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二元收扩喷管设计参数对红外特征影响的数值研究

施小娟 吉洪湖

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. doi: 10.13224/j.cnki.jasp.2020.05.006
引用本文: 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. doi: 10.13224/j.cnki.jasp.2020.05.006
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. doi: 10.13224/j.cnki.jasp.2020.05.006
Citation: 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. doi: 10.13224/j.cnki.jasp.2020.05.006

二元收扩喷管设计参数对红外特征影响的数值研究

doi: 10.13224/j.cnki.jasp.2020.05.006

Numerical investigation of influence of two-dimensional convergent and divergent nozzle’s design parameters on infrared characteristics

  • 摘要: 采用正交试验设计方法进行排气系统红外辐射(IR)特征数值模拟算例的设计,研究了二元收扩喷管(2D-CD)喉部宽高比、喉部型面半径比、收敛半角和扩张半角等参数对排气系统红外辐射特征的影响,并且开展了参数对排气系统红外辐射特征影响灵敏度的分析。结果表明:扩张半角是影响二元排气系统红外辐射特征空间范围最宽的参数,收敛半角主要影响尾向10°~30°范围的红外辐射特征,喉部宽高比主要影响正尾向0°和侧向90°的红外辐射特征,喉部型面半径比对红外辐射特征的影响较小;二元排气系统不同方向上红外辐射特征的最主要影响参数不同,正尾向0°方向上的最主要影响参数是喉部宽高比,侧向90°方向上的最主要影响参数按影响程度大小排序依次为扩张半角、喉部宽高比。

     

  • [1] CAPONE F J.The nonaxisymmetric nozzle:it is for real[R].AIAA 79-1810,1979.
    [2] 季鹤鸣,雷雨冰,邵万仁.二元收扩喷管的方案设计与试验研究[J].航空发动机,1995,21(4):8-13. JI Heming,LEI Yubing,SHAO Wanren.Concept design and experimental study of the 2D-CD nozzle[J].Aeroengine,1995,21(4):8-13.(in Chinese)
    [3] 廉筱纯,吴虎.航空发动机原理[M].西安:西北工业大学出版社,2005.
    [4] 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)
    [5] 邓洪伟,金文栋,叶留增,等.二元矢量喷管内外流场数值计算与隐身性分析[J].航空科学技术,2012(1):45-48. DENG Hongwei,JIN Wendong,YE Liuzeng,et al.Numerical simulation of two-dimensional nozzle and analysis of its stealth technology[J].Aeronautical Science and Technology,2012(1):45-48.(in Chinese)
    [6] CLINE J,BEHM D,KIDD K,et al.F/A-22 IR signature flight test model validation[J].Aircraft Survivability,2003,3:9-11.
    [7] PATERSON J.Overview of low observable technology and its effects on combat aircraft survivability[J].Journal of Aircraft,1999,36(2):380-388.
    [8] DECHOR R.Infrared emission from turbofans with high aspect ratio nozzles[R].AIAA 81-4319,1981.
    [9] STEVENS H L.F-15/nonaxisymmetric nozzle system integration study support program[R].NASA CR-135252,1978.
    [10] 斯仁,吉洪湖,刘常春,等.冷却抑制二元收扩喷管红外特征的模型实验与数值研究[J].推进技术,2014,35(4):463-469. SI Ren,JI Honghu,LIU Changchun,et al.Model experiment and numerical analysis on infrared character and infrared suppression by cooling of two-dimensional convergent-divergent nozzle[J].Journal of Propulsion Technology,2014,35(4):463-469.(in Chinese)
    [11] 卢浩浩,吉洪湖,刘健,等.二元俯仰矢量排气系统红外特征模拟实验研究[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)
    [12] 卢浩浩,吉洪湖,王丁,等.部件冷却对二元俯仰矢量排气系统红外特征抑制实验[J].航空动力学报,2017,32(9):2070-2079. LU Haohao,JI Honghu,WANG Ding,et al.Experiment on infrared characteristics suppression by component cooling of two-dimensional convergent-divergent vectoring nozzle exhaust system[J].Journal of Aerospace Power,2017,32(9):2070-2079.(in Chinese)
    [13] 卢浩浩,吉洪湖,刘健,等.涵道比对二元俯仰矢量排气系统红外特征影响的实验研究[J].红外技术,2017,39(7):648-652. LU Haohao,JI Honghu,LIU Jian,et al.Experiment investigation of infrared radiation characteristics of two-dimensional convergent-divergent vectoring nozzle exhaust system on different bypass ratio states[J].Infrared Technology,2017,39(7):648-652.(in Chinese)
    [14] 王杏涛.飞行器红外辐射特征及发动机舱蒙皮降温规律研究[D].南京:南京航空航天大学,2015. WANG Xingtao.Research on infrared radiation performance of air vehicle and temperature reduction disciplinarian of engine nacelle skin[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2015.(in Chinese)
    [15] 额日其太,王志杰,吴寿生.高速热喷流条件下二元收扩喷管扩张段壁面冷却的初步试验研究.航空动力学报,2002,17(1):40-44. Eriqitai,WANG Zhijie,WU Shousheng.Preliminary experimental investigation on the divergent wall cooling of two dimensional C-D nozzles at high speed and hot jet conditions[J].Journal of Aerospace Power,2002,17(1):40-44.(in Chinese)
    [16] 施小娟,吉洪湖,斯仁.二元收扩喷管设计参数对气动性能影响的数值研究[J].航空动力学报,2016,31(8):1799-1810. SHI Xiaojuan,JI Honghu,SI Ren.Numerical investigation of geometric parameters’ influence to aerodynamic performance of two dimensional convergent and divergent nozzle[J].Journal of Aerospace Power,2016,31(8):1799-1810.(in Chinese)
    [17] 邱轶兵,张文利,闵凡飞,等.试验设计与数据处理[M].合肥:中国科学技术大学出版社,2008.
    [18] 施小娟.涡扇发动机收敛喷管红外辐射特征及引射抑制技术研究[D].南京:南京航空航天大学,2007. SHI Xiaojuan.Investigation of infrared radiation characteristic of convergent nozzle in turbofan engine and ejector’s suppressing technology[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2007.(in Chinese)
    [19] 黄伟,吉洪湖.基于BRDF的排气系统红外辐射特征计算研究[J].航空学报,2012,33(7):1227-1235. HUANG Wei,JI Honghu.Computational investigation of infrared radiation characteristics of exhaust system based on BRDF[J].Acta Aeronautica et Astronautica Sinica,2012,33(7):1227-1235.(in Chinese)
    [20] 黄伟,吉洪湖,斯仁,等.涡扇发动机排气系统红外特征[J].推进技术,2010,31(6):745-750. HUANG Wei,JI Honghu,SI Ren,et al.Infrared characteristics calculating of turbofan engine exhaust system[J].Journal of Propulsion Technology,2010,31(6):745-750.(in Chinese)
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出版历程
  • 收稿日期:  2019-12-02
  • 刊出日期:  2020-05-28

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