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进口导叶角对叶根失稳压气机流动失稳的影响

陈晓松 武文倩 潘天宇 李秋实

陈晓松, 武文倩, 潘天宇, 等. 进口导叶角对叶根失稳压气机流动失稳的影响[J]. 航空动力学报, 2023, 38(1):215-222 doi: 10.13224/j.cnki.jasp.20210355
引用本文: 陈晓松, 武文倩, 潘天宇, 等. 进口导叶角对叶根失稳压气机流动失稳的影响[J]. 航空动力学报, 2023, 38(1):215-222 doi: 10.13224/j.cnki.jasp.20210355
CHEN Xiaosong, WU Wenqian, PAN Tianyu, et al. Influence of inlet guide vane angle on flow instability of hub instability compressor[J]. Journal of Aerospace Power, 2023, 38(1):215-222 doi: 10.13224/j.cnki.jasp.20210355
Citation: CHEN Xiaosong, WU Wenqian, PAN Tianyu, et al. Influence of inlet guide vane angle on flow instability of hub instability compressor[J]. Journal of Aerospace Power, 2023, 38(1):215-222 doi: 10.13224/j.cnki.jasp.20210355

进口导叶角对叶根失稳压气机流动失稳的影响

doi: 10.13224/j.cnki.jasp.20210355
基金项目: 国家自然科学基金(51636001, 51976005); 国家科技重大专项(2017-Ⅱ-0005-0018)
详细信息
    作者简介:

    陈晓松(1996-),女,硕士生,主要从事叶轮机械流动不稳定性研究

    通讯作者:

    潘天宇(1989-),男,副教授,博士,主要从事叶轮机械流动不稳定性研究。E-mail: pantianyu@buaa.edu.cn

  • 中图分类号: V231.3

Influence of inlet guide vane angle on flow instability of hub instability compressor

  • 摘要:

    以一台航空高速压气机为研究对象,通过加装进口导叶调整压气机进气预旋角,采集失稳过程中的动态压力信号,观察不同导叶角度、流动失稳演化过程。结果表明:在负导叶角情况下,压气机由转子叶尖突尖波引起失稳;在零导叶角及较小的正导叶角情况下,由静子叶根区域的局部喘振诱发失稳;在较大的正导叶角情况下,静子叶根在节流过程中首先出现局部失稳,进一步节流导致叶尖旋转失速团出现,压气机完全失稳。分析认为,导叶角的增加通过降低反力度,调整了转静间的负荷分配,从而引起了失速初始扰动发生上述“转子突尖波-静子局部喘振-静子局部失稳”的转变。

     

  • 图 1  压气机实验台

    Figure 1.  Compressor test rig

    图 2  实验台测点布置图

    Figure 2.  Layout of measuring transducers of test rig

    图 3  78%设计转速总压比-无量纲流量特性图

    Figure 3.  Total pressure ratio-non-dimensional mass flow rate performance map of 78% design speed

    图 4  0°进口导叶角失稳过程

    Figure 4.  Instability evolution at 0° inlet guide vane angle

    图 5  0°进口导叶角静子叶根局部喘振现象

    Figure 5.  Partial surge at 0° inlet guide vane angle at stator hub region

    图 6  −2°进口导叶角失稳过程

    Figure 6.  Instability evolution at −2° inlet guide vane angle

    图 7  −2°进口导叶角转子叶尖旋转失速团

    Figure 7.  Rotating stall process at −2° inlet guide vane angle at rotor tip region

    图 8  −4°进口导叶角失稳过程

    Figure 8.  Instability evolution at −4° inlet guide vane angle

    图 9  −4°进口导叶角转子叶尖旋转失速团

    Figure 9.  Rotating stall process at −4° inlet guide vane angle at rotor tip region

    图 10  −6°进口导叶角失稳过程

    Figure 10.  Instability evolution at −6° inlet guide vane angle

    图 11  −6°进口导叶角转子叶尖旋转失速团

    Figure 11.  Rotating stall process at −6° inlet guide vane angle at rotor tip region

    图 12  +2°进口导叶角失稳过程

    Figure 12.  Instability evolution at +2° inlet guide vane angle

    图 13  +4°进口导叶角失稳过程

    Figure 13.  Instability evolution at +4° inlet guide vane angle

    图 14  +6°进口导叶角失稳过程

    Figure 14.  Instability evolution at +6° inlet guide vane angle

    表  1  跨声速轴流压气机主要设计参数

    Table  1.   Main design parameters of the transonic axial compressor

    设计参数数值
    转速/(r/min)22000
    压比1.6
    绝热效率0.84
    质量流量/(kg/s)13.5
    转子叶片数17
    转子叶尖马赫数1.21
    轮毂比0.565
    展弦比0.956
    第1排静子叶片数29
    第2排静子叶片数29
    下载: 导出CSV
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出版历程
  • 收稿日期:  2021-07-08
  • 网络出版日期:  2022-09-07

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