涡扇发动机排气系统中心锥气膜冷却结构的气动和红外辐射特性实验

单勇; 张靖周; 邵万仁; 尚守堂; 邓洪伟

涡扇发动机排气系统中心锥气膜冷却结构的气动和红外辐射特性实验

1.
南京航空航天大学能源与动力学院,南京 210016
2.
中国航空工业集团公司沈阳发动机设计研究所,沈阳 110015

基金项目: 航空科学基金(2010ZB52019)

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出版历程
- 收稿日期: 2011-01-29
- 修回日期: 2011-05-09
- 刊出日期: 2012-01-28

Experiments on aerodynamic and infrared radiation characteristics of film-cooling center-body exhaust system for a turbofan engine

1.
College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
2.
Shenyang Aeroengine Design and Research Institute, Aviation Industry Corporation of China, Shenyang 110015, China

摘要

摘要: 以降低涡扇发动机排气系统红外辐射为目的,针对某型涡扇排气系统构建1/3缩比模型,采用实验的方法比较了中心锥有/无冷却的排气系统喷流温度场和红外辐射场,验证了中心锥冷却结构能够大幅度降低涡扇发动机排气系统尾向红外辐射强度.研究结果表明:中心锥表面在外涵气体冷却下温度降低,同时尾焰核心温度也降低.当涵道比为0.3时,在0°~10°范围内,气膜冷却中心锥体排气系统红外辐射降低24%~32%;在20°~90°范围内,红外辐射强度降低0.8%~2.1%.当涵道比增加到0.8时,0°方向的红外辐射强度降低60%;20°~90°范围内的红外辐射强度降低了33%~51%.
- 涡扇排气系统 /
- 模型实验 /
- 气膜冷却 /
- 红外辐射 /
- 中心锥
Abstract: For depressing the infrared radiation of the turbofan exhaust system,a 1/3 scaled model was constructed according one-type engine to investigate the plume temperature and infrared radiation for exhaust system with/without cooling center body,to validate the suppression capability of cooling center body.The experimental datum shows the temperature of the center body surface decrease under the bypass flow cooling.On the condition of bypass ratio 0.3,the infrared radiation intensity of the exhaust system with cooling center body depress by 24%~32% at the detected angle from 0° to 10° comparing to that of the baseline center body.When the bypass ratio increase to 0.8,the infrared radiation intensity of the exhaust system with cooling center body depress by 60% at the detected angle of 0°,and by 33%~51% at the detected angle of 20° to 90°.
- turbo-fan exhaust system /
- scaled model experiment /
- film cooling /
- infrared radiation /
- center-body

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参考文献(13)

[1]	林左鸣.战斗机发动机的研制现状和发展趋势[J].航空发动机,2006,32(1):1-8. LIN Zuoming.The current development and future trends of fighter engines[J].Journal of Aeroengine,2006,32(1):1-8.(in Chinese)
[2]	张靖周,李立国,高潮.波瓣喷管红外抑制系统的实验研究[J].航空动力学报,1997,12(2):212-214. ZHANG Jingzhou,LI Liguo,GAO Chao.An experimental study on a lobed nozzle of an infrared suppression system[J].Journal of Aerospace Power,1997,12(2):212-214.(in Chinese)
[3]	SHAN Yong,ZHANG Jingzhou.Numerical investigation of flow mixture enhancement and infrared radiation shield by lobed forced mixer[J].Applied Thermal Engineering,2009,29(17-18):3687-3695.
[4]	单勇,张靖周,邵万仁.某型涡扇排气系统缩比模型红外辐射特性实验[J].航空动力学报,2009,24(10):2228-2234. SHAN Yong,ZHANG Jingzhou,SHAO Wanren.Experiments on infrared radiation characteristics of exhaust system for a turbofan engine[J].Journal of Aerospace Power,2009,24(10):2228-2234.(in Chinese)
[5]	潘丞雄,张靖周,邵万仁,等.齿冠形收敛喷管模型气动和红外辐射特性数值研究[J].航空动力学报,2010,25(7):1518-1523. PAN Chengxiong,ZHANG Jingzhou,SHAO Wanren.Numerical research on flow dynamics and infrared radiation characteristics for scaled chevron convergent nozzle[J].Journal of Aerospace Power,2010,25(7):1518-1523.(in Chinese)
[6]	黄勇,郭志辉,魏福清,等.收扩喷管加小突片对尾喷流红外辐射的影响[J].航空动力学报,2001,16(1):19-22. HUANG Yong,GUO Zhihui,WEI Fuqing,et al.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)
[7]	黄勇,郭志辉,魏福清,等.小突片对热射流红外辐射的影响研究[J].推进技术,2001,22(2):122-125. HUANG Yong,GUO Zhihui,WEI Fuqing,et al.Effect of tabs fixed on a convergent nozzle to the infrared radiation of the exhausting hot jet[J].Journal of Propulsion Technology,2001,22(2):122-125.(in Chinese)
[8]	罗昕,张靖周,单勇,等.加遮挡板后二元喷管的红外辐射特性数值模拟[J].推进技术,2008,29(6):696-700. LUO Xin,ZHANG Jingzhou,SHAN Yong,et al.Numerical simulation on the infrared radiation character istics of two-dimensional nozzles with sheltering baffles[J].Journal of Propulsion Technology,2008,129(16):696-700.(in Chinese)
[9]	范仁钰,张靖周,单勇.遮挡板结构对二元喷管红外辐射特性的影响[J].航空动力学报,2011,26(2):343-348. FAN Renyu,ZHANG Jingzhou,SHAN Yong.Effects of sheltering baffles on the infrared radiation characteristics of two-dimensional nozzles[J].Journal of Aerospace Power,2011,26(2):343-348.(in Chinese)
[10]	罗明东,吉洪湖,黄伟,等.涡扇发动机二元喷管的红外光谱辐射特性实验[J].推进技术,2007,28(4):394-398. LUO Mingdong,JI Honghu,HUANG Wei,et al.Experiment on spectral infrared radiant characteristics of two-dimensional nozzles of turbofan engine[J].Journal of Propulsion Technology,2007,28(4):394-398.(in Chinese)
[11]	郑礼宝.全尺寸二元喷管红外辐射特性研究[J].航空学报,2002,23(2):140-142. ZHENG Libao.Infrared emissions from turbojet with two-dimensional nozzle[J].Acta Aeronautica et Astronautica Sinica,2002,23(2):140-142.(in Chinese)
[12]	罗明东,吉洪湖,黄伟,等.涡扇发动机二元喷管的红外光谱辐射特性实验[J].推进技术,2007,28(4):394-398. LUO Mingdong,JI Honghu,HUANG Wei,et al.Experiment on spectral infrared radiant characteristics of two-dimensional nozzles of turbofan engine[J].Journal of Propulsion Technology,2007,28(4):394-398.(in Chinese)
[13]	MacLean M K.Static internal performance tests of single expansion ramp nozzle concepts designed with LO considerations.AIAA 93-2429,1993.