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压气机叶顶流动不稳定性试验和数值研究

王昊 王牌 向宏辉 张建武 王掩刚

王昊, 王牌, 向宏辉, 等. 压气机叶顶流动不稳定性试验和数值研究[J]. 航空动力学报, 2023, 38(3):674-684 doi: 10.13224/j.cnki.jasp.20210452
引用本文: 王昊, 王牌, 向宏辉, 等. 压气机叶顶流动不稳定性试验和数值研究[J]. 航空动力学报, 2023, 38(3):674-684 doi: 10.13224/j.cnki.jasp.20210452
WANG Hao, WANG Pai, XIANG Honghui, et al. Experiment and numerical investigation on tip flow instabilities of compressors[J]. Journal of Aerospace Power, 2023, 38(3):674-684 doi: 10.13224/j.cnki.jasp.20210452
Citation: WANG Hao, WANG Pai, XIANG Honghui, et al. Experiment and numerical investigation on tip flow instabilities of compressors[J]. Journal of Aerospace Power, 2023, 38(3):674-684 doi: 10.13224/j.cnki.jasp.20210452

压气机叶顶流动不稳定性试验和数值研究

doi: 10.13224/j.cnki.jasp.20210452
基金项目: 国家自然科学基金(51906205); 国家科技重大专项(J2019-Ⅱ-0020-0041)
详细信息
    作者简介:

    王昊(1986-),男,讲师,博士,主要从事叶轮机械非定常流动及压气机不稳定性研究。E-mail:wanghao@nwpu.edu.cn

  • 中图分类号: V231.3

Experiment and numerical investigation on tip flow instabilities of compressors

  • 摘要:

    为了研究大叶顶间隙下压气机的流动失稳演化过程和物理机理,以某单级轴流压气机试验台为研究对象,利用布置于机匣壁面的动态压力传感器测量叶顶流场的脉动特征,利用全通道数值模拟获得与流场失稳发展相关的非定常流动细节。结果表明:随着流量减小压气机内部流动经历了稳定状态、旋转不稳定性和旋转失速3个阶段,叶顶泄漏涡的两种临界行为与不稳定性模式的转变有关。当叶顶泄漏涡移动到相邻叶片尾缘时,在与相邻叶片的干涉作用下开始随时间振荡,导致了小尺度的扰动沿周向传播,即旋转不稳定性。在近失速工况下,叶顶泄漏涡与主流交界面超过叶片流道进口平面,导致前缘溢流,并伴随着前缘径向涡的周期性产生、周向迁移和衰减。此时,前缘径向涡沿周向几乎呈均匀分布,构成了有序传播的扰动。随着压气机被进一步节流,前缘径向涡的有序传播被破坏,形成了局部聚集的分布特征,从而产生了局部堵塞更强、熵更高的失速团。

     

  • 图 1  压气机试验台示意图

    Figure 1.  Schematic diagram of the compressor experiment rig

    图 2  动态压力测试布局示意图

    Figure 2.  Setup schematic diagram of time-resolved pressure measurements

    图 3  压气机气动特性线(试验测量和数值模拟)

    Figure 3.  Performance curve of compressor (experiment measurement and numerical simulation)

    图 4  动态压力时间序列和频谱(试验结果)

    Figure 4.  Time traces and frequency spectra of dynamic pressure (experimental result)

    图 5  RI2工况下动态压力的频率谱、相干系数谱和相位谱(试验结果)

    Figure 5.  Spectra of frequency, coherence and phase angle of measured unsteady pressure at RI2 condition (experimental result)

    图 6  压气机计算网格细节

    Figure 6.  Compressor calculated mesh details

    图 7  RI2和RS工况下测试和计算的动态压力频谱对比

    Figure 7.  Comparison of measured and calculated dynamic pressure spectra at RI2 and RS condition

    图 8  RI1工况下瞬态叶顶泄漏涡结构($ {\lambda }_{2} $判据)和叶片表面静压系数

    Figure 8.  Instants of tip leakage vortex structure ($ {\lambda }_{2} $ criterion ) and blade surface pressure at RI1 condition

    图 9  RI1工况下98%相对叶高下不同时刻叶片表面压力系数和叶尖泄漏速度弦向分布

    Figure 9.  Pressure coefficient of blade surface at 98% relative blade height and blade tip leakage velocity distribution for different instants at RI1 condition

    图 10  RI2工况下的叶顶间隙blade to blade截面流线及静压系数分布

    Figure 10.  Distribution of blade to blade section streamline and static pressure coefficient of tip clearance at RI2 condition

    图 11  RI3工况下前缘径向涡流线($ {\lambda }_{2} $准则)

    Figure 11.  Leading edge vortex streamlines at RI3 condition ($ {\lambda }_{2} $ criterion )

    图 12  RI3工况下前缘涡动力学的瞬态演化

    Figure 12.  Transients evolution of leading edge vortex dynamics at RI3 conditions

    图 13  RI3和RS工况下叶顶静压分布和RS工况下叶顶熵的分布

    Figure 13.  Distribution of blade tip static pressure distribution at RI3 and RS condition and blade tip entropy distribution at RS conditionn

    表  1  压气机关键设计参数

    Table  1.   Key design parameters of the compressor

    参数数值
    直径/mm600
    轮毂比0.7
    设计转速/(r/min)3000
    设计流量/(kg/s)4.9
    进口导叶数13
    叶片数21
    展弦比1.41
    稠度1.598
    转子叶顶间隙2.2%H
    转子叶顶间隙3.1%C
    叶顶线速度/(m/s)93.62
    下载: 导出CSV
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  • 收稿日期:  2021-08-15
  • 网络出版日期:  2022-09-07

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