijianhua.1993@163.com

    通讯作者:

    肖保国(1980-),男,研究员,博士,主要从事超声速燃烧流动研究。E-mail:xbgxl@163.com

  • 中图分类号: V235.21

Suppressing oscillation method of supersonic combustion and flow in transitional cavity

  • 摘要:

    针对长深比为10.0的过渡型凹腔在隔离段入口马赫数为3.0条件下存在的冷流自激振荡现象,提出了一种凹腔内增加肋条抑制振荡的方案。通过试验和数值计算,对该方案抑制振荡的效果进行了检验,并分析了肋条增加前后燃烧室流场结构和燃烧性能的差别。研究发现:通过在凹腔内增加肋条能够消除过渡型凹腔冷流工况下存在的175.8 Hz的自激振荡,燃烧流场也更加稳定;增加肋条后凹腔的稳焰能力有所降低,部分在凹腔未完全燃烧的煤油进入扩张段后继续发生反应,从而使燃烧区向下游延伸、增大,发动机的燃烧效率和净推力分别降低5.4%和8.9%,但推力更加平稳;燃烧室一维平均热流密度峰值由2.9 MW/m2降低至1.8 MW/m2,燃烧室的热环境大幅改善。

     

  • 图 1  直连式脉冲燃烧风洞[10]

    Figure 1.  Direct-connected pulse combustion wind tunnel[10]

    图 2  风洞试验段(单位:mm)

    Figure 2.  Test section of wind tunnel (unit:mm)

    图 3  喷注支杆示意图(单位:mm)

    Figure 3.  Sketch map of the injection strut (unit:mm)

    图 4  两种不同构型的凹腔

    Figure 4.  Two cavities with different configurations

    图 5  基础凹腔计算模型

    Figure 5.  Calculation model of basic cavity

    图 6  网格无关性验证

    Figure 6.  Grid independence verification

    图 7  基础凹腔一个周期内波系结构

    Figure 7.  Waves system of basic cavity in one period

    图 8  冷流工况下基础凹腔的壁面压力

    Figure 8.  Wall pressure of basic cavity under non-reacting flow

    图 9  基础凹腔流场不同切面马赫数分布

    Figure 9.  Mach number distributions on different slices of basic cavity

    图 10  基础凹腔对称面流场结构

    Figure 10.  Flow field on symmetry plane of basic cavity

    图 11  三维凹腔波系结构

    Figure 11.  Waves system of three-dimensional cavity

    图 12  冷流流动时声压级曲线

    Figure 12.  Sound pressure level of non-reacting flow

    图 13  三维凹腔不同切面流场结构

    Figure 13.  Flow field at different slices of three-dimensional cavity

    图 14  两种凹腔燃烧流场对比

    Figure 14.  Comparison of reacting flow fields of two cavities

    图 15  燃烧工况下基础凹腔壁面压力

    Figure 15.  Wall pressure of basic cavity under reacting flow

    图 16  燃烧工况下三维凹腔壁面压力

    Figure 16.  Wall pressure of three-dimensional cavity underreacting flow

    图 17  燃烧工况下基础凹腔内非稳态现象

    Figure 17.  Unsteady phenomenon of basic cavity under reacting flow

    图 18  燃烧工况下三维凹腔内的马赫数和温度分布

    Figure 18.  Mach number and temperature distribution of three-dimensional cavity under reacting flow

    图 19  燃烧工况下的声压级曲线

    Figure 19.  Sound pressure level under reaction flow

    图 20  燃烧工况下凹腔中心线沿程压力分布对比

    Figure 20.  Comparison of wall pressure distributions along centerline under reacting flow

    图 21  壁面热流密度分布对比

    Figure 21.  Comparison of heat flux distributions

    图 22  壁面一维热流密度分布对比

    Figure 22.  Comparison of one-dimensional heat flux distributions

    表  1  来流条件

    Table  1.   Inflow condition

    马赫数分子量摩尔分数/%静温/K静压/kPa
    氧气氮气
    3.026.7121.421.357.3545.244.0
    下载: 导出CSV

    表  2  燃烧性能

    Table  2.   Combustion performance

    参数基础凹腔三维凹腔
    燃烧
    效率/%
    凹腔出口处76.648.1
    扩张段出口处98.593.1
    壁面压力
    积分/N
    冷流工况175.5*(38.2~312.9)178.8
    燃烧工况−109.5*(−142.8~−76.2)−80.7
    净推力/N285.0*259.5
    注:右上角带有星号“*”角标的数字表示推力积分波动值的平均值。
    下载: 导出CSV
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  • 收稿日期:  2021-09-06
  • 网络出版日期:  2022-10-26

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