一种双S形二元排气系统红外特性的模型实验

王丁; 吉洪湖; 卢浩浩; 王浩

doi:10.13224/j.cnki.jasp.2017.12.020

一种双S形二元排气系统红外特性的模型实验

doi: 10.13224/j.cnki.jasp.2017.12.020

南京航空航天大学能源与动力学院,南京 210016

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出版历程
- 收稿日期: 2016-05-29
- 刊出日期: 2017-12-28

Experiment on infrared signature of a model of serpentine twodimensional exhaust system

摘要

摘要: 通过模型实验测量了一种双S形二元(2-D)喷管排气系统壁面压力和温度分布,以及分别在侧向、下方和上方探测面上的红外辐射强度分布,并与基准轴对称排气系统作了对比分析。实验结果表明:双S形二元喷管排气系统在上方探测面上,红外辐射强度比较大,最大值出现在10°探测角；相比基准轴对称排气系统,双S形二元排气喷管系统红外辐射强度在0°探测角方位平均降低了75.5%,在侧向、下方及上方探测面上90°探测角方位分别降低了57.6%、50.9%和17.3%。
- 排气系统 /
- 双S形二元喷管 /
- 红外辐射 /
- 红外抑制 /
- 模型实验
Abstract: The pressure and temperature distributions on the surface of a model of serpentine twodimensional（2D）nozzle exhaust system were measured, and its infrared radiation(IR) intensity on the side, lower and upper detection planes were also measured; these results were compared with those of a relevant axisymmetric exhaust system. The results showed that, the radiation intensity of serpentine 2D nozzle exhaust system on the upper detection plane was much higher than that on other two planes, with the maximum value at angle 10°; compared with axisymmetric exhaust system, the radiation intensity of serpentine 2-D nozzle exhaust system reduced by 75.5% at angle 0°, and 57.6%, 50.9% and 17.3% at angle 90° respectively on the side, lower and upper detection planes.
- exhaust system /
- serpentine twodimensional (2-D) nozzle /
- infrared radiation /
- infrared suppression /
- model experiment

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参考文献(22)

[1]	刘永昌,朱虹.红外寻的制导的发展现状与新趋势［J］.红外技术,1999,21(4):7-12.LIU Yongchang,ZHU Hong.The development and new trend of IR seeking guidance techniques［J］.Infrared Technology,1999,21(4):7-12.(in Chinese)
[2]	《航空发动机手册》编委会.航空发动机手册:第7分册进排气装置［M］.北京:航空工业出版社,2002.
[3]	金捷,朱谷君,徐南荣,等.发动机高速排气系统红外辐射特性的数值计算与分析［J］.航空动力学报,2002,12(5):582-585.JIN Jie,ZHU Gujun,XU Nanrong,et al.Numerical simulation of infrared radiation characteristics for aero engine highspeed exhaust system［J］.Journal of Aerospace Power,2002,17(5):583-585.(in Chinese)
[4]	HILEY P E,WALLACE H W.Study of nonaxisymmetric nozzles installed in advanced fighter aircraft［R］.AIAA 75-1316,1975.
[5]	STEVENS H L.F15/Nonaxisymmetric nozzle system integration study support program［R］.NASA-CR-135252,1978.
[6]	BANKEN G J,CORNETTE W M,GLEASON K M.Investigation of infrared characteristics of three generic nozzle concepts［R］.AIAA 80-0160,1980.
[7]	CHU C W,DER J J,WUN W.A simple 2Dnozzle plume model for IR analysis［R］.AIAA 80-1808,1980.
[8]	PRESZ W M,NELSON C B.Gas turbine exhaust cooling concepts［R］.AIAA 94-3083,1994.
[9]	BABBITT R R,COHN J A,FLEMING K J.Advanced high bypass mixedflow exhaust system design study［R］.AIAA 91-2242,1991.
[10]	胡传炘.隐身涂层技术［M］.北京:化学工业出版社,2004.
[11]	李娜,吉洪湖,黄伟,等.混合排气二元收敛喷管气动与红外隐身综合设计方法［J］.航空动力学报,2011,26(11):2563-2570.LI Na,JI Honghu,HUANG Wei,et al.Comprehensive design of aerodynamic and infrared stealth of 2D convergent nozzle with mixed flow［J］.Journal of Aerospace Power,2011,26（11）:2563-2570.(in Chinese)
[12]	刘常春,吉洪湖,黄伟,等.一种双S形二元喷管的红外辐射特性数值研究［J］.航空动力学报,2013,28(7):1482-1488.LIU Changchun,JI Honghu,HUANG Wei,et al.Numerical simulation on infrared radiation characteristics of serpentine 2D nozzle［J］.Journal of Aerospace Power,2013,28(7):1482-1488.(in Chinese)
[13]	BRUNET E,SEINE N S,DARIS T,et al.Exhaust assembly forming a horizontal propulsion gas elbow in an aircraft:US007784284B2［P］.2010-08-31.
[14]	刘常春,吉洪湖,李娜,等.一种二元S形喷管的红外辐射特性数值研究［J］.工程热物理学报,2010,31(9):1567-1570.LIU Changchun,JI Honghu,LI Na,et al.Numerical simulation on infrared radiant characteristics of 2D S??????????椮湊??桲楮湡敬猠敯? Engineering Thermophysics, 2010,31(9):1567-1570.(in Chinese)
[15]	章叶川,王占学,史经纬,等.双S形喷管流动及红外特性分析［J］.航空动力学报,2013,28(11):2468-2474.ZHANG Yechuan,WANG Zhanxue,SHI Jingwei,et al.Analysis on flow and infrared radiation characteristics of double Snozzle［J］.Journal of Aerospace Power,2013,28(11):2468-2474.(in Chinese)
[16]	卫永斌,艾俊强.并列双发三维非对称多S弯喷管参数化设计方法［J］.航空动力学报,2015,30(2):271-280.WEI Yongbin,AI Junqiang.Parameter design method of double juxtaposition 3D asymmetric severalSshaped nozzles［J］.Journal of Aerospace Power,2015,30(2):271-280.(in Chinese)
[17]	孙啸林,王占学,周莉,等.基于多参数耦合的S弯隐身喷管设计方法研究［J］.工程热物理学报,2015,36(11):2371-2375.SUN Xiaolin,WANG Zhanxue,ZHOU Li,et al.The design method of serpentine stealth nozzles based on coupled parameters［J］.Journal of Engineering Thermophysics,2015,36(11):2371-2375.(in Chinese)
[18]	丁娟,杨青真,李翔,等.不同出口型式S型喷管红外辐射特性研究［J］.科学技术与工程,2014,14(7):273-276.DING Juan,YANG Qingzhen,LI Xiang,et al.Research on the infrared radiation characteristic of Sshaped nozzles with different outlet［J］.Science Technology and Engineering,2014,14(7):273-276.(in Chinese)
[19]	SULLIVAN K M.Numerical investigation of Sduct geometric effects on inlet performance using sequential design of experiments［D］.Kaduna:Air Force Institute of Technology,2009.
[20]	李荣松,王强,额日其太.尾缘修形的二元喷管内外流场数值研究［J］.航空动力学报,2005,20(3):389-393.LI Rongsong,WANG Qiang,Eriqitai.Numerical investigation of twodimensional nozzle with trailing edge modification［J］.Journal of Aerospace Power,2005,20(3):389-393.(in Chinese)
[21]	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.Computationalinvestigation of infrared radiation characteristics of exhaust system based on BRDF［J］.Acta Aeronautica et Astronautica Sinica,2012,33(7):1227-1235.(in Chinese)
[22]	罗明东,吉洪湖,黄伟,等.用FTIR光谱仪测量排气系统中红外光谱辐射强度的方法［J］.航空动力学报,2007,22(9):1423-1429.LUO Mingdong,JI Honghu,HUANG Wei,et al.Research on measurement method of midIR spectral radiant intensity of exhaust system with FTIR spectrometer［J］.Journal of Aerospace Power,2007,22(9):1