大扩张比喷管分离流动冷流试验研究

刘沛, 李耿, 赵利

刘沛, 李耿, 赵利. 大扩张比喷管分离流动冷流试验研究[J]. 实验流体力学, 2017, 31(1): 62-66. DOI: 10.11729/syltlx20160067
引用本文: 刘沛, 李耿, 赵利. 大扩张比喷管分离流动冷流试验研究[J]. 实验流体力学, 2017, 31(1): 62-66. DOI: 10.11729/syltlx20160067
Liu Pei, Li Geng, Zhao Li. Experimental study on cold separation flow in large expansion ratio nozzle[J]. Journal of Experiments in Fluid Mechanics, 2017, 31(1): 62-66. DOI: 10.11729/syltlx20160067
Citation: Liu Pei, Li Geng, Zhao Li. Experimental study on cold separation flow in large expansion ratio nozzle[J]. Journal of Experiments in Fluid Mechanics, 2017, 31(1): 62-66. DOI: 10.11729/syltlx20160067

大扩张比喷管分离流动冷流试验研究

详细信息
    通讯作者:

    刘沛(1989-),男,河南省南阳人,助理工程师。研究方向:固体火箭发动机设计。通信地址:陕西省西安市120信箱(710025)。E-mail:liupei0102@163.com

  • 中图分类号: V435

Experimental study on cold separation flow in large expansion ratio nozzle

  • 摘要: 为研究流动分离条件下气流特性,针对某试验大扩张比喷管,开展了地面冷流试验研究。试验得到了分离点前后测点压强与入口压强的变化规律,并对测点压强数据进行了傅里叶分析。研究结果表明,随着入口压强升高,分离点前测点压强不断升高,分离点后测点压强降低,远离分离点的下游测点压强基本不变,且略低于环境压强;流动分离会导致分离点后压强脉动增大,且脉动主要为50Hz以内的低频脉动,该研究为大扩张比喷管的设计及试验提供了重要参考。
    Abstract: In order to investigate flow characteristics of the separation flow, cold flow tests were conducted in a solid rocket motor nozzle with a high expansion ratio under the sea level condition. The influences of the inlet pressure on the pressure of test points upstream and downstream the separation location were revealed in the tests and pressure data were analyzed by means of FFT. The results show that the pressure increases for test points upstream the separation location but decreases for test points downstream the separation location. The pressure is steady and right below the ambient pressure for test points downstream and far away from the separation location. Pressure fluctuations become more evident after separation in comparison with that before separation, and the enhanced pressure fluctuations were mainly low-frequency fluctuations in the range of 50Hz. The research has important reference to the designing and testing of the nozzle with a high expansion ratio.
  • 图  1   喷管结构图

    Fig.  1   Configuration of test nozzle

    图  2   试验装置照片

    Fig.  2   Photo of test facility

    图  3   试验过程喷管外壁情况

    Fig.  3   Photo of nozzle in test

    图  4   入口测点压强-时间曲线

    Fig.  4   p-t curve at inlet

    图  5   p1测点压强-时间曲线

    Fig.  5   p-t curve oftest point p1

    图  6   p2测点压强-时间曲线

    Fig.  6   p-t curve of test point p2

    图  7   p8测点压强-时间曲线

    Fig.  7   p-t curve oftest point p8

    图  8   流动分离条件下喷管壁面压强变化曲线[15]

    Fig.  8   Wall pressure distribution under the separation condition

    图  9   试验壁面压强分布,pc=4.28MPa

    Fig.  9   Wall pressure distribution by test,pc=4.28MPa

    图  10   测点p4~p6p11的压强-时间曲线,pc = 4.28MPa

    Fig.  10   p-t curve of test points p4~p6p11,pc = 4.28MPa

    图  11   测点p4数据频谱

    Fig.  11   Spectrum of pressure of test point p4

    图  12   测点p5数据频谱

    Fig.  12   Spectrum of pressure of test point p5

    图  13   测点p6数据频谱

    Fig.  13   Spectrum of pressure of test point p6

    图  14   测点p11数据频谱

    Fig.  14   Spectrum of pressure of test point p11

    表  1   测点p4~p6p11压强数据统计分析

    Table  1   Statistic analyses of pressure data of test points p4~p6p11

    Pointspmin/kPapmax/kPa(pmax-pmin)/kPapstd/kPa
    p445.5150.274.760.6642
    p535.2737.712.440.3073
    p663.6675.9212.261.5333
    p1184.2798.8814.612.0707
    下载: 导出CSV
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  • 期刊类型引用(1)

    1. 吴超,黄兴. 基于被动引射的大扩张比喷管流动数值研究. 航空科学技术. 2022(10): 31-37 . 百度学术

    其他类型引用(3)

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出版历程
  • 收稿日期:  2016-04-16
  • 修回日期:  2016-07-25
  • 刊出日期:  2017-02-24

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