Volume 29 Issue 10
Oct.  2014
Turn off MathJax
Article Contents
Article Navigation >  Journal of Aerospace Power  > 2014  >  (10): 2288-2293
REN Ze-bin, LIAO Da-xiong, ZHANG Guo-biao. Aerodynamic design of the ejector of 2m×2m supersonic wind tunnel[J]. Journal of Aerospace Power, 2014, (10): 2288-2293. doi: 10.13224/j.cnki.jasp.2014.10.003
Citation: REN Ze-bin, LIAO Da-xiong, ZHANG Guo-biao. Aerodynamic design of the ejector of 2m×2m supersonic wind tunnel[J]. Journal of Aerospace Power, 2014, (10): 2288-2293. doi: 10.13224/j.cnki.jasp.2014.10.003
shu

Aerodynamic design of the ejector of 2m×2m supersonic wind tunnel

doi: 10.13224/j.cnki.jasp.2014.10.003

  • 1. State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China;

  • 2. Facility Design and Instrumentation Institute, China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China

  • Received Date: 2013-06-28
  • Publish Date: 2014-10-28
    Abstract
  • The performance parameters of the ejector were analyzed and computed based on one-dimensional gas dynamic equations under different conditions. The ejector was characterized by multi-nozzles and constant-area mixing. The design compression ratio was 2.1 to 2.7, and the ejection coefficient was 0.392 to 0.651. Twenty four nozzles were installed on two layers, with the area ratio of 0.235. The computational results have good accordance with the 1:13 scale pilot ejector test results. The five experimental compression ratios were a little higher than the design values. Although the operating parameters of the ejector were partly deviated from the design values according to the overall adjustment, the compression ratios and ejection coefficients were still consistent with the computed values. The debugging results of the 2m×2m supersonic wind tunnel show that the performance of the ejector meets the requirements of testing.

     

    • FullText(HTML)
  • loading
    • References(15)
  • [1]
    李立国,张靖周.航空用引射混合器[M].北京:国防工业出版社,2007.
    [2]
    赵静野,孙厚钧,高军.引射器基本工作原理及其应用[J].北京建筑工程学院学报,2001,17(3):12-15. ZHAO Jingye,SUN Houjun,GAO Jun.Basic principles and applications of ejector[J].Journal of Beijing Institute of Civil Engineering and Architecture,2001,17(3):12-15.(in Chinese)
    [3]
    刘政崇,廖达雄,董谊信.高低速风洞气动与结构设计[M].北京:国防工业出版社,2003.
    [4]
    凌其扬,廖达雄,陶祖贤.风洞引射器试验研究[J].气动实验与测量控制,1994,8(2):10-18. LING Qiyang,LIAO Daxiong,TAO Zuxian.Experimental research of wind tunnel injector[J].Aerodynamic Experiment and Measurement and Control,1994,8(2):10-18.(in Chinese)
    [5]
    周廷波,刘卫红,张国彪,等.2m×2m超声速风洞全挠性壁喷管气动设计及动态调试结果分析[J].实验流体力学,2012,26(4):68-72. ZHOU Tingbo,LIU Weihong,ZHANG Guobiao,et al.The aerodynamic design and commissioning of the flexible nozzle of the 2m×2m supersonic wind tunnel[J].Journal of Experiments in Fluid Mechanics,2012,26(4):68-72.(in Chinese)
    [6]
    虞择斌,廖达雄,刘政崇,等.2m超声速风洞总体结构设计[J].实验流体力学,2012,26(2):90-96. YU Zebin,LIAO Daxiong,LIU Zhengchong,et al.The general structural design for 2m supersonic wind tunnel[J].Journal of Experiments in Fluid Mechanics,2012,26(2):90-96.(in Chinese)
    [7]
    Emanuel G.Optimum performance for a single-stage gaseous ejector[J].AIAA Journal,1976,14(9):1292-1296.
    [8]
    Keenan J H,Neumann E P,Lustwerk F.An investigation of ejector design by analysis and experiment[J].Journal of Applied Mechanics,1950,17(3):299-309.
    [9]
    廖达雄,任泽斌,余永生,等.压混合引射器设计与实验研究[J].强激光与粒子束,2006,18(5):728-732. LIAO Daxiong,REN Zebin,YU Yongsheng,et al.Design and experiment of constant pressure mixing ejector[J].High Power Laser and Particle Beams,2006,18(5):728-732.(in Chinese)
    [10]
    王锁芳,李立国.多喷管引射器的性能分析[J].南京航空航天大学学报,1996,28(3):350-356. WANG Suofang,LI Liguo.Performance analysis of a multi-nozzle ejector[J].Journal of Nanjing University of Aeronautics and Astronautics,1996,28(3):350-356.(in Chinese)
    [11]
    邱义芬,王俊清,袁修干.多喷嘴引射器性能计算模型[J].北京航空航天大学学报,1997,23(5):622-626. QIU Yifen,WANG Junqing,YUAN Xiugan.Multiple nozzle ejector performance calculating model[J].Journal of Beijing University of Aeronautics and Astronautics,1997,23(5):622-626.(in Chinese)
    [12]
    缪亚芹,王锁芳,吴恒刚.多喷管引射器试验研究与数值模拟[J]. 南京师范大学学报:工程技术版,2006,6(2):68-71. MIAO Yaqin,WANG Suofang,WU Henggang.Experimental investigation and numerical simulation about the multi-nozzle ejector[J].Journal of Nanjing Normal University:Engineering and Technology,2006,6(2):68-71.(in Chinese)
    [13]
    王锁芳,李立国.六喷管超音速引射器性能的理论分析和实验研究[J].航空动力学报,1996,11(3):312-314,334-335. WANG Suofang,LI Liguo.A study on supersonic 6-nozzle ejector performance[J].Journal of Aerospace Power,1996,11(3):312-314,334-335.(in Chinese)
    [14]
    姜正良,吴万敏.气体引射器的一维流动特性计算及优化设计[J].空气动力学学报,1995,13(4):481-486. JIANG Zhengliang,WU Wanmin.The optimum design and calculation of flow feature of one dimensional flow for gas ejector[J].Acta Aerodynamic Sinica,1995,13(4):481-486.(in Chinese)
    [15]
    张靖周,单勇.二维引射—混合器流场的数值研究与验证[J].航空动力学报,2002,17(5):524-527. ZHANG Jingzhou,SHAN Yong.Numerical computation and examination of a two-dimensional mixer-ejector system[J].Journal of Aerospace Power,2002,17(5):524-527.(in Chinese)
    • Relative Articles
    • Supplements(0)
    • Cited By
  • 加载中

Catalog

    通讯作者: 陈斌, bchen63@163.com
    • 1. 

      沈阳化工大学材料科学与工程学院 沈阳 110142

    1. 本站搜索
    2. 百度学术搜索
    3. 万方数据库搜索
    4. CNKI搜索
    Get Citation
    PDF(815.0KB)
    XML

    Article Metrics

    Article views (1822) PDF downloads(1011) Cited by()
    Proportional views
    Related

    Copyright © 《Journal of Aerospace Power》 All Rights Reserved.

    Supported by: Beijing Renhe Information Technology Co., Ltd.  

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return