Numerical investigation of influence of two-dimensional convergent and divergent nozzle’s design parameters on infrared characteristics
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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。Abstract: The computational cases of infrared radiation (IR) characteristics of exhaust system were designed using the orthogonal experiment design method. The influences of geometric parameters on IR characteristics of two-dimensional exhaust system were investigated. The geometric parameters studied included throat width to height ratio, throat radius ratio, convergent half angle and divergent half angle of two-dimensional convergent and divergent (2D-CD) nozzle. The sensitivity analysis of the four geometric parameters was performed. Results showed that the divergent half angle was the widest parameter that influenced the spatial range of IR characteristics of 2D exhaust system. The convergent half angle mainly influenced IR characteristics within the range of 10°-30° in the tail direction. The throat width to height ratio mainly influenced the IR characteristics of 0° in the positive tail direction and 90° in the lateral direction. The throat radius ratio had little influence on the IR characteristics. The main influence parameters of IR characteristics in different directions of 2D exhaust system were different. The most important influence parameter in the direction of 0° was throat width to height ratio. The most important influence parameters in the direction of 90° were divergent half angle and throat width to height ratio.
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[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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