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附面层吸入式进气道内流动损失特性

邓文剑 王占学 周莉 赵海宇

邓文剑, 王占学, 周莉, 等. 附面层吸入式进气道内流动损失特性[J]. 航空动力学报, 2023, 38(3):698-708 doi: 10.13224/j.cnki.jasp.20210205
引用本文: 邓文剑, 王占学, 周莉, 等. 附面层吸入式进气道内流动损失特性[J]. 航空动力学报, 2023, 38(3):698-708 doi: 10.13224/j.cnki.jasp.20210205
DENG Wenjian, WANG Zhanxue, ZHOU Li, et al. Flow losses characteristics of BLI inlet[J]. Journal of Aerospace Power, 2023, 38(3):698-708 doi: 10.13224/j.cnki.jasp.20210205
Citation: DENG Wenjian, WANG Zhanxue, ZHOU Li, et al. Flow losses characteristics of BLI inlet[J]. Journal of Aerospace Power, 2023, 38(3):698-708 doi: 10.13224/j.cnki.jasp.20210205

附面层吸入式进气道内流动损失特性

doi: 10.13224/j.cnki.jasp.20210205
基金项目: 工信部某前瞻性技术研究项目
详细信息
    作者简介:

    邓文剑(1980-),男,副研究员,博士,主要研究方向为新型推进技术、进排气系统、飞发一体化

    通讯作者:

    王占学(1969-),男,教授、博士生导师,博士,主要研究方向为新型推进技术与发动机总体性能。E-mail: wangzx@nwpu.edu.cn

  • 中图分类号: V231.3

Flow losses characteristics of BLI inlet

  • 摘要:

    用数值仿真手段,对进气道内流总压损失采用逐段对比分析的方法,研究了附面层吸入式(BLI)进气道相对于常规S弯进气道的内流总压损失特性。结果表明:进气道出口马赫数不变,较低来流马赫数和较高来流马赫数工况下(方案对应马赫数0.3以下和马赫数0.6以上),BLI进气道产生的流动损失比常规S弯进气道的大,差量达2.4%;中等来流马赫数工况下(本文方案对应马赫数0.3与马赫数0.6之间),BLI进气道产生的流动损失比常规S弯进气道的略小,差量在0.3%以内;流动损失特性间的差异是由于BLI进气道进口前壁面与进口低能附面流改变了进口段流动特性、及在S弯管道内发展的综合作用结果。

     

  • 图 1  BLI进气道典型结构图

    Figure 1.  Typical structure of BLI inlet

    图 2  唇口剖面型线

    Figure 2.  Profile of lip section

    图 3  进气道几何构型

    Figure 3.  Geometry of inlet

    图 4  BLI进气道局部网格

    Figure 4.  Local mesh of BLI inlet

    图 5  参考进气道模型和网格

    Figure 5.  Geometry and mesh of reference inlet

    图 6  仿真计算结果对比

    Figure 6.  Comparision of simulation result

    图 7  进气道总压恢复性能曲线图

    Figure 7.  Total pressure recover coefficient of inlet

    图 8  进气道对称剖面上的总压恢复系数云图

    Figure 8.  Contour of total pressure recover coefficient in symmetry plane of inlet

    图 9  进气道入口前截面位置

    Figure 9.  Location of inlet entrance front section

    图 10  不同来流马赫数入口前截面相对总压降曲线

    Figure 10.  Relative total pressure drop at inlet front plane with different incoming Mach number

    图 11  BLI进气道入口前截面总压恢复系数云图

    Figure 11.  Contour of total pressure recover coefficient at the highlight plane of BLI S-shaped inlet

    图 12  不同来流马赫数进气道内相对总压降曲线图

    Figure 12.  Relative total pressure drop in inlet with different incoming Mach number

    图 13  进气道喉道面

    Figure 13.  Throat plane of inlet

    图 14  进气道进口段相对总压降

    Figure 14.  Relative total pressure drop in entrance region of inlet

    图 15  进气道上唇口、侧唇口和下唇口位置

    Figure 15.  Location of inlet upper lip, side lip, and lower lip

    图 16  $M{a_\infty } = 0.1$时BLI进气道与S弯进气道唇口流线分布

    Figure 16.  Streamline around the lip of BLI and S-shaped inlet at $M{a_\infty } = 0.1$

    图 17  $M{a_\infty } = 0.4$时BLI进气道与S弯进气道唇口流线分布

    Figure 17.  Streamline around the lip of BLI and S-shaped inlet at $M{a_\infty } = 0.4$

    图 18  $M{a_\infty } = 0.8$时BLI进气道与S弯进气道唇口流线分布

    Figure 18.  Streamline around the lip of BLI and S-shaped inlet at $M{a_\infty } = 0.8$

    图 19  进气道进口截面和喉道截面上总压恢复云图($M{a_\infty } = 0.4$

    Figure 19.  Contour of total pressure recover coefficient at entrance section and throat section of inlet ($M{a_\infty } = 0.4$

    图 20  进气道内管道相对总压降

    Figure 20.  Relative total pressure drop in inlet diffuser

    图 21  进气道壁面流线及扩压段进出口总压分布云图

    Figure 21.  Wall streamline of inlet and contour of total pressure at entrance and exit section of diffuser

    表  1  网格无关性计算结果($M{a_\infty } = 0.4$

    Table  1.   Results of mesh independent calculation ($M{{{a}}_\infty } = 0.4$

    网格数量/104进气道出口总压恢复系数
    4360.9796
    6720.9733
    8250.9715
    10780.9712
    下载: 导出CSV
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出版历程
  • 收稿日期:  2021-04-28
  • 网络出版日期:  2023-02-06

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