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低雷诺数下低压涡轮叶片振动对分离及转捩的影响机制

张英强 张燕峰 朱淼怡 董旭 王名扬 卢新根

张英强, 张燕峰, 朱淼怡, 等. 低雷诺数下低压涡轮叶片振动对分离及转捩的影响机制[J]. 航空动力学报, 2024, 39(9):20220631 doi: 10.13224/j.cnki.jasp.20220631
引用本文: 张英强, 张燕峰, 朱淼怡, 等. 低雷诺数下低压涡轮叶片振动对分离及转捩的影响机制[J]. 航空动力学报, 2024, 39(9):20220631 doi: 10.13224/j.cnki.jasp.20220631
ZHANG Yingqiang, ZHANG Yanfeng, ZHU Miaoyi, et al. Influence mechanism of low-pressure turbine blade vibration on separation and transition at low Reynolds number[J]. Journal of Aerospace Power, 2024, 39(9):20220631 doi: 10.13224/j.cnki.jasp.20220631
Citation: ZHANG Yingqiang, ZHANG Yanfeng, ZHU Miaoyi, et al. Influence mechanism of low-pressure turbine blade vibration on separation and transition at low Reynolds number[J]. Journal of Aerospace Power, 2024, 39(9):20220631 doi: 10.13224/j.cnki.jasp.20220631

低雷诺数下低压涡轮叶片振动对分离及转捩的影响机制

doi: 10.13224/j.cnki.jasp.20220631
基金项目: 国家自然科学基金(52276044)
详细信息
    作者简介:

    张英强(1998-),男,硕士生,主要从事叶轮机械气动热力学研究

    通讯作者:

    张燕峰(1983-),男,研究员,博士,研究领域为叶轮机械气动热力学。E-mail:zhangyf@iet.cn

  • 中图分类号: V232.4

Influence mechanism of low-pressure turbine blade vibration on separation and transition at low Reynolds number

  • 摘要:

    低压涡轮叶片振动显著影响边界层演化过程和流动状态,进而影响气动性能。为了探究低压涡轮叶片振动对分离转捩的影响机制,利用数值模拟手段对比分析了低雷诺数(Re=25000)下低压涡轮叶片不同频率的振动对吸力面边界层分离及转捩和流动损失的影响。研究表明,叶片因振动与流体产生的相对运动使分离流与主流提前相遇从而引发转捩提前,限制分离泡的发展,缩减分离泡的尺寸,削弱分离泡内部回流掺混。叶片振动使边界层厚度有所减小,削弱了尾缘附近的流动阻塞与尾迹掺混,大幅度降低了分离及转捩过程中的湍流脉动水平,上述变化使总压损失得到了大幅度降低,最高可以降低23.02%,气动性能得到大大改善。

     

  • 图 1  计算域网格

    Figure 1.  Computational domain grid

    图 2  静止叶片静压分布系数数值模拟结果与试验结果对比

    Figure 2.  Comparison of numerical simulation and experiment results of static pressure distribution coefficient when the blade is stationary

    图 3  静止和振动叶片吸力面壁面摩擦力对比

    Figure 3.  Comparison of the friction force on suction surface of stationary and vibrating blades

    图 4  静止和振动叶片吸力面壁面时均速度对比

    Figure 4.  Comparison of time-averaged velocities on suction surface of stationary and vibrating blades

    图 5  静止和振动叶片吸力面不同流向位置处速度型对比

    Figure 5.  Comparison of boundary layer velocity at various streamwise locations on blade suction surface of stationary and vibrating blades

    图 6  叶片以175 Hz频率振动时吸力面不同时刻的瞬态压力场及流线分布

    Figure 6.  Transient pressure field and streamline distribution on suction surface at different times of vibrating blade with 175 Hz

    图 7  叶片以175 Hz频率振动不同时刻吸力面壁面摩擦力分布

    Figure 7.  Friction force distribution on suction surface at different times of vibrating blade with 175 Hz

    图 8  静止和振动叶片吸力面边界层参数对比

    Figure 8.  Comparison of boundary layer parameters on suction surface of stationary and vibrating blades

    图 9  静止和振动叶片吸力面湍流度对比

    Figure 9.  Comparison of turbulence near suction surface of stationary and vibrating blades

    图 10  静止叶片及不同振动频率叶片叶型损失对比

    Figure 10.  Comparison of profile losses among stationary blades and blades with different vibration frequencies

    表  1  叶型PACK-B的几何特性及气动参数

    Table  1.   Geometric characteristics and aerodynamic parameters of airfoil PACK-B

    参数数值
    弦长C/mm83.28
    轴向弦长Cax/mm75.4
    栅距S/mm66.8
    几何进气角β1/(°)35
    几何出气角β2/(°)60
    载荷系数1.1
    下载: 导出CSV
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  • 收稿日期:  2022-08-29
  • 网络出版日期:  2024-03-04

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