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大攻角状态压气机分离流及叶片动力响应特性

倪奇峰 侯安平 刘若阳 周拜豪 张明明

倪奇峰, 侯安平, 刘若阳, 等 . 大攻角状态压气机分离流及叶片动力响应特性[J]. 北京航空航天大学学报, 2017, 43(7): 1410-1418. doi: 10.13700/j.bh.1001-5965.2016.0912
引用本文: 倪奇峰, 侯安平, 刘若阳, 等 . 大攻角状态压气机分离流及叶片动力响应特性[J]. 北京航空航天大学学报, 2017, 43(7): 1410-1418. doi: 10.13700/j.bh.1001-5965.2016.0912
NI Qifeng, HOU Anping, LIU Ruoyang, et al. Separation flow and blade dynamic response characteristic of compressor at high attack angle[J]. Journal of Beijing University of Aeronautics and Astronautics, 2017, 43(7): 1410-1418. doi: 10.13700/j.bh.1001-5965.2016.0912(in Chinese)
Citation: NI Qifeng, HOU Anping, LIU Ruoyang, et al. Separation flow and blade dynamic response characteristic of compressor at high attack angle[J]. Journal of Beijing University of Aeronautics and Astronautics, 2017, 43(7): 1410-1418. doi: 10.13700/j.bh.1001-5965.2016.0912(in Chinese)

大攻角状态压气机分离流及叶片动力响应特性

doi: 10.13700/j.bh.1001-5965.2016.0912
基金项目: 

国家自然科学基金 11290140

详细信息
    作者简介:

    倪奇峰  男, 博士研究生。主要研究方向:叶轮机气动设计、非定常流动及气动弹性

    侯安平  男, 博士, 副教授, 博士生导师。主要研究方向:叶轮机气动设计、空气轴承及高速电机设计、非定常流动及气动弹性

    通讯作者:

    侯安平, E-mail:houap@buaa.edu.cn

  • 中图分类号: V231.3

Separation flow and blade dynamic response characteristic of compressor at high attack angle

Funds: 

National Natural Science Foundation of China 11290140

More Information
  • 摘要:

    为研究大攻角状态压气机转子内部分离区的脱落和传播过程及转子叶片对其动力响应问题,对某跨声速压气机级进行了非定常数值模拟和双向迭代流固耦合数值模拟。研究结果表明,在近失速状态,转子叶片通道内会周期性地发生2次叶背分离区的脱落和传播现象。第1个分离区主要表现出轴向传播特性,其会对下游流场产生影响;第2个分离区主要表现出周向传播特性,其会作用于周向相邻的转子叶片,对转子叶排自身产生激励作用,进而影响叶片表面压力分布,引起叶片较强的动力响应,对叶片结构强度的影响不可忽略。非定常/流固耦合计算手段能够较全面地预测流场中激励源的频率、幅值与位置等,在压气机设计阶段应对此类预测工作予以重视,以期更准确地预测叶片共振及动力响应等问题。

     

  • 图 1  压气机计算模型与计算网格

    Figure 1.  Computational model and mesh of compressor

    图 2  流体网格无关性分析

    Figure 2.  Fluid mesh independence analysis

    图 3  时间步长无关性分析

    Figure 3.  Time step independence analysis

    图 4  90%叶高位置的相对马赫数分布云图

    Figure 4.  Relative Mach number distribution contour at 90% spanwise location

    图 5  监测点相对马赫数时域脉动与频谱分析

    Figure 5.  Relative Mach number time domain fluctuation and frequency spectrum analysis at monitoring point

    图 6  不同非定常时刻的相对马赫数分布云图

    Figure 6.  Relative Mach number distribution contours at different unsteady time points

    图 7  不同非定常时刻的气流角变化

    Figure 7.  Variation of flow angle at different unsteady time points

    图 8  不同非定常时刻叶片叶盆面的压力云图

    Figure 8.  Pressure contour of pressure side of blade at different unsteady time points

    图 9  90%叶高位置的叶片表面压力分布

    Figure 9.  Blade surface pressure distribution at 90% spanwise location

    图 10  转子叶片气动力随时间的变化

    Figure 10.  Variation of aerodynamic force of rotor blade with time

    图 11  叶片振动时域曲线

    Figure 11.  Blade vibration time domain curves

    图 12  叶片振动位移云图

    Figure 12.  Blade vibration displacement contours

    图 13  叶片振动频谱图

    Figure 13.  Frequency spectrum analysis of blade vibration

    表  1  转子叶片材料属性

    Table  1.   Material property of rotor blades

    参数 弹性模量/GPa 泊松比 密度/(kg·m-3)
    数值 120 0.32 4370
    下载: 导出CSV

    表  2  叶片固有频率与振型

    Table  2.   Natural frequency and vibration mode of blade

    阶数 固有频率/Hz 振型
    1 1840
    2 3011
    3 4865
    4 5341
    下载: 导出CSV
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出版历程
  • 收稿日期:  2016-12-02
  • 录用日期:  2017-01-13
  • 刊出日期:  2017-07-20

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