Volume 30 Issue 8
Aug.  2015
Turn off MathJax
Article Contents
Article Navigation >  Journal of Aerospace Power  > 2015  >  30(8): 1988-1996
LIU Jian, JI Hong-hu, LI Ning, YU Ming-fei. Effects of funnel-shaped mixer on thrust and infrared radiation characteristics of turbofan engine[J]. Journal of Aerospace Power, 2015, 30(8): 1988-1996. doi: 10.13224/j.cnki.jasp.2015.08.024
Citation: LIU Jian, JI Hong-hu, LI Ning, YU Ming-fei. Effects of funnel-shaped mixer on thrust and infrared radiation characteristics of turbofan engine[J]. Journal of Aerospace Power, 2015, 30(8): 1988-1996. doi: 10.13224/j.cnki.jasp.2015.08.024
shu

Effects of funnel-shaped mixer on thrust and infrared radiation characteristics of turbofan engine

doi: 10.13224/j.cnki.jasp.2015.08.024

  • 1. College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;

  • 2. Department of Combustion Research, Guizhou Aero-engine Research Institute, Aviation Industry Corporation of China, Guiyang 550081, China

  • Received Date: 2014-02-13
  • Publish Date: 2015-08-28
    Abstract
  • The flow fields, thrust coefficient and infrared radiation characteristics of exhaust systems with funnel-shaped mixer were analyzed, and compared with annular mixer. The flow fields were calculated by Fluent commerical software, and the infrared radiation characteristics were calculated by by reverse Monte-Carlo method. Effects of funnel-shaped mixer on thrust coefficient and infrared characteristics of exhaust system were analyzed. The results show that: (1) When the funnel-shaped mixer is used, low temperature bypass stream is easy to eject into high temperature core stream, and the temperature distribution on cross section of exhaust system is similar to chrysanthemum. (2) When the funnel-shaped mixer is used, the infrared thrust coefficient of exhaust system decreases by 0.2%. (3) When the funnel-shaped mixer is used, the infrared radiation of plume decreases at all detection angles, down by 44.6% at detection angle of 90 degree, meanwhile the infrared radiation of wall increases little at large detection angles.

     

    • FullText(HTML)
  • loading
    • References(19)
  • [1]
    武振波,武哲.武装直升机红外隐身系统研究[J].北京航空航天大学学报,2003,29(7):588-592. WU Zhenbo,WU Zhe.Research on infrared stealth system for armed helicopter[J].Journal of Beijing University of Aeronautics and Astronautics,2003,29(7):588-592.(in Chinese)
    [2]
    Mahulikar S P,Sonawane H R,Rao G A.Infrared signature studies of aerospace vehicles[J].Progress in Aerospace Sciences 2007,43(7/8):218-245.
    [3]
    曲长文,苏峰,李炳荣,等.反辐射导弹对抗技术[M].北京:国防工业出版社,2012.
    [4]
    桑建华.飞行器隐身技术[M].北京:航空工业出版社,2013.
    [5]
    Presz W,Reynolds G,McCormick D.Thrust augmentation using mixer-ejector-diffuser systems[R].AIAA 94-0020,1994.
    [6]
    Presz W,Reynolds G,Hunter C.Thrust augmentation with mixer/ejector systems[R].AIAA-2002-0230,2002.
    [7]
    Presz W,Gousy R,Morin B.Forced mixer lobes in ejector designs[R].AIAA 86-1614,1986.
    [8]
    Presz W,Blinn R F,Morin B.Short efficient ejector systems[R].AIAA 87-1837,1987.
    [9]
    邵万仁,吴寿生.涡扇发动机菊花型排气混合器的初步选型试验研究[J].航空发动机,1999(3):15-24. SHAO Wanren,WU Shousheng.Preliminary experimentstudy on chrysanthemum-shaped mixer in turbofan engine[J].Aeroengine,1999(3):15-24.(in Chinese)
    [10]
    康冠群,王强.分开式与混合式排气喷管气动特性对比研究[J].航空发动机,2013,39(6):24-30. KANG Guanqun,WANG Qiang.Comparison investigation on aerodynamic characteristics of separate-flow and mixed-flow exhaust nozzles[J].Aeroengine,2013,39(6):24-30.(in Chinese)
    [11]
    张靖周,李立国,高潮,等.波瓣喷管红外抑制系统的实验研究[J].航空动力学报,1997,12(2):212-224. ZHANG Jingzhou,LI Liguo,GAO Chao,et al.An experiment study on a lobed nozzle of an infrared suppression system[J].Journal of Aerospace Power,1997,12(2):212-224.(in Chinese)
    [12]
    张靖周,单勇,李立国.直升机排气系统用波瓣喷管隐射-混合式红外抑制器研究[J].航空学报,2007,28(1):32-36. ZHANG Jingzhou,SHAN Yong,LI Liguo.Investigation on lobed nozzle mixer-ejector infrared suppressor for helicopter exhaust system[J].Acta Aeronautica et Astronautica Sinica,2007,28(1):32-36.(in Chinese)
    [13]
    单勇,张靖周,李立国.直升机红外抑制器红外辐射特性的数值研究和实验验证[J].红外与毫米波学报,2006,25(2):95-100. SHAN Yong,ZHANG Jingzhou,LI Liguo.Numerical calculation and experimental verification for the infrared radiation characteristics of helicopter infrared radiation suppressor[J].Journal of Infrared and Millim Waves,2006,25(2):95-100.(in Chinese)
    [14]
    陶文铨.数值传热学[M].2版.西安:西安交通大学出版社,2001.
    [15]
    胡娅萍,吉洪湖,白涛涛.湍流模型对发动机排气系统流场和红外辐射特征计算的影响[J].航空动力学报,2012,27(11):2414-2420. HU Yaping,JI Honghu,BAI Taotao.Effect of turbulence models on numerical simulation of flow and infrared radiation characteristics of aero-engine exhaust system[J].Journal of Aerospace Power,2012,27(11):2414-2420.(in Chinese)
    [16]
    黄伟,吉洪湖.加力式涡扇发动机非加力状态部件红外辐射分析[J].航空动力学报,2011,26(1):48-53. HUANG Wei,JI Honghu.Analysis of components infrared radiation of afterburning turbofan engine under non-afterburning condition[J].Journal of Aerospace Power,2011,26(1):48-53.(in Chinese)
    [17]
    谈和平,夏新林,刘林华,等.红外辐射特性与传输的数值计算[M].哈尔滨:哈尔滨工业大学出版社,2006.
    [18]
    徐南荣,卞南华.红外辐射与制导[M].北京:国防工业出版社,1997.
    [19]
    劳埃德.热成像系统[M].北京:国防工业出版社,1981.
    • 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(1127.0KB)
    XML

    Article Metrics

    Article views (1082) PDF downloads(734) 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