中心锥冷却对喷管腔体红外辐射的抑制作用数值分析

张勃; 吉洪湖; 张宗斌; 罗明东; 林兰之

中心锥冷却对喷管腔体红外辐射的抑制作用数值分析

1.
南京航空航天大学能源与动力学院, 南京 210016
2.
成都飞机设计研究所总体设计部, 成都 610041

计量
- 文章访问数: 1638
- HTML浏览量: 89
- PDF量: 549
- 被引次数: 0
出版历程
- 收稿日期: 2011-04-19
- 修回日期: 2011-08-29
- 刊出日期: 2012-03-28

Numerical investigation of thermal radiation characteristics of nozzle cavities with center cone cooled

1.
College of Power and Energy, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
2.
System Engineering Department, Chengdu Institute of Aircraft Designing, Chengdou 610041, China

摘要

摘要: 航空发动机高温部件是发动机3~5μm上的重要红外辐射之一,对高温部件之一的中心锥的红外抑制技术进行了数值研究.在中心锥前端布置气膜缝槽,缝槽几何参数经过优化设计,将部分外涵低温气流经过支板引入中心锥,对支板和锥体壁面形成冲击冷却,在锥体前端形成气膜覆盖,使得支板与中心锥壁面得到了有效冷却,两者平均温度分别降低21.1%和46.2%,冷却气量约为外涵流量的1.6%.喷管腔体3~5μm波段上红外辐射得到有效抑制,喷管正后方红外辐射相比原型喷管降低30%,0°~45°范围内红外辐射则明显降低.
- 红外抑制 /
- 喷管腔体 /
- 中心锥 /
- 气膜冷却 /
- 冲击冷却
Abstract: Numerical investigation was performed on the infrared suppress characteristics of the nozzles with and without cone cooled.In the former,cone and blade were cooled by secondary channel gas,and the temperatures of blade and cone walls were effectively decreased by 21.1% and 46.2% respectively,using only 1.6% of the secondary gas.The radiation of nozzle cavity in 3~5μm was suppressed effectively,the radiation in the small view angle range from behind the nozzle decreased obviously,and the radiation decreased by 30% from straight behind the nozzle compared to the nozzle without cone cooling.
- infrared suppressing /
- nozzle cavity /
- cone /
- film cooling /
- impinging cooling

HTML

参考文献(13)

[1]	张宗斌,桑建华.发动机排气系统红外隐身技术研究[J].隐身技术,2009(3):2-4. ZHANG Zongbin,SANG Jianhua.Research of infrared technology of aeroegine exhaust system[J].Stealth Technology,2009(3):2-4.(in Chinese)
[2]	航空发动机手册编委会.航空发动机手册第七分册,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 aeroengine high-speed exhaust system[J].Journal of Aerospace Power,2002,12(5):582-585.(in Chinese)
[4]	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,2004,19(2):104-110. ZHANG Bo,JI Honghu.Numerical study of internal and external flow mixing for rectangular nozzles with large aspect ratio[J].Journal of Aerospace Power,2004,19(2):104-110.(in Chinese)
[5]	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,2007,22(11):1820-1825. ZHANG Bo,JI Honghu,LUO Mingdong,et al.Investigation of the effect of aspect ratio to infrared suppressing characteristics of rectangular nozzles[J].Journal of Aerospace Power,2007,22(11):1820-1825.(in Chinese)
[6]	张靖周,单勇.直升机排气系统用波瓣喷管引射-混合式红外抑制器研究[J].航空学报,2007,28(1):32-36. ZHANG Jingzhou,SHAN Yong.Investigation on lobed nozzle mixer-ejector infrared suppressor for helicopter exhaust system[J].Acta Aeronautica et Astronautica Sinica,2007,28(1):32-36.(in Chinese)
[7]	黄勇,郭志辉,魏福清.收扩喷管加小突片对尾喷流红外辐射的影响[J].航空动力报,2001,16(1):19-22. HUANG Yong,GUO Zhihui,WEI Fuqing.Effect of tabs fixed on a convergent-divergent nozzle on infrared radiation of exhausting jet[J].Journal of Aerospace Power,2001,16(1):19-22.(in Chinese)
[8]	黄宏艳,王强.V 形尾缘喷管流场与红外特性的数值模拟[J].北京航空航天大学学报,2008,34(2):158-161. HUANG Hongyan,WANG Qiang.Numerical simulation on flow field and infrared characteristics of chevron nozzles[J].Journal of Beijing University of Aeronautics and Astronautics,2008,34(2):158-161.(in Chinese)
[9]	刘友宏,卲万仁,张锦绣.发动机排气系统及尾喷流的流场和红外特征数值模拟[J].航空动力学报,2008,23(4):591-597. LIU Youhong,SHAO Wanren,ZHANG Jinxiu.Numerical simulation of flowfield and infrared characteristics of an aeroengine exhaust system and its plume[J].Journal of Aerospace Power,2008,23(4):591-597.(in Chinese)
[10]	Presz W M,Nelson C B.Gas turbine exhaust cooling concepts.AIAA-94-3083,1994.
[11]	Robert S,John R H.Thermal radiation heat transfer[M].Washington D C:McGraw-Hill Book Company,1990.
[12]	Ontar Corporation.PCModWin manual[M].North Andover,MA:Ontar Corporation,1995.
[13]	Ludwig C B,Malkmus W,Reardon J E,et al.Handbook of infrared radiation from combustion gases.NASA-SP-3080,1973.