Impacts of two-dimensional curved mixing duct exit geometric parameters on flow dynamics and infrared radiation characteristics for IR suppressor

Chen Geng; Tan Xiaoming; Shan Yong; Zhang Jingzhou

Volume 44 Issue 6

Aug. 2015

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Article Navigation > Infrared and Laser Engineering > 2015 > 44(6): 1704-1711

Chen Geng, Tan Xiaoming, Shan Yong, Zhang Jingzhou. Impacts of two-dimensional curved mixing duct exit geometric parameters on flow dynamics and infrared radiation characteristics for IR suppressor[J]. Infrared and Laser Engineering, 2015, 44(6): 1704-1711.

Citation:

Chen Geng, Tan Xiaoming, Shan Yong, Zhang Jingzhou. Impacts of two-dimensional curved mixing duct exit geometric parameters on flow dynamics and infrared radiation characteristics for IR suppressor[J]. Infrared and Laser Engineering, 2015, 44(6): 1704-1711.

Impacts of two-dimensional curved mixing duct exit geometric parameters on flow dynamics and infrared radiation characteristics for IR suppressor

1.
Jiangsu Province Key Laboratory of Aerospace Power Systems,College of Energy and Power,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China

Received Date: 2014-10-29
Rev Recd Date: 2014-12-03
Publish Date: 2015-06-25

Abstract

Based on general CFD/IR numerical simulations, the effects of two-dimensional curved mixing duct geometric parameters on helicopter aerodynamics and infrared radiation characteristics were investigated. Conclusions can be drawn as follows according to the computational results: Compared with two-dimensional curved mixing duct with rectangular outlet, the distorted configurations of mixing duct lobed rectangular outlet extend the perimeter of exhaust exit, thus the strength of the secondary flow shed by lobes is enhanced due to the effective shear-mixing caused by viscous and shear force, which contributes to a maximum increase about 19.2% in pumping capacity of the overall IR suppressor. Simultaneously, wall temperature of mixing duct is reduced significantly and the maximum infrared radiation intensity is decreased about 13.3% to its highest when changing the shape of mixing duct outlet from rectangle to rectangular lobe. When the lobe heights of mixing ducts remain unchanged, with the increase of lobe numbers, the pumping ratio of IR suppressor firstly increases then decreases, while the total pressure recovery coefficient firstly decreases then increases. In addition, when the lobe numbers of remain unchanged, with the increase of lobe heights, the pumping ratio rises gradually, but the total pressure recovery coefficient keeps declining, and in this situation, the infrared radiation intensity peak achieve a maximum decrease about 11.6%.
- IR suppressor,
- two-stage ejection,
- two-dimensional curved mixing duct,
- lobed mixer,
- pumping ratio,
- total pressure recovery coefficient,
- infrared radiation intensity

References

[1]
[2]	Armand F, Amelio Y. Infrared suppression for a gas turbine engine: US, 5699965[P]. 1997.
[3]	Ponton A J. The use of concurrent engineering techniques in helicopter IR suppressor design [R]. AIAA-2005-1290, 2005.
[4]
[5]	Thompson J, Birk A M, Cunningham M. Design of infrared signature suppressor for the Bell 205(UH-1H) helicopters, Part I: aerothermal design[C]//Proceedings of Seventh CASI Propulsion Symposium, 1999.
[6]
[7]
[8]	Mahulikar S P, Prasad H S S, Potnuru S K. Infrared signature suppression of helicopter engine duct based on conceal and camouflage[J]. J Propul Power, 2008, 24(3): 613-618.
[9]
[10]	Mahulikar S P, Rao G A, Sonawane H R. Infrared signature studies of aircraft and helicopters[J]. PIERS Proceedings,2009, 2(26): 18-21.
[11]	Yu Simon C M, Yip T H, Liu C Y. The mixing characteristics of forced mixers with scalloped lobes[J]. AIAA Journal of Propulsion and Power,1997, 13(2): 305-311.
[12]
[13]	Bettini C, Cravero C, Cogliandro S. Multidisciplinary analysis of a complete infrared suppression system[J]. ASME Proceedings, 2007, 6: 1365-1370.
[14]
[15]	Paterson R W. Turbofan mixer nozzle flow field-a benchmark experimental study[J]. Journal of Engineering for Gas Turbines and Power, 1984, 106: 692-698.
[16]
[17]	Xie Yi, Li Teng, Liu Youhong. Numerical investigation of vortical structures in a jet mixing flow of lobed mixer [J].Science Technology and Engineering, 2011, 11(32): 7972-7978. (in Chinese) 谢翌, 李腾, 刘友宏. 波瓣混合器混合流场中涡结构的数值研究[J]. 科学技术与工程, 2011, 11(32): 7972-7978.
[18]
[19]	Yue Wei, Lei Zhijun, Su Shangmei, et al. Numerical investigation on vortex structure and jet mixing mechanism in lobed mixer [J]. Journal of Aerospace Power, 2013, 28(2): 338-347. (in Chinese) 岳巍, 雷志军, 苏尚美, 等. 波瓣混合器涡系结构及射流掺混机理的数值研究[J]. 航空动力学报, 2013, 28(2): 338-347.
[20]
[21]	Zhang Jingzhou, Shan Yong, Li Liguo. 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) 张靖周,单勇,李立国. 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.
[22]
[23]	Wang Tonghui, Wang Xianwei, Zhang Jingzhou, et al. Effect of covering shelter on infrared radiation characteristics of helicopter infrared radiation suppressor[J]. Journal of Aerospace Power, 2009, 24(7): 1493-1499. (in Chinese) 王同辉, 王先炜, 张靖周, 等. 直升机红外抑制器遮挡罩间距对红外辐射特性的影响[J]. 航空动力学报, 2009, 24(7): 1493-1499.
[24]
[25]	Shan Yong, Zhang Jingzhou, Li Liguo. Numerical calculation and experimental verification for the infrared radiation characteristics of helicopter infrared radiation suppressor[J]. J Infrared Millim Waves, 2006, 25(2): 95-100. (in Chinese) 单勇, 张靖周, 李立国. 直升机红外抑制器红外辐射特性的数值研究和实验验证[J]. 红外与毫米波学报, 2006, 25(2): 95-100.
[26]
[27]	Liu Youhong, Liu Wei. Experimental and numerical study of ejection characteristics of circular lobe ejector with bend mixers [J]. Journal of Aerospace Power, 2005, 20(1): 92-97. (in Chinese) 刘友宏, 刘伟. 圆排波瓣弯曲混合管引射实验与数值模拟[J]. 航空动力学报, 2005, 20(1): 92-97.
[28]
[29]
[30]	Presz W M, Werle M. Multi-stage mixer/ejector system[R]. AIAA-2002-4064, 2002.
[31]
[32]	Pan Chengxiong, Zhang Jingzhou, Shan Yong. Research on suppressing flow separation of lobed mixer-ejector by scarfing treatment[J]. Acta Aeronautica et Astronautica Sinica, 2013, 34(2): 255-262. (in Chinese) 潘丞雄, 张靖周, 单勇. 斜切对抑制引射式波瓣喷管内部流动分离的效果研究[J]. 航空学报, 2013, 34(2): 255-262.
[33]
[34]	Ren Lifeng, Zhang Jingzhou, Wang Xianwei, et al. Analysis of stealth properties on IR radiation suppressor embed inside helicopter rear airframe [J]. Infrared and Laser Engineering, 2011, 40(11): 2091-2097. (in Chinese) 任利锋, 张靖周, 王先炜, 等. 直升机后机身内埋式红外抑制器隐身性能分析[J]. 红外与激光工程, 2011, 40(11): 2091-2097.
[35]	Qi Xueqin, Wang Pingyang, Zhang Jingzhou, et al. Reverse Monte Carlo simulation on infrared radiation of lobed nozzle/mixer plume[J]. Journal of Shanghai Jiaotong University, 2005, 39(8): 1229-1232. (in Chinese) 亓雪芹, 王平阳, 张靖周, 等. 反向蒙特卡罗法模拟波瓣喷管的红外辐射特性[J]. 上海交通大学学报, 2005, 39(8):1229-1232.
[36]
[37]
[38]	Lv Jianwei, Wang Qiang. Numerical calculation and analysis of infrared radiation characteristics from aircraft skin by using RMC method[J]. Infrared and Laser Engineering, 2009, 38(2): 232-237. (in Chinese) 吕建伟, 王强. 飞行器蒙皮红外辐射特性的反向蒙特卡罗计算与分析方法[J]. 红外与激光工程, 2009, 38(2): 232-237.
[39]	Zhao Qiang, Yang Shizhi, Qiao Yanli, et al. Computation of radiative transfer model based on MODIS infrared channel [J]. Infrared and Laser Engineering, 2009, 38(2): 238-241. (in Chinese) 赵强, 杨世值, 乔延利, 等. 基于MODIS红外通道的辐射传输计算[J]. 红外与激光工程, 2009, 38(2): 238-241.

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通讯作者: 陈斌, bchen63@163.com

1.
沈阳化工大学材料科学与工程学院沈阳 110142

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Impacts of two-dimensional curved mixing duct exit geometric parameters on flow dynamics and infrared radiation characteristics for IR suppressor

1. Jiangsu Province Key Laboratory of Aerospace Power Systems,College of Energy and Power,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China

Received Date: 2014-10-29

Rev Recd Date: 2014-12-03

Publish Date: 2015-06-25

Key words:

Abstract: Based on general CFD/IR numerical simulations, the effects of two-dimensional curved mixing duct geometric parameters on helicopter aerodynamics and infrared radiation characteristics were investigated. Conclusions can be drawn as follows according to the computational results: Compared with two-dimensional curved mixing duct with rectangular outlet, the distorted configurations of mixing duct lobed rectangular outlet extend the perimeter of exhaust exit, thus the strength of the secondary flow shed by lobes is enhanced due to the effective shear-mixing caused by viscous and shear force, which contributes to a maximum increase about 19.2% in pumping capacity of the overall IR suppressor. Simultaneously, wall temperature of mixing duct is reduced significantly and the maximum infrared radiation intensity is decreased about 13.3% to its highest when changing the shape of mixing duct outlet from rectangle to rectangular lobe. When the lobe heights of mixing ducts remain unchanged, with the increase of lobe numbers, the pumping ratio of IR suppressor firstly increases then decreases, while the total pressure recovery coefficient firstly decreases then increases. In addition, when the lobe numbers of remain unchanged, with the increase of lobe heights, the pumping ratio rises gradually, but the total pressure recovery coefficient keeps declining, and in this situation, the infrared radiation intensity peak achieve a maximum decrease about 11.6%.

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Reference (39)

[1]
[2]	Armand F, Amelio Y. Infrared suppression for a gas turbine engine: US, 5699965[P]. 1997.
[3]	Ponton A J. The use of concurrent engineering techniques in helicopter IR suppressor design [R]. AIAA-2005-1290, 2005.
[4]
[5]	Thompson J, Birk A M, Cunningham M. Design of infrared signature suppressor for the Bell 205(UH-1H) helicopters, Part I: aerothermal design[C]//Proceedings of Seventh CASI Propulsion Symposium, 1999.
[6]
[7]
[8]	Mahulikar S P, Prasad H S S, Potnuru S K. Infrared signature suppression of helicopter engine duct based on conceal and camouflage[J]. J Propul Power, 2008, 24(3): 613-618.
[9]
[10]	Mahulikar S P, Rao G A, Sonawane H R. Infrared signature studies of aircraft and helicopters[J]. PIERS Proceedings,2009, 2(26): 18-21.
[11]	Yu Simon C M, Yip T H, Liu C Y. The mixing characteristics of forced mixers with scalloped lobes[J]. AIAA Journal of Propulsion and Power,1997, 13(2): 305-311.
[12]
[13]	Bettini C, Cravero C, Cogliandro S. Multidisciplinary analysis of a complete infrared suppression system[J]. ASME Proceedings, 2007, 6: 1365-1370.
[14]
[15]	Paterson R W. Turbofan mixer nozzle flow field-a benchmark experimental study[J]. Journal of Engineering for Gas Turbines and Power, 1984, 106: 692-698.
[16]
[17]	Xie Yi, Li Teng, Liu Youhong. Numerical investigation of vortical structures in a jet mixing flow of lobed mixer [J].Science Technology and Engineering, 2011, 11(32): 7972-7978. (in Chinese) 谢翌, 李腾, 刘友宏. 波瓣混合器混合流场中涡结构的数值研究[J]. 科学技术与工程, 2011, 11(32): 7972-7978.
[18]
[19]	Yue Wei, Lei Zhijun, Su Shangmei, et al. Numerical investigation on vortex structure and jet mixing mechanism in lobed mixer [J]. Journal of Aerospace Power, 2013, 28(2): 338-347. (in Chinese) 岳巍, 雷志军, 苏尚美, 等. 波瓣混合器涡系结构及射流掺混机理的数值研究[J]. 航空动力学报, 2013, 28(2): 338-347.
[20]
[21]	Zhang Jingzhou, Shan Yong, Li Liguo. 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) 张靖周,单勇,李立国. 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.
[22]
[23]	Wang Tonghui, Wang Xianwei, Zhang Jingzhou, et al. Effect of covering shelter on infrared radiation characteristics of helicopter infrared radiation suppressor[J]. Journal of Aerospace Power, 2009, 24(7): 1493-1499. (in Chinese) 王同辉, 王先炜, 张靖周, 等. 直升机红外抑制器遮挡罩间距对红外辐射特性的影响[J]. 航空动力学报, 2009, 24(7): 1493-1499.
[24]
[25]	Shan Yong, Zhang Jingzhou, Li Liguo. Numerical calculation and experimental verification for the infrared radiation characteristics of helicopter infrared radiation suppressor[J]. J Infrared Millim Waves, 2006, 25(2): 95-100. (in Chinese) 单勇, 张靖周, 李立国. 直升机红外抑制器红外辐射特性的数值研究和实验验证[J]. 红外与毫米波学报, 2006, 25(2): 95-100.
[26]
[27]	Liu Youhong, Liu Wei. Experimental and numerical study of ejection characteristics of circular lobe ejector with bend mixers [J]. Journal of Aerospace Power, 2005, 20(1): 92-97. (in Chinese) 刘友宏, 刘伟. 圆排波瓣弯曲混合管引射实验与数值模拟[J]. 航空动力学报, 2005, 20(1): 92-97.
[28]
[29]
[30]	Presz W M, Werle M. Multi-stage mixer/ejector system[R]. AIAA-2002-4064, 2002.
[31]
[32]	Pan Chengxiong, Zhang Jingzhou, Shan Yong. Research on suppressing flow separation of lobed mixer-ejector by scarfing treatment[J]. Acta Aeronautica et Astronautica Sinica, 2013, 34(2): 255-262. (in Chinese) 潘丞雄, 张靖周, 单勇. 斜切对抑制引射式波瓣喷管内部流动分离的效果研究[J]. 航空学报, 2013, 34(2): 255-262.
[33]
[34]	Ren Lifeng, Zhang Jingzhou, Wang Xianwei, et al. Analysis of stealth properties on IR radiation suppressor embed inside helicopter rear airframe [J]. Infrared and Laser Engineering, 2011, 40(11): 2091-2097. (in Chinese) 任利锋, 张靖周, 王先炜, 等. 直升机后机身内埋式红外抑制器隐身性能分析[J]. 红外与激光工程, 2011, 40(11): 2091-2097.
[35]	Qi Xueqin, Wang Pingyang, Zhang Jingzhou, et al. Reverse Monte Carlo simulation on infrared radiation of lobed nozzle/mixer plume[J]. Journal of Shanghai Jiaotong University, 2005, 39(8): 1229-1232. (in Chinese) 亓雪芹, 王平阳, 张靖周, 等. 反向蒙特卡罗法模拟波瓣喷管的红外辐射特性[J]. 上海交通大学学报, 2005, 39(8):1229-1232.
[36]
[37]
[38]	Lv Jianwei, Wang Qiang. Numerical calculation and analysis of infrared radiation characteristics from aircraft skin by using RMC method[J]. Infrared and Laser Engineering, 2009, 38(2): 232-237. (in Chinese) 吕建伟, 王强. 飞行器蒙皮红外辐射特性的反向蒙特卡罗计算与分析方法[J]. 红外与激光工程, 2009, 38(2): 232-237.
[39]	Zhao Qiang, Yang Shizhi, Qiao Yanli, et al. Computation of radiative transfer model based on MODIS infrared channel [J]. Infrared and Laser Engineering, 2009, 38(2): 238-241. (in Chinese) 赵强, 杨世值, 乔延利, 等. 基于MODIS红外通道的辐射传输计算[J]. 红外与激光工程, 2009, 38(2): 238-241.

Impacts of two-dimensional curved mixing duct exit geometric parameters on flow dynamics and infrared radiation characteristics for IR suppressor

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