二元俯仰矢量喷管排气系统红外特征模拟实验

卢浩浩; 吉洪湖; 刘健; 王丁; 王浩; 周兵

doi:10.13224/j.cnki.jasp.2017.08.010

二元俯仰矢量喷管排气系统红外特征模拟实验

doi: 10.13224/j.cnki.jasp.2017.08.010

南京航空航天大学能源与动力学院，南京 210016

计量
- 文章访问数: 1184
- HTML浏览量: 3
- PDF量: 812
- 被引次数: 0
出版历程
- 收稿日期: 2016-06-28
- 刊出日期: 2017-08-28

Experiment on infrared signature of two dimensional convergent-divergent vectoring nozzle exhaust system

摘要

摘要: 实验研究了二元俯仰矢量喷管排气系统在几何偏转角0°，10°，20°三种状态下的壁面温度分布与红外辐射特征，并与基准轴对称喷管排气系统进行了对比分析。结果表明：二元俯仰矢量喷管排气系统的红外辐射特征相对基准轴对称喷管排气系统有明显下降，正尾向降幅约10%；随着几何偏转角的增加，隔热屏与收敛段的温度逐渐上升,偏转段压力侧壁面温度略有上升，吸力侧壁面温度略有下降，最大变化幅值30K；排气系统红外辐射强度随偏转角增大而增大，尾向15°~45°和-15°~-60°范围内增幅明显，最大增幅可达70%。
- 排气系统 /
- 二元俯仰喷管 /
- 矢量偏转 /
- 红外辐射 /
- 轴对称喷管排气系统
Abstract: Experiments was conducted to study the distribution of wall temperature and infrared radiation characteristics on two dimensional convergent-divergent (2D-CD) vectoring nozzle exhaust system in three geometric deflection states, deflection of 0, 10, 20 degrees, and the results were compared with the reference axisymmetric nozzle exhaust system. The experimental results show that the infrared radiation characteristics is significantly lower than the reference axisymmetric nozzle exhaust system with a decline of 10% in the tail direction. With the increase of geometric deflection angle, the temperature of heat shield wall, convergent section wall increase, and the temperature of pressure side wall in deflection section increase slightly, while the temperature of suction side wall in deflection section decrease slightly, where the maximum change value is 30K; the increasing angle also significantly enhances the infrared radiation intensity, especially, in the tail direction from 15° to 45° and from -15° to -60°, where the maximum increase reaches 70%.
- exhaust system /
- 2D-CD nozzle /
- vector deflection /
- infrared radiation /
- axisymmetric nozzle exhaust system

HTML

参考文献(18)

[1]	桑建华.飞行器隐身技术［M］.北京:航空工业出版社,2013.
[2]	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［J］.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)
[3]	郑礼宝,张靖周.矢量二元收扩喷管热射流复杂流场特征研究［J］.流体力学实验与测量,2000,14(2):26-30.ZHENG Libao,ZHANG Jinzhou.Investigation of hot-jet characteristics of 2D-CD vectoring nozzles［J］.Experiments and Measurements in Fluid Mechanics,2000,14(2):26-30.(in Chinese)
[4]	宁怀松,张志学,邵万仁,等.二元收扩喷管气动方案优化设计［J］.航空发动机,2014,40(3):52-55.NING Huaisong,ZHANG Zhixue,SHAO Wangren,et al.Internal performance optimization of 2D-CD nozzle［J］.Aeroengine,2014,40(3):52-55.(in Chinese)
[5]	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（4）:8-13.
[6]	任超奇,王强,胡海洋.收扩喷管与飞行器的一体化气动优化设计［J］.航空动力学报,2014,29(10):2294-2302.REN Chaoqi,WANG Qiang,HU Haiyang.Integrated aerodynamic optimization design of convergent-divergent nozzle and vehicle afterbody［J］.Journal of Aerospace Power,2014,29(10):2294-2302.(in Chinese)
[7]	杨弘炜,李椿萱.不同矢量角偏转下二元喷管内流特性的数值研究［J］.航空动力学报,1995,10(3):217-220.YONG Hongwei,LI Chunxuan.Numerical simulation of internal flow in 2-D nozzles with thrust vectoring［J］.Journal of Aerospace Power,1995,10(3):217-220.(in Chinese)
[8]	RE R J,LEAVITT L D.Static internal performance including thrust vectoring and reversing of two-dimensional convergent-divergent nozzles［R］.NASA TP 2253,1984.
[9]	陈玲玲,杨青真,李岳峰.推力矢量喷管设计与启动特性分析研究［J］.科学技术与工程,2012,12(6):1304-1307.CHEN Lingling,YANG Qingzhen,LI Yuefeng.Aerodynamic design and analysis of thrust vectoring nozzles［J］.Science Technology and Engineering,2012,12(6):1304-1307.(in Chinese)
[10]	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)
[11]	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)
[12]	王殿磊.二元收扩喷管几何参数对气动与红外隐身特性影响数值研究［D］.南京:南京航空航天大学,2012.WANG Dianlei.Numerical study of the impacts of geometry parameters of convergent-divergent nozzle with circle to rectangular transition on flow and infrared stealth characteristics［D］.Nanjing:Nanjing University of Aeronautics and Astronautics,2012.(in Chinese)
[13]	BERRIER B L,RE R J.Effects of several geometric parameters on the static internal performance of three non-axisymmetric nozzle concepts［R］.NASA TP-1468,1979.
[14]	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)
[15]	陈俊,吉洪湖,斯仁,等.采用低发射率涂层的发动机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)
[16]	宫禹.涡扇发动机排气系统红外隐身实验装置的总体设计与性能仿真研究［D］.南京:南京航空航天大学,2007.GONG Yu.Design and performance simulation of an experimental rig for infrared stealth research of exhaust system of a turbofan engine［D］.Nanjing:Nanjing University of Aeronautics and Astronautics,2007.(in Chinese)
[17]	罗明东,吉洪湖,黄伟,等.非加力涡扇发动机二元喷管红外辐射特性实验研究［J］.航空动力学报,2006,21(4):631-636.LUO Mingdong,JI Honghu,HUANG Wei,et al.Numerical evaluation on infrared radiant intensity of exhaust system of turbine engine without afterburning［J］.Journal of Aerospace Power,2006,21(4):631-636.(in Chinese)
[18]	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):1423-1429.(in Chinese)