A numerical investigation is performed to study cooling and infrared radiation suppression of the plug trailing-body of a two-dimensional plug nozzle at a primary flow total temperature of 920 K and a cooling flow temperature of 470 K. The effects of the multi-hole perforated percentage (ranging from 1% to 4%), cooling air usage (limited in 4.3% of the primary mass flow rate) and vector angle (ranging from 0° to 20°) on cooling and infrared radiation suppression of the plug trailing-body are analyzed. The results show that the plug trailing-body cooling has an effective role in decreasing the surface temperature and suppressing infrared radiation intensity. The multi-hole perforated percentage of 2% seems more reasonable. Once coolant usage is increased beyond 2.85% of the primary mass flow rate, the increase of coolant usage has a weak influence on further reduction of surface temperature. The cooling action on the plug trailing-body with coolant usage of 2.85% of the primary mass flow rate is capable of suppressing the infrared radiation intensity about 50% relative to the un-cooled nozzle on the horizontal detective plane. On the vertical detective plane, the cooling action on the plug trailing-body shows more significant influence on infrared radiation suppression. The vector angle has a weak influence on surface temperature distribution. However, the distribution of infrared radiation is seriously affected by vector deflection.
ZHENG Jiansheng, SHAN Yong, ZHANG Jingzhou. Cooling and infrared radiation suppression effect of plug trailing-body of two-dimensional vector plug nozzle[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(12): 121384-121384. DOI: 10.7527/S1000-6893.2017.121384
[1]Mahulikar S P, Sonawane H R, Rao G A.Infrared signa-ture studies of aerospace vehicles. Progress in Aerospace Sciences, 2007, 43: 218-245.
[2]单勇, 张靖周.波瓣喷管气膜冷却混合管气动和红外辐射特性实验[J].航空学报, 2008, 29(2):309-314
[3]Shan Yong, Zhang Jingzhou.Experimental on aerody-namic and infrared radiation characteristics of lobed noz-zlefilm cooling mixing duct[J].Acta Aeronautica et Astro-nautica Sinica, 2008, 29(2):309-314
[4]杨承宇，张靖周，单勇.单边膨胀喷管红外辐射特性的数值模拟[J].航空学报, 2010, 31(10):1919-1926
[5]Yang Chengyu, Zhang Jingzhou, Shan Yong.Numerical simulation on infrared radiation characteristics of single expansion ramp nozzles[J].Acta Aeronautica et Astronau-tica Sinica, 2010, 31(10):1919-1926
[6]Blunck D L, Gore J P.Study of narrowband radiation intensity measurements from subsonic exhaust plumes[J].Journal of Propulsion and Power, 2011, 27(1):227-235
[7]黄伟，吉洪湖.基于的排气系统红外辐射特征计算研究[J].航空学报, 2012, 33(7):1227-1235
[8]Huang Wei, Ji Honghu.Computational investigation of infrared radiation characteristics of exhaust system based on BRDF[J].Acta Aeronautica et Astronautica Sinica, 2012, 33(7):1227-1235
[9]Blunck D L, Gore J P.Study of narrowband radiation intensity measurements from subsonic exhaust plumes[J].Journal of Propulsion and Power, 2011, 27(1):227-235
[10]Shan Y, Zhang J Z, Pan C X.Numerical and experimen-tal investigation of infrared radiation characteristics of a turbofan engine exhaust system with film cooling central body [J]. Aerospace Science and Technology, 2013, 28: 281-288.
[11]Baranwal N, Mahulikar S P.Aircraft engine’s infrared lock-on range due to back pressure penalty from choked convergent nozzle[J]. Aerospace Science and Technology, 2014, 39: 377-383.
[12]Clark J S, Lieberman A.Thermal design study of an air-cooled plug-nozzle system for a supersonic-cruise air-craft[R]. NASA TM X-2475, 1972.
[13]Maiden D L, Petit J E.Investigation of two-dimensional wedge exhaust nozzles for advanced aircraft[R]. AIAA Paper 75-1317, 1975.
[14]Nosek S M, Straight D M.Heat transfer characteristics of partially film cooled plug nozzle on a J-85 after-burning turbojet engine[R]. NASA TM X-3362, 1976.
[15]Cler D L, Mason M L, Guthrie A R.Experimental inves-tigation of spherical-convergent-flap thrust-vectoring two-dimensional plug nozzles[R]. AIAA Paper 93-2431, 1993.
[16]琚春光, 刘宇.塞式喷管推力模型的建立与实验验证[J].航空学报, 2007, 28(4):821-826
[17]Ju Chun-guang, Liu Yu.Establishment and experiment comparison of thrust models for plug nozzle[J].Acta Aeronautica et Astronautica Sinica, 2007, 28(4):821-826
[18]Munday D, Mihaescu M, Gutmark E.Experimental and numerical study of jets from elliptic nozzles with conic plug[J].AIAA Journal, 2011, 49(3):554-564
[19]Kapilavai D S K, Tapee J, Sullivan J, et al.Experimental testing and numerical simulations of shrouded plug-nozzle flow fields[J].Journal of Propulsion and Power, 2012, 28(3):530-544
[20]Chutkey K, Balakrishnan N.Analysis of annular plug nozzle flowfield[J].Journal of Spacecraft and Rockets, 2014, 51(2):478-490
[21]陈俊, 吉洪湖, 黄伟, 等.涡扇发动机轴对称塞式喷管红外辐射特征计算[J].工程热物理学报, 2010, 31(12):2079-2082
[22]Chen Jun, Ji Honghu, Huang Wei, et al.Investigation of the infrared radiation characteristics for plug nozzle of a turbofan engine[J].Journal of Engineering Thermophys-ics, 2010, 31(12):2079-2082
[23]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, 27(11):2429-2435
[24]Chen Jun, Ji Honghu.Numerical simulation of the infra-red radiation characteristics and infrared restraining ef-fect of lower wall temperature for two-dimensional plug nozzle[J].Journal of Aerospace Power, 2012, 27(11):2429-2435
[25]张靖周, 王旭, 单勇.塞锥后体气膜冷却对轴对称塞式喷管红外辐射和气动性能的影响[J].航空学报, 2015, 36(8):2601-2608
[26]Zhang Jingzhou, Wang Xu, Shan Yong.Effects of plug rear-body film cooling on infrared radiation and aerody-namic performance of axisymmetric plug nozzle[J].Acta Aeronautica et Astronautica Sinica, 2015, 36(8):2601-2608
[27]Pan Cheng-xiong, Zhang Jing-zhou, Shan Yong.Model-ing and analysis of helicopter thermal and infrared radia-tion[J].Chinese Journal of Aeronautics, 2011, 24(5):558-567
CJA