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

doi:10.7527/S1000-6893.2015.0119

流体力学与飞行力学

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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

张靖周^1,2, 王旭¹, 单勇¹

1. 南京航空航天大学能源与动力学院江苏省航空动力系统重点实验室, 南京 210016;
2. 先进航空发动机协同创新中心, 北京 100191

收稿日期:2015-03-31 修回日期:2015-05-04 出版日期:2015-08-15 发布日期:2015-05-14
通讯作者: 张靖周男, 博士, 教授。《航空学报》第七、八届编委。主要研究方向: 强化传热、强化冷却和红外辐射特征控制。Tel: 025-84895909 E-mail: zhangjz@nuaa.edu.cn E-mail:zhangjz@nuaa.edu.cn
作者简介:王旭男, 硕士研究生。主要研究方向: 红外辐射特征控制。Tel: 025-84895909 E-mail: 736913151@qq.com;单勇男, 博士, 副教授。主要研究方向: 强化冷却和红外辐射特征控制。Tel: 025-84895909 E-mail: nuaasy@nuaa.edu.cn

Effects of plug rear-body film cooling on infrared radiation and aerodynamic performance of axisymmetric plug nozzle

ZHANG Jingzhou^1,2, WANG Xu¹, SHAN Yong¹

1. Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
2. Collaborative Innovation Center of Advanced Aero-Engine, Beijing 100191, China

Received:2015-03-31 Revised:2015-05-04 Online:2015-08-15 Published:2015-05-14
Contact: 10.7527/S1000-6893.2015.0119 E-mail:zhangjz@nuaa.edu.cn

摘要/Abstract

摘要：

运用数值模拟方法,在主流质量流量为130 kg/s、总温为920 K和冷却空气总温为480 K的参数条件下,对比分析了塞锥后体气膜孔排布方式、气膜孔倾角(15°~30°)和气膜冷却空气用量(3%主流质量流量以内)对轴对称塞式喷管红外辐射和气动性能的影响。研究结果表明:塞锥后体的气膜冷却对喷管推力系数的影响十分微弱;对塞锥后体提供1%主流质量流量的冷却空气,喷管红外辐射强度相对无冷却喷管降低50%左右;当冷却空气用量增大至3%时,喷管红外辐射强度下降约60%,总压恢复系数降低较为显著;在相同的冷却空气用量下,小孔排间距的多孔排布方式与大孔排间距相比,具有近乎相同的红外辐射抑制效果和低的总压恢复系数下降幅度;气膜孔倾角从30°减小至15°,对塞锥后体表面温度的降低以及喷管总压恢复系数的改善效果微弱。

关键词: 排气喷管, 轴对称塞式喷管, 塞锥气膜冷却, 红外辐射, 气动性能

Abstract:

A series of computations is conducted to investigate the effects of plug rear-body film cooling on the infrared radiation and aerodynamic performance of axisymmetric plug nozzle under the primary flow conditions (primary mass flow rate of 130 kg/s and total temperature of 920 K) as well as the cooling flow temperature of 480 K. The film-hole arrangement, film-holes inclination angle (ranging from 15° to 30°) and cooling air usage (limited in 3% of primary mass flow rate) are chosen as the influencing factors for comparison. The results show that the film cooling on plug rear-body has a very weak influence on the nozzle thrust coefficient. The cooling action on plug rear-body with cooling air usage of one percent of the primary mass flow rate is capable of having approximately 50% infrared radiation intensity reduction relative to the un-cooled nozzle. As the cooling air usage is increased to 3% of the primary mass flow rate, 60% infrared radiation intensity reduction is achieved; however, the total pressure recovery coefficient is decreased more significantly. Given the same cooling air usage, the multi-holes arrangement with small row-pitch seems to be more reasonable because it results in the nearly same infrared radiation suppression but low total pressure recovery coefficient reduction in comparison with the multi-hole arrangement with large row-pitch. The decrease of film-hole inclination angle from 30° to 15° has little influence on reducing surface temperature of the plug rear-body as well as improving total pressure recovery coefficient of the nozzle.

Key words: exhaust nozzle, axisymmetric plug nozzle, plug film cooling, infrared radiation, aerodynamic performance

中图分类号:

V231

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.

ZHANG Jingzhou, WANG Xu, SHAN Yong. Effects of plug rear-body film cooling on infrared radiation and aerodynamic performance of axisymmetric plug nozzle[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(8): 2601-2608.

参考文献

[1] Mahulikar S P, Sonawane H R, Rao G A. Infrared signature studies of aerospace vehicles[J]. Progress in Aerospace Sciences, 2007, 43(7-8): 218-245.
[2] Clark J S, Lieberman A. Thermal design study of an air-cooled plug-nozzle system for a supersonic-cruise aircraft, NASA TM X-2475[R]. Washington, D.C.: NASA, 1972.
[3] Petit J E, Capone F J. Performance characteristics of wedge nozzle installed on an F-18 propulsion wind tunnel model, AIAA-1979-1164[R]. Reston: AIAA, 1979.
[4] Ito T, Fujii K, Hayashi A K. Computations of axisymmetric plug-nozzle flow: flow structures and thrust performance[J]. Journal of Propulsion and Power, 2002, 18(2): 254-260.
[5] Wang C H, Liu Y, Liao Y F. Study on aerodynamic behavior and performance of aerospike nozzles[J]. Chinese Journal of Aeronautics, 2006, 19(1): 1-9.
[6] Ju C G, Liu Y. Establishment and experiment comparison of thrust models for plug nozzle[J]. Acta Aeronautica et Astronautica Sinica, 2007, 28(4): 821-826 (in Chinese). 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.
[7] Verma S B, Viji M. Linear-plug flowfield and base pressure development in freestream flow[J]. Journal of Propulsion and Power, 2011, 27(6): 1247-1258.
[8] 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.
[9] 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.
[10] Chutkey K, Balakrishnan N. Analysis of annular plug nozzle flowfield[J]. Journal of Spacecraft and Rockets, 2014, 51(2): 478-490.
[11] Shan Y, Zhang J Z. Experimental on aerodynamic and infrared radiation characteristics of lobed nozzle/film cooling mixing duct[J]. Acta Aeronautica et Astronautica Sinica, 2008, 29(2): 309-314 (in Chinese). 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.
[12] Wang H L, Zhang J Z, Shan Y. Numerical study on infrared radiation characteristics of spherical convergent flap nozzles[J]. Acta Aeronautica et Astronautica Sinica, 2009, 30(9): 1567-1582 (in Chinese). 王宏亮, 张靖周, 单勇. 球型收敛调节片喷管红外特性数值研究[J]. 航空学报, 2009, 30(9): 1576-1582.
[13] Hu H Y, Wang Q. A numerical simulation on the infrared radiation of hot exhausting nozzles with coupled flow and heat transfer model[J]. Science China Technological Science, 2010, 53(10): 2699-2707.
[14] Yang C Y, Zhang J Z, Shan Y. Numerical simulation on infrared radiation characteristics of single expansion ramp nozzles[J]. Acta Aeronautica et Astronautica Sinica, 2010, 31(10): 1919-1926 (in Chinese). 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.
[15] Huang W, Ji H H. Computational investigation of infrared radiation characteristics of exhaust system based on BRDF[J]. Acta Aeronautica et Astronautica Sinica, 2012, 33(7): 1227-1235 (in Chinese). 黄伟, 吉洪湖. 基于BRDF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.
[16] 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.
[17] 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.
[18] Chen J, Ji H H, Huang W, et al. Investigation of the infrared radiation characteristics for plug nozzle of a turbofan engine[J]. Journal of Engineering Thermophysics, 2010, 31(12): 2079-2082 (in Chinese). 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.
[19] Chen J, Ji H H. Numerical simulation of the infrared radiation characteristics and infrared restraining effect of lower wall temperature for two-dimensional plug nozzle[J]. Journal of Aerospace Power, 2012, 27(11): 2429-2435 (in Chinese). 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.
[20] Shan Y, Zhang J Z, Shao W R, et al. Experiments on aerodynamic and infrared radiation characteristics of film-cooling center-body exhaust system for a turbofan engine[J]. Journal of Aerospace Power, 2012, 27(1): 9-15 (in Chinese). 单勇, 张靖周, 邵万仁, 等. 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[J]. 航空动力学报, 2012, 27(1): 9-15.
[21] Shan Y, Zhang J Z, Pan C X. Numerical and experimental investigation of infrared radiation characteristics of a turbofan engine exhaust system with film cooling central body[J]. Aerospace Science and Technology, 2013, 28(1): 281-288.
[22] Zhang B, Ji H H, Zhang Z B, et al. Numerical investigation of effect of truncated cone with different cooling structures on infrared suppressing characteristics of nozzle cavities[J]. Journal of Aerospace Power, 2014, 29(10): 2362-2368 (in Chinese). 张勃, 吉洪湖, 张宗斌, 等. 截锥不同冷却结构对喷管腔体红外抑制影响的数值研究[J]. 航空动力学报, 2014, 29(10): 2362-2368.
[23] Pan C X, Zhang J Z, Shan Y. Modeling and analysis of helicopter thermal and infrared radiation[J]. Chinese Journal of Aeronautics, 2011, 24(5): 558-567.

E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

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

Effects of plug rear-body film cooling on infrared radiation and aerodynamic performance of axisymmetric plug nozzle

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