湍流模型对发动机排气系统流场和红外辐射特征计算的影响

胡娅萍; 吉洪湖; 白涛涛

湍流模型对发动机排气系统流场和红外辐射特征计算的影响

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中国空空导弹研究院, 河南洛阳 471009

计量
- 文章访问数: 2060
- HTML浏览量: 429
- PDF量: 665
- 被引次数: 0
出版历程
- 收稿日期: 2012-01-16
- 刊出日期: 2012-11-28

Effect of turbulence models on numerical simulation of flow and infrared radiation characteristic of aero-engine exhaust system

1.
College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
2.
China Research Institute of Air-to-Air Missiles, Aviation Industry Corporation of China, Luoyang, Henan 471009, China

摘要

摘要: 计算分析了采用k-ω SST(shear-stress transport)模型、RNG(renormalization group)k-ε模型配合标准壁面函数(RNG k-ε+标准壁面函数)、RNG k-ε模型配合增强型壁面函数法(RNG k-ε+增强壁面函数)3种湍流模拟方法,对典型涡扇发动机轴对称收敛喷管排气系统流场、温度场、组分质量浓度场及红外辐射特征计算结果的影响.研究表明:对于这3种方法,排气系统腔体内壁面压力分布基本一致;但在温度场、组分质量浓度分布以及红外辐射特征方面的差别较大.RNG k-ε+增强壁面函数计算得到的内涵壁面与燃气流的温度、CO₂与H₂O的质量浓度和红外辐射强度值最大,RNG k-ε+标准壁面函数的计算结果其次,而k-ω SST 模型的计算结果最小.通过与试验结果对比,发现k-ω SST模型对排气系统红外辐射特征的模拟更加合理一些.
- 湍流模型 /
- 壁面函数 /
- 排气系统 /
- 流场 /
- 红外辐射
Abstract: The flow field and infrared radiation (IR) characteristics of an aero-engine exhaust system were simulated with three turbulence models, including k-ω shear-stress transport (SST) model,renormalization group (RNG) k-ε model with standard wall functions and RNG k-ε model with enhanced wall functions.The results show that among the three methods, the static pressures are nearly the same,but the distributions of temperature,species and IR are different.The temperature of gas and the inner wall of inner duct,the mass concentration of species and IR are the greatest when RNG k-ε model with enhanced wall functions is used;those are the second when RNG k-ε model with standard wall functions is used,and the results of k-ω SST model are minimal.The comparison of experimental data and those of computation shows that the IR results of k-ω SST model are more reasonable.
- turbulence model /
- wall functions /
- exhaust system /
- flow field /
- infrared radiation

HTML

参考文献(15)

[1]	黄伟,吉洪湖.加力式涡扇发动机非加力状态部件红外辐射分析[J].航空动力学报,2011,26(1):48-53. HUANG Wei,JI Honghu.Analysis of components infrared radiation of afterburning turbofan engine under non-afterburning condition[J].Journal of Aerospace Power,2011,26(1):48-53.(in Chinese)
[2]	刘福城,吉洪湖,林兰之,等.二元引射喷管几何特征参数对推力及红外特性的影响[J].航空动力学报,2011,26(6):1244-1250. LIU Fucheng,JI Honghu,LIN Lanzhi,et al.Impact of geometry parameters on the thrust and infrared radiation characteristics of two-dimensional ejector nozzle[J].Journal of Aerospace Power,2011,26(6):1244-1250.(in Chinese)
[3]	黄伟,吉洪湖,斯仁,等.涡扇发动机排气系统红外特征[J].推进技术,2010,31(6):745-772. HUANG Wei,JI Honghu,SI Ren,et al.Infrared characteristics calculating of turbofan engine exhaust system[J].Journal of Propulsion Technology,2010,31(6):745-772.(in Chinese)
[4]	罗明东,吉洪湖,黄伟,等.轴对称喷管与后机身组合结构的红外特性实验[J].南京航空航天大学学报,2007,39(3):293-297. LUO Mingdong,JI Honghu,HUANG Wei,et al.Experiments on infrared radiation characteristics of combination axisymmetric nozzle and aft fuselage[J].Journal of Nanjing University of Aeronautics ＆ Astronautics,2007,39(3):293-297.(in Chinese)
[5]	陶文铨.数值传热学[M].西安:西安交通大学出版社,2001.
[6]	Ladd J A,Korakianitis T.On the assessment of one- and two-equation turbulence models for the computation of impinging jet flowfields [R].AIAA-96-2545,1996.
[7]	Kral L D,Mani M,Ladd J A.On the application of turbulence models for aerodynamic and propulsion flowfields [R].AIAA-96-0564,1996.
[8]	Moreau S,Mauffred T.Numerical simulations of afterbody flowfields with two-equation turbulence models [R].AIAA-96-0570,1996.
[9]	Dippold V.Investigation of wall function and turbulence model performance within the wind code [R].AIAA-2005-1002,2005.
[10]	刘友宏,李立国.直排波瓣喷管引射器流场计算k-ε模型的选择[J].空气动力学学报,2002,20(3):343-350. LIU Youhong,LI Liguo.Numerical study of k-ε turbulent models for flow within a straightly lobed nozzle[J].ACTA Aerodynamica Sinica,2002,20(3):343-350.(in Chinese)
[11]	王全,王强.激波诱导二元矢量喷管内流特性数值研究[J].航空动力学报,2006,21(4):681-685. WANG Quan,WANG Qiang.Computational analysis on static internal flow field of shock vector controlled vectoring exhaust nozzles[J].Journal of Aerospace Power,2006,21(4):681-685.(in Chinese)
[12]	黄宏艳,王强.过膨胀状态下轴对称收-扩喷管内外流场计算及分析[J].航空动力学报,2007,22(7):1069-1073. HUANG Hongyan,WANG Qiang.Numerical investigation on internal and external flows for axisymmetric convergent-divergent nozzles on over-expansion state[J].Journal of Aerospace Power,2007,22(7):1069-1073.(in Chinese)
[13]	胡海洋,王强.跨声速条件下轴对称收扩喷管内外流场的数值研究[J].航空动力学报,2008,23(6):1041-1046. HU Haiyang,WANG Qiang.Numerical study on combination flow field of axisymmetric convergent-divergent nozzle under transonic and supersonic conditions[J].Journal of Aerospace Power,2008,23(6):1041-1046.(in Chinese)
[14]	TANG Zhigong,LIU Gang,MOU Bin,et al.Effects of turbulence models on the numerical simulation of nozzle jets[J].ACTA Aerodynamica Sinica,2010,28(2):188-196.
[15]	罗明东,吉洪湖,黄伟.非加力涡轮发动机排气系统红外辐射强度的数值计算[J].航空动力学报,2007,22(10):1609-1616. LUO Mingdong,JI Honghu,HUANG Wei.Numerical evaluation on infrared intensity of exhaust system of turbine engine without afterburning[J].Journal of Aerospace Power,2007,22(10):1609-1616.(in Chinese)