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基于凝结实验平台的音速喷嘴凝结现象研究

王超 林大烜 丁红兵 王刚 安海骄

王超, 林大烜, 丁红兵, 等 . 基于凝结实验平台的音速喷嘴凝结现象研究[J]. 北京航空航天大学学报, 2017, 43(11): 2232-2239. doi: 10.13700/j.bh.1001-5965.2017.0074
引用本文: 王超, 林大烜, 丁红兵, 等 . 基于凝结实验平台的音速喷嘴凝结现象研究[J]. 北京航空航天大学学报, 2017, 43(11): 2232-2239. doi: 10.13700/j.bh.1001-5965.2017.0074
WANG Chao, LIN Daxuan, DING Hongbing, et al. Study on condensation in sonic nozzle based on experimental condensation apparatus[J]. Journal of Beijing University of Aeronautics and Astronautics, 2017, 43(11): 2232-2239. doi: 10.13700/j.bh.1001-5965.2017.0074(in Chinese)
Citation: WANG Chao, LIN Daxuan, DING Hongbing, et al. Study on condensation in sonic nozzle based on experimental condensation apparatus[J]. Journal of Beijing University of Aeronautics and Astronautics, 2017, 43(11): 2232-2239. doi: 10.13700/j.bh.1001-5965.2017.0074(in Chinese)

基于凝结实验平台的音速喷嘴凝结现象研究

doi: 10.13700/j.bh.1001-5965.2017.0074
基金项目: 

国家自然科学基金 61627803

国家自然科学基金 51506148

国家自然科学基金 61673291

天津市自然科学基金 16JCQNJC03700

天津市重点实验室基金 TKLPMC-201611

详细信息
    作者简介:

    王超 男, 博士, 教授。主要研究方向:电学层析成像、多相流测量和生物阻抗检测

    丁红兵 男, 博士, 讲师。主要研究方向:多相流测量、气体流量传感器

    通讯作者:

    丁红兵, E-mail: hbding@tju.edu.cn

  • 中图分类号: TH814

Study on condensation in sonic nozzle based on experimental condensation apparatus

Funds: 

National Natural Science Foundation of China 61627803

National Natural Science Foundation of China 51506148

National Natural Science Foundation of China 61673291

Natural Science Foundation of Tianjin 16JCQNJC03700

Research Fund of Tianjin Key Laboratory TKLPMC-201611

More Information
  • 摘要:

    音速喷嘴中流动的蒸汽或含湿气体由于自身的温降而发生凝结现象,对音速喷嘴的计量会产生一定的影响。针对音速喷嘴凝结现象和自激振荡的复杂变化情况,利用一套凝结实验平台研究了音速喷嘴内湿空气凝结现象,得到了不同条件的喷嘴沿程压力,并建立了凝结流动Eulerian两相模型,对凝结现象的影响因素进行了数值分析,使实验结果得到了验证和补充。结果表明,载气的压力、温度、湿度会对凝结产生比较大的影响。凝结发生位置伴随载气温度、湿度的提高而前移,强度有所增大。随着载气压力的增大,凝结发生位置前移,但是强度相对减弱。自激振荡的频率与载气湿度、温度呈正相关,与载气压力呈负相关,振幅与载气的压力、温度、湿度均呈正相关。

     

  • 图 1  音速喷嘴结构

    Figure 1.  Sonic nozzle structure

    图 2  Wilson线在焓熵(h-s)图中的走势

    Figure 2.  Tendency of Wilson line in an enthalpy-entropy(h-s) map

    图 3  音速喷嘴中膨胀凝结过程

    Figure 3.  Expansion and condensation process in sonic nozzle

    图 4  凝结实验平台结构

    Figure 4.  Structure of experimental condensation apparatus

    图 5  高压雾化装置

    Figure 5.  High-pressure atomization generator

    图 6  实验喷嘴结构和尺寸

    Figure 6.  Structure and size of experimental nozzle

    图 7  沿程压力采集系统

    Figure 7.  Acquisition system of pressure distribution at nozzle wall

    图 8  CFD仿真与实验数据对比

    Figure 8.  Comparison between CFD simulation and experimental data

    图 9  不同入口湿度下喷嘴壁面压力分布

    Figure 9.  Pressure distribution at nozzle wall with different inlet humidity

    图 10  不同入口温度下喷嘴壁面压力分布

    Figure 10.  Pressure distribution at nozzle wall with different inlet temperatures

    图 11  不同入口压力下喷嘴壁面压力分布

    Figure 11.  Pressure distribution at nozzle wall with different inlet pressure

    图 12  不同入口压力下喷嘴壁面压力分布(CFD)

    Figure 12.  Pressure distribution at nozzle wall with different inlet pressure (CFD)

    图 13  不同入口温度下喷嘴壁面压力分布(CFD)

    Figure 13.  Pressure distribution at nozzle wall with different inlet temperatures (CFD)

    图 14  动态压力测试

    Figure 14.  Dynamic pressure test

    图 15  不同自激振荡模式下频率和幅值与过冷度关系

    Figure 15.  Relationship between frequency and amplitude and degree of supercooling under different self-oscillation modes

    表  1  网格独立性测试结果

    Table  1.   Grid independence test results

    参数 网格
    (N1×N2)
    质量流量/(kg·s-1) 相对变化量/%
    N1变化
    N2=120
    850×120 0.053 020 379
    900×120 0.053 027 642 0.013 7
    950×120 0.053 028 746 0.002 1
    N1 = 900
    N2变化
    900×100 0.053 035 973
    900×120 0.053 027 642 0.015 7
    900×140 0.053 026 096 0.002 9
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  • 收稿日期:  2017-02-16
  • 录用日期:  2017-05-19
  • 刊出日期:  2017-11-20

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