冷却抑制二元收扩喷管红外特征的模型实验与数值研究

推进技术 ›› 2014, Vol. 35 ›› Issue (4): 463-469.

冷却抑制二元收扩喷管红外特征的模型实验与数值研究

斯仁,吉洪湖,刘常春,黄伟,卢浩浩

南京航空航天大学能源与动力学院,江苏南京 210016;南京航空航天大学能源与动力学院,江苏南京 210016;南京航空航天大学能源与动力学院,江苏南京 210016;南京航空航天大学能源与动力学院,江苏南京 210016;南京航空航天大学能源与动力学院,江苏南京 210016

发布日期:2021-08-15
作者简介:斯仁(1984—),男,博士生,研究领域为飞行器红外隐身技术。E-mail:sbo_nuaa@qq.com

Model Experiment and Numerical Analysis on Infrared Character and Infrared Suppression by Cooling of Two-Dimensional Convergent-Divergent Nozzle

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

Published:2021-08-15

摘要/Abstract

摘要： 为研究二元收扩喷管排气系统的红外特征及其采取冷却措施后的红外抑制效果,设计了带有冷却结构的喷管实验模型,测量了3组实验状态下的喷管壁面温度和红外辐射强度分布,分析了喷管腔体内各部件的辐射贡献大小。研究结果表明:二元收扩喷管排气系统的积分辐射强度在0°方向上最大,并且随着角度的增大而减小；扩张板的壁面温度下降21.1%,侧壁的壁面温度下降26.6%,可使积分辐射强度降低11.5%～31.9%；在扩张段冷却的基础上,中心锥的壁面温度下降9%,可使积分辐射强度降低21.7%～38.9%。 

关键词: 二元收扩喷管;红外特征;冷却;红外抑制 

Abstract: To study the infrared character and infrared suppression by cooling of the two-dimensional convergent-divergent nozzle exhaust system, the experimental model of nozzle with cooling structure was designed, the distribution of wall temperature and infrared radiation intensity of three kinds of experimental states were measured,and the infrared radiation of nozzle internal components were analyzed. The results show that, the integral radiation intensity of two- dimensional convergent-divergent nozzle exhaust system decreases with the angle and its maximum value is located at 0°. When the wall temperature of divergent flap is reduced by 21.1% and side wall is reduced by 26.6%, the integral radiation intensity can decrease by 11.5%~31.9%. When the wall temperature of cone is reduced by 9% on the basis of cooling the divergent section, the integral radiation intensity can decrease by 21.7%～38.9%.

Key words: Two-dimensional convergent-divergent nozzle; Infrared character; Cooling; Infrared suppression

斯仁,吉洪湖,刘常春,黄伟,卢浩浩. 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 Hong-hu, LIU Chang-chun, HUANG Wei, LU Hao-hao. 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.

参考文献

[1] 张勃, 吉洪湖.大宽高比矩形喷管的射流与外流的掺混特性的数值研究[J].航空动力学报,2004,9(2):104-110.
[2] 张勃, 吉洪湖, 罗明东, 等.宽高比对尾向可见明火矩形喷管红外抑制特性影响研究[J].航空动力学报,2007,2(11):1820-1825.
[3] Stevens H L, Thayer E B, Fullerton J F.Development of the Multi-Function 2-D/C-D Nozzle[R].AIAA 81-1491.
[4] Goetz G F, Young J H, Palcza J L.A Two-Dimensional Airframe Integrated Nozzle Design With Inflight Thrust Vectoring and Reversing Capabilities for Advanced Fighter Aircraft[R].AIAA 76-626.
[5] Hiley P E, Wallace H W, Booz D E.Study of Non-Axisymmetric Nozzles Installed in Advanced Fighter Aircraft[R].AIAA 75-1316.
[6] Stevens H I.F-15/Non-Axisymmetric Nozzle System Integration Study Support Program Contractor Report[R].NASA-CR-135252.
[7] 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,2002,7(1).
[8] 黄伟, 吉洪湖.加力式涡扇发动机非加力状态部件红外辐射分析[J].航空动力学报,2011,6(01).
[9] 张勃, 吉洪湖, 张宗斌, 等.中心锥冷却对喷管腔体红外辐射的抑制作用数值分析[J].航空动力学报,2012,7(3).
[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,2012,7(11).
[11] Kim J H, Samimy M, Erskine W R.Mixing Enhancement with Minimal Thrust Loss in a High Speed Rectangular Jet[R].AIAA 98-696.
[12] Yetter J A, Leavitt L D.Effects of Sidewall Geometry on the Installed Performance of NonAxisymmetric Convergent-Divergent Exhaust Nozzles[R].NASA-TP-1771c1.
[13] 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, 2007,2(09).
[14] 罗明东, 吉洪湖, 黄伟, 等.无加力高涵道比涡扇发动机二元喷管的红外辐射特性实验研究[J].航空动力学报,2006,1(4):631-636.
[15] 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,2010,1(6).(HUANG Wei, JI Hong-hu, SI Ren, et al.Infrared Characteristics Calculating of Turbofan Engine Exhaust System[J].Journal of Propulsion Technology, 2010,1(6).)