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低动能来流下背负式进气道非定常流动特性分析

刘志敏 闫盼盼 张群峰 黎星佐 孙超

刘志敏, 闫盼盼, 张群峰, 等 . 低动能来流下背负式进气道非定常流动特性分析[J]. 北京航空航天大学学报, 2019, 45(4): 672-680. doi: 10.13700/j.bh.1001-5965.2018.0573
引用本文: 刘志敏, 闫盼盼, 张群峰, 等 . 低动能来流下背负式进气道非定常流动特性分析[J]. 北京航空航天大学学报, 2019, 45(4): 672-680. doi: 10.13700/j.bh.1001-5965.2018.0573
LIU Zhimin, YAN Panpan, ZHANG Qunfeng, et al. Unsteady flow characteristics of dorsal inlet under low-energy inflow[J]. Journal of Beijing University of Aeronautics and Astronautics, 2019, 45(4): 672-680. doi: 10.13700/j.bh.1001-5965.2018.0573(in Chinese)
Citation: LIU Zhimin, YAN Panpan, ZHANG Qunfeng, et al. Unsteady flow characteristics of dorsal inlet under low-energy inflow[J]. Journal of Beijing University of Aeronautics and Astronautics, 2019, 45(4): 672-680. doi: 10.13700/j.bh.1001-5965.2018.0573(in Chinese)

低动能来流下背负式进气道非定常流动特性分析

doi: 10.13700/j.bh.1001-5965.2018.0573
基金项目: 

国家自然科学基金 11772314

装备预研领域基金课题 6140206040316JW17001

详细信息
    作者简介:

    刘志敏 男, 博士研究生, 研究员。主要研究方向:飞行器设计

    闫盼盼 男, 博士。主要研究方向:应用计算流体力学

    张群峰 男, 博士, 副教授。主要研究方向:应用计算流体力学

    黎星佐 男, 硕士。主要研究方向:飞行器设计

    孙超 男, 硕士, 高级工程师。主要研究方向:飞行器设计

    通讯作者:

    张群峰, E-mail: zhangqunfeng@263.net

  • 中图分类号: V211.3

Unsteady flow characteristics of dorsal inlet under low-energy inflow

Funds: 

National Natural Science Foundation of China 11772314

National Defense Pre-research Foundation of China 6140206040316JW17001

More Information
  • 摘要:

    为了改善飞翼布局背负式S弯进气道低动能来流状态下的流动性能,采用改进的延迟分离涡模拟(IDDES)方法对原型及改进型背负式进气道流场进行了数值模拟研究,对比分析了进气道流量特性及内部脉动压力特性。结果表明:低动能来流时背负式进气道上部唇口附近存在很大的气流转折角,导致唇口产生分离涡;原型进气道唇口分离涡强度高,高能量分离涡在进气道顶部破裂产生了大范围旋涡结构,进一步加剧了流动分离,从而引发进气道内产生强烈的压力脉动,声压级最大幅值高达145 dB;改进型进气道唇口分离涡得到了有效控制,强度大幅下降,进气道内部压力脉动幅值也显著降低,声压级降幅达8 dB;改进型进气道分离的抑制使进气道有效流通截面积增大,质量流量增加。同时,流场出口品质提升,进气道出口综合畸变指数降低了9.5%。

     

  • 图 1  背负式S弯进气道计算模型

    Figure 1.  Calculation model of dorsal S-shaped inlet

    图 2  对称面网格分布

    Figure 2.  Grid distribution on symmetry plane

    图 3  背负式进气道内Q值等值面分布(Q=1×107 s-2)

    Figure 3.  Q iso-surface distribution inside dorsal inlet(Q=1×107 s-2)

    图 4  背负式进气道唇口附近流线图

    Figure 4.  Streamline near dorsal inlet lip

    图 5  背负式进气道入口前四阶POD模态

    Figure 5.  The first four order POD modes of dorsal inlet

    图 6  改进型背负式进气道内Q值等值面分布(Q=1×107 s-2)

    Figure 6.  Q iso-surface distribution inside improved dorsal inlet (Q=1×107 s-2)

    图 7  改进型背负式进气道唇口附近流线图

    Figure 7.  Streamline near improved dorsal inlet lip

    图 8  改进型背负式进气道入口前四阶POD模态

    Figure 8.  The first four order POD modes of improved dorsal inlet

    图 9  背负式进气道内部横截面流向速度分布云图

    Figure 9.  Streamwise velocity distribution contour of interior sections of dorsal inlet

    图 10  改进型背负式进气道内部横截面流向速度分布云图

    Figure 10.  Streamwise velocity distribution contour of interior sections of improved dorsal inlet

    图 11  背负式进气道质量流量随时间变化曲线

    Figure 11.  Variation curves of mass flux with time of dorsal inlet

    图 12  背负式进气道出口截面总压监测点分布

    Figure 12.  Distribution of total pressure monitor points on outlet section of dorsal inlet

    图 13  σr沿周向分布

    Figure 13.  Circumferential distribution of σr

    图 14  背负式进气道内部前四阶POD模态

    Figure 14.  The first four order POD modes of dorsal inlet interior

    图 15  改进型背负式进气道内部前四阶POD模态

    Figure 15.  The first four order POD modes of improved dorsal inlet interior

    图 16  背负式进气道脉动压力功率谱密度分析及快速傅里叶变换分析

    Figure 16.  Power spectral density and fast Fourier transformation of fluctuating pressure for dorsal inlet

    图 17  改进型背负式进气道脉动压力功率谱密度分析及快速傅里叶变换分析

    Figure 17.  Power spectral density and fast Fourier transformation of fluctuating pressure for improved dorsal inlet

    表  1  畸变指数

    Table  1.   Distortion coefficient

    工况 εav Δσ0 θ/(°) W
    原型 0.034 0.04 135 0.074
    改进型 0.031 0.036 128 0.067
    下载: 导出CSV
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出版历程
  • 收稿日期:  2018-09-28
  • 录用日期:  2018-10-15
  • 网络出版日期:  2019-04-20

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