球面收敛二元矢量喷管气动及红外特性研究:模拟高空状态

征建生; 张靖周; 单勇; 季靖远

doi:10.13224/j.cnki.jasp.2017.02.017

球面收敛二元矢量喷管气动及红外特性研究:模拟高空状态

doi: 10.13224/j.cnki.jasp.2017.02.017

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

基金项目: 国家自然科学基金（51306088）；江苏省自然科学基金（BK20130790）

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出版历程
- 收稿日期: 2015-06-08
- 刊出日期: 2017-02-28

Investigation on aerodynamic and infrared performance of a spherical convergent two-dimensional vectoring nozzle:simulating high altitude status

摘要

摘要: 针对高空状态下球面收敛二元矢量喷管排气系统,通过数值模拟研究了喷管俯仰偏转角对排气系统气动和红外辐射特性的影响,并与地面状态进行了对比分析.在该研究参数范围内,研究结果表明:在俯仰偏转角为20°范围内,俯仰偏转对排气系统推力系数和总压恢复系数的影响微弱,气动推力矢量角与俯仰偏转角几乎相等,高空状态下,喷管的推力系数和总压恢复系数下降0.5%与1.1%；热喷流峰值红外辐射强度仅为地面状态的12%~24%,排气系统的总体红外辐射强度峰值与地面状态下的比值峰值在0.35~0.45之间；随着下俯仰偏转角的增加,排气系统红外辐射峰值呈现下降的趋势.
- 高空状态 /
- 球面收敛二元矢量喷管 /
- 俯仰偏转 /
- 气动特性 /
- 红外辐射特性
Abstract: A numerical investigation was performed to study the effects of pitching angle on the aerodynamic and infrared performances of a spherical convergent twodimensional vectoring nozzle under high attitude status. In the present research, the comparison with the ground status simulation was also taken into consideration. The results show that the pitch deflection has a very weak impact on the thrust coefficient and total pressure recovery coefficient of exhaust system under the pitching angle ranging from 0 degree to 20 degree. The aerodynamic vectoring angle is nearly the same as the geometric vectoring angle. The thrust coefficient and total pressure recovery coefficient of exhaust nozzle under high attitude status decrease 0.5% and 1.1%, respectively. As the total infrared radiation of exhaust system in 3-5μm band is concerned, the peak infrared radiation intensity of plume under high attitude status is only 12-24 percent of the corresponding values under ground status. For the total infrared radiation of exhaust system, the ratio of high attitude status to ground status is among 0.35 and 0.45. In general, the peak number of nozzle's infrared performance is continuously decreasing with the increase of vector angle.
- high attitude status /
- spherical convergent twodimensional vectoring nozzle /
- pitch deflection /
- aerodynamic characteristics /
- infrared radiation

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参考文献(18)

[1]	Gutierrez J L.First full scale engine evaluation of an IHPTET exhaust nozzle technology demonstrator［R］.AIAA 95-2747,1995.
[2]	梁春华,靳宝林,李雨桐.球形收敛调节片推力矢量喷管的发展［J］.航空发动机,2002(3):55-58. LIANG Chunhua,JIN Baolin,LI Yutong.Development of spherical convergent flap nozzle［J］.Aeroengine,2002(3):55-58.(in Chinese)
[3]	Meyer B E,MacLean M K.Scale model test results for several spherical/twodimensional nozzle concepts［R］.AIAA 93-2430,1993.
[4]	Wing D J.Static thrust and vectoring performance of a spherical convergent flap nozzle with a nonrectangular divergent duct［R］.NASA TP-1998-206912,1998.
[5]	宋洁,王强.复杂形式球型收敛调节片喷管内流场计算及分析［J］.航空动力学报,2007,22(8):1325-1329. SONG Jie,WANG Qiang.Numerical investigation on internal flow of a spherical convergent flap nozzle with complex geometry［J］.Journal of Aerospace Power,2007,22(8):1325-1329.(in Chinese)
[6]	金捷,王强.轴对称矢量喷管内流特性的数值模拟研究［J］.航空动力学报,2001,16(4):394-397. JIN Jie,WANG Qiang.Numerical simulation of static internal performance for an axisymmetric vectoring exhaust nozzle［J］.Journal of Aerospace Power,2001,16(4):394-397.(in Chinese)
[7]	赵一鹗,余少志.复杂几何形状喷管内外三维流场的数值模拟［J］.推进技术,2000,21(3):30-33. ZHAO Yie,YU Shaozhi.Numerical simulation on internal and external flow fields of nozzle with complex geometry［J］.Journal of Propulsion Technology,2000,21(3):30-33.(in Chinese)
[8]	郑礼宝,张靖周.矢量二元收扩喷管热射流复杂流场特征研究［J］.流体力学实验与测量,2000,14(2):26-30,48. ZHENG Libao,ZHANG Jingzhou.Investigation of hotjet characteristics of 2D CD vectoring nozzle［J］.Experiments and Measurements in Fluid Mechanics,2000,14(2):26-30,48.(in Chinese)
[9]	王宏亮,张靖周,单勇.球型收敛调节片喷管静态内性能数值研究［J］.推进技术,2008,29(4):443-447. WANG Hongliang,ZHANG Jingzhou,SHAN Yong.Numerical study on static internal performance of spherical convergent flap nozzle［J］.Journal of Propulsion Technology,2008,29(4):443-447.(in Chinese)
[10]	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. WANG Hongliang,ZHANG Jingzhou,SHAN Yong.Numerical study on infrared radiation characteristics of spherical convergent flap nozzles［J］.Acta Aeronautica et Astronautica Sinica,2009,30(9):1576-1582.(in Chinese)
[11]	Mahulikar S P,Sonawane H R,Rao G A.Infrared signature studies of aerospace vehicles［J］.Progress in Aerospace Sciences,2007,43(7):218-245.
[12]	张小英,王先炜.轴对称矢量喷管红外特性的数值计算研究［J］.航空动力学报,2004,19(3):366-369. ZHANG Xiaoying,WANG Xianwei.Numerical research of infrared characteristics of axial symmetrical vectoring nozzle［J］.Journal of Aerospace Power,2004,19(3):366-369.(in Chinese)
[13]	刘友宏,邵万仁,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)
[14]	斯仁,吉洪湖,刘福城,等.二元引射喷管高空性能及对无人机红外抑制的数值研究［J］.航空动力学报,2014,29(1):42-50. SI Ren,JI Honghu,LIU Fucheng,et al.Investigation of thrust characteristics of twodimensional ejector nozzle and infrared characteristics of the UAV［J］.Journal of Aerospace Power,2014,29(1):42-50.(in Chinese)
[15]	罗明东,吉洪湖,黄伟,等.二元喷管热喷流的红外光谱辐射特性实验［ J］.推进技术,2007,28(2):152-156. LUO Mingdong,JI Honghu,HUANG Wei,et al.Experiment on spectral infrared radiation characteristics of exhaust jet from 2D nozzle of turbofan engine［J］.Journal of Propulsion Technology,2007,28(2):152-156.(in Chinese)
[16]	李伟,张勃,吉洪湖,等.不同锯齿对二元喷管实际腔体红外辐射特征影响的数值模拟［J］.航空动力学报,2014,29(8):1810-1816. LI Wei,ZHANG Bo,JI Honghu,et al.Numerical simulation on infrared radiation characteristics of twodimensional chevron nozzles considering engine components［J］.Journal of Aerospace Power,2014,29(8):1810-1816.(in Chinese)
[17]	ZHANG Jingzhou,PAN Chengxiong,SHAN Yong.Progress in helicopter infrared signature suppression［J］.Chinese Journal of Aeronautics,2014,27(2):189-199.
[18]	PAN Chengxiong,ZHANG Jingzhou,SHAN Yong.Modeling and analysis of helicopter thermal and infrared radiation［J］.Chinese Journal of Aeronautics,2011,24(5):558-567.