Volume 35 Issue 10
Oct.  2020
Turn off MathJax
Article Contents
Article Navigation >  Journal of Aerospace Power  > 2020  >  35(10): 2078-2088
WANG Hao, JI Honghu, SANG Xueyi. Effects of fully shielded guiding strut on infrared signatures of exhaust system[J]. Journal of Aerospace Power, 2020, 35(10): 2078-2088. doi: 10.13224/j.cnki.jasp.2020.10.007
Citation: WANG Hao, JI Honghu, SANG Xueyi. Effects of fully shielded guiding strut on infrared signatures of exhaust system[J]. Journal of Aerospace Power, 2020, 35(10): 2078-2088. doi: 10.13224/j.cnki.jasp.2020.10.007
shu

Effects of fully shielded guiding strut on infrared signatures of exhaust system

doi: 10.13224/j.cnki.jasp.2020.10.007
  • 1.

    College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China

  • 2.

    Shanghai Aerospace Control Technology Institute,China Aerospace Science and Technology Corporation,Shanghai 201108,China

  • Received Date: 2020-04-02
  • Publish Date: 2020-10-28
    Abstract
  • In order to suppress the contribution of the last-stage turbine rotor to the infrared (IR) radiation in backward of the exhaust system, the fully shielded guiding strut (FSGS) was designed. IR signatures of the baseline axisymmetric exhaust system and the exhaust system with FSGS under different cooling conditions were obtained by experiments. The results indicated that the wall temperature of the FSGS was lower than that of the last-stage turbine rotor. However, the wall temperatures of the heat shield and nozzle of the exhaust system with the FSGS increased. FSGS had an outstanding effect on suppressing the IR radiation of the exhaust system within the directions of 0° ~ 10°, and its IR radiation intensity was 13.9% lower than that of the baseline axisymmetric exhaust system at 0° detection angle. The application of film cooling on the FSGS can further reduce the IR radiation of the exhaust system in those directions mentioned above. Under the blowing ratios (BR) of 0.5, 0.7 and 0.9, the IR radiation intensity of the exhaust system at 0° detection angle was weakened by 18.1%, 25.8% and 34.5%, respectively. Therefore, the FSGS with film cooling is a very effective way to suppress the IR contribution of the last-stage turbine to the exhaust system.

     

    • FullText(HTML)
  • loading
    • References(19)
  • [1]
    桑建华.飞行器隐身技术［M］.北京:航空工业出版社,2013.
    [2]
    吉洪湖.飞发一体化设计中的发动机隐身问题［J］.航空动力,2018(2):67-71. JI Honghu.Fundamental issues of aircraft/engine integration for low observability［J］.Aerospace Power,2018(2):67-71.(in Chinese)
    [3]
    卢浩浩,吉洪湖,刘健,等.二元俯仰矢量喷管排气系统红外特征模拟实验［J］.航空动力学报,2017,32(8):1861-1868. LU Haohao,JI Honghu,LIU Jian,et al.Experiment on infrared signature of two dimensional convergent-divergent vectoring nozzle exhaust system［J］.Journal of Aerospace Power,2017,32(8):1861-1868.(in Chinese)
    [4]
    WANG Hao,JI Honghu,LU Haohao.The influence of nozzle deflection on fluid dynamic and infrared characteristics of a two-dimensional convergent-divergent vectoring exhaust system［J］.Proceedings of the Institution of Mechanical Engineers,2019,233(12):4646-4662.(in Chinese)
    [5]
    施小娟,吉洪湖.二元收扩喷管设计参数对红外特征影响的数值研究［J］.航空动力学报,2020,35(5):944-955. SHI Xiaojuan,JI Honghu.Numerical investigation of influence of two-dimensional convergent and divergent nozzle’s design parameters on infrared characteristics［J］.Journal of Aerospace Power,2020,35(5):944-955.(in Chinese)
    [6]
    范仁钰,张靖周,单勇.遮挡板结构对二元喷管红外辐射特性的影响［J］.航空动力学报,2011,26(2):343-348. FANG Renyu,ZHANG Jingzhou,SHAN Yong.Effects of sheltering baffles on the infrared radiation characteristics of two-dimensional nozzles［J］.Journal of Aerospace Power,2011,26(2):343-348.(in Chinese)
    [7]
    刘常春,吉洪湖.S弯二元喷管红外辐射特性实验［J］.航空动力学报,2019,34(7):1493-1500. LIU Changchun,JI Honghu.Experiment on infrared radiation characteristics of S shaped 2D nozzle［J］.Journal of Aerospace Power,2019,34(7):1493-1500.(in Chinese)
    [8]
    张靖周,王旭,单勇.塞锥后体气膜冷却对轴对称塞式喷管红外辐射和气动性能的影响［J］.航空学报,2015,36(8):2601-2608. ZHANG Jingzhou,WANG Xu,SHAN Yong.Effects of plug rear-body film cooling on infrared radiation and aerodynamics performance of axisymmetric plug nozzle［J］.Journal of Aeronautics,2015,36(8):2601-2608.(in Chinese)
    [9]
    周兵,吉洪湖.塞锥气膜冷却对二元塞式喷管红外特征的影响［J］.航空动力学报,2016,31(12):2895-2903. ZHOU Bing,JI Honghu.Effect of wedge film cooling on the infrared signature of two-dimensional wedge nozzle［J］.Journal of Aerospace Power,2016,31(12):2895-2903.(in Chinese)
    [10]
    陈俊,吉洪湖.二元塞式喷管红外特征及壁面降温的红外抑制效果计算［J］.航空动力学报,2012,27(11):2429-2435. CHEN Jun,JI Honghu.Numerical simulation of the infrared radiation characteristics and infrared restraining effect of lower wall temperature for two-dimensional plug nozzle［J］.Journal of Aerospace Power,2012,27(11):2429-2435.(in Chinese)
    [11]
    HILEY P E,WALLACET H W,BOOZ D E.Nonaxisymmetric nozzles installed in advanced fighter aircraft［J］.Journal of Aircraft,1976,13(12):1000-1006.
    [12]
    单勇,张靖周,邵万仁,等.涡扇发动机排气系统中心锥气膜冷却结构的气动和红外辐射特性实验［J］.航空动力学报,2012,27(1):9-15. SHAN Yong,ZHANG Jingzhou,SHAO Wanren,et al.Experiments on aerodynamic and infrared radiation characteristics of film-cooling center-body exhaust system for a turbofan engine［J］.Journal of Aerospace Power,2012,27(1):9-15.(in Chinese)
    [13]
    LIU Jian,JI Honghu.Investigation on infrared signature of axisymmetric vectoring exhaust system with infrared suppressions［J］.Journal of Thermophysics and Heat Transfer,2018,32(3):627-636.
    [14]
    刘福城,吉洪湖,斯仁,等.短套管二元引射喷管设计及气动与红外特性数值研究［J］.红外技术,2013,35(10):623-628,664. LIU Fucheng,JI Honghu,SI Ren,et al.Numerical simulation of two-dimensional ejector nozzle with short shroud［J］.Infrared Technology,2013,35(10):623-628,664.(in Chinese)
    [15]
    李经警.横向射流入射对喷管尾喷流红外辐射及掺混特性的影响研究［D］.南京:南京航空航天大学,2018. LI Jingjing.The infrared radiation and mixing enhancement characteristics of nozzle plumes influenced by cross-flow［D］.Nanjing:Nanjing University of Aeronautics and Astronautics,2018.(in Chinese)
    [16]
    陈俊,吉洪湖,斯仁,等.采用低发射率涂层的发动排气系统红外特征实验［J］.红外技术,2011,33(7):395-400. CHEN Jun,JI Honghu,SI Ren,et al.Experiment of IR suppression for nozzle with low infrared emissivity coating［J］.Infrared Technology,2011,33(7):395-400.(in Chinese)
    [17]
    LIU Jian,JI Honghu.Experimental investigation on infrared signatures of axisymmetric vectoring exhaust nozzle with film cooling and low-emissivity coating［J］.Journal of Engineering for Gas Turbines and Power,2018,140(9):091203.1-091203.11.
    [18]
    ZHANG J M,WANG C F,LUM K Y.Multidisciplinary design of S-shaped intake［R］.AIAA 2008-7060,2008.
    [19]
    李娜.混合排气二元收敛喷管气动与红外隐身综合设计方法研究［D］.南京:南京航空航天大学,2010.
    • 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(5046.0KB)
    XML

    Article Metrics

    Article views (448) PDF downloads(350) 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