涡扇发动机收敛排气系统进口总温总压对喷流中心线温度分布影响

王丰; 吉洪湖; 于明飞

doi:10.13224/j.cnki.jasp.2016.04.007

涡扇发动机收敛排气系统进口总温总压对喷流中心线温度分布影响

doi: 10.13224/j.cnki.jasp.2016.04.007

南京航空航天大学能源与动力学院, 南京 210016

详细信息

作者简介:
王丰(1988-),男,山西长治人,硕士生,主要从事航空发动机红外隐身研究.

中图分类号: V231.1
计量
- 文章访问数: 1283
- HTML浏览量: 228
- PDF量: 611
- 被引次数: 0
出版历程
- 收稿日期: 2014-07-21
- 刊出日期: 2016-04-28

Influence of total temperature and pressure at the inlet of convergent exhaust system of turbofan engine on temperature distribution at plume centerline

College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 为了在涡扇发动机总体设计阶段,建立红外辐射特征预测模型,通过计算流体动力学方法研究涡扇发动机排气系统进口总温总压对其喷流无量纲温度分布规律的影响,得到适合涡扇发动机总体设计阶段使用的计算喷流中心线上温度分布的经验公式.结果表明:喷流中心线上相同无量纲温度对应的无量纲距离与涡扇发动机排气系统内外涵进口总压、外涵总温成正比与内涵总温成反比.总结出的涡扇发动机喷流中心线上温度分布的计算经验公式与数值计算结果吻合较好.
- 红外辐射特征 /
- 总温 /
- 总压 /
- 喷流 /
- 排气系统
Abstract: During the overall process of designing the turbofan engine, the model for predicting the signature of infrared radiation was established.With the method for calculating the fluid dynamics, the influence of the total temperature and total pressure at the inlet of convergent exhaust system of turbofan engine on the temperature distribution at plume centerline was estimated; the overall process of designing the turbofan engine was required and the approximate formula for calculating the temperature distribution at plume centerline was achieved. The result shows that the dimensionless distance corresponding to the dimensionless temperature at plume centerline is proportional to the total pressure of the inner duct, the bypass duct and total temperature of the bypass duct at the inlet of convergent exhaust system of turbofan engine, but inversely proportional to the total temperature of the inner duct.Therefore, it can be concluded that the summed-up experience formula of temperature distribution at the plume centerline of turbofan engine agrees well with the numerical results.
- signature of infrared radiation /
- total temperature /
- total pressure /
- plume /
- exhaust system

HTML

参考文献(16)

[1]	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 chevon nozzles considering engine components[J].Journal of Aerospace Power,2014,29(8):1810-1816.(in Chinese)
[2]	黄伟,吉洪湖,斯仁,等.降低表面温度和发射率抑制排气系统红外辐射的研究[J].推进技术,2011,32(4):550-556. HUANG Wei,JI Honghu,SI Ren,et al.Investigation of infrared suppression of exhaust system by reducing surface temperature and emissivity[J].Journal of Propulsion Technology,2011,32(4):550-556.(in Chinese)
[3]	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. SHAN Yong,ZHANG Jingzhou,SHAO Wanren,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)
[4]	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)
[5]	黄伟,吉洪湖,罗明东,等.对流辐射板抑制涡扇发动机热喷流红外辐射的实验[J].航空动力学报,2007,22(12):2000-2005. HU Wei,JI Honghu,LUO Mingdong,et al.Experiment of IR suppression for hot plume from turbofan engine with convection-radiation board[J].Journal of Aerospace Power,2007,22(12):2000-2005.(in Chinese)
[6]	陈翾,张健,王艳武,等.基于涂料性能参数的红外隐身技术[J].光学精密工程,2009,17(2):280-285. CHEN Xuan,ZHANG Jian,WANG Yanwu,et al.Infrared stealth technology based on performance parameters of camouflage coating[J].Optics and Precision Engineering,2009,17(2):280-285.(in Chinese)
[7]	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 evaluationon infrared radiant intensity of exhaust system of turbine engine without afterburning[J].Journal of Aerospace Power,2007,22(10):1609-1616.(in Chinese)
[8]	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)[9] 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):745-750,772. HUANG Wei,JI Honghu,SI Ren,et al.Infrared characteristics calculating of turbofan engine exhaust system[J].Journal of Propulsion Technology,2010,31(6):745-750,772.(in Chinese)
[10]	Decher R.Infrared emissions from turbofans with high aspect ratio nozzles[J].Journal of Aircraft,1981,18(12):1025-1031.
[11]	Tollmien W.Berechnung turbulenter ausbreitungsvorgänge[J].Zeitschrift für Angewandte Mathematik und Mechanik,1926,6(6):468-478.(in German)
[12]	肖洋,唐洪武,华明,等.同向圆射流混合特性实验研究[J].水科学进展,2006,17(4):512-517. XIAO Yang,TANG Hongwu,HUA Ming,et al.Experimental investigation on mixing characteristics of a round jet in co-flow[J].Advances in Water Science,2006,17(4):512-517.(in Chinese)
[13]	Kleinstein G.An approximate solution for the axisymmetric jet of a laminar compressible fluid[J].Quarterly of Applied Mathematics,1962,20(1):49-59.
[14]	Witze P.Centerline velocity decay of compressible free jets[J].AIAA Journal,1974,12(4):417-418.
[15]	刘常春,吉洪湖,黄伟,等.一种双S弯二元喷管的红外辐射特性数值研究[J].航空动力学报,2013,28(7):1482-1488. LIU Changchun,JI Honghu,HUANG Wei,et al.Numerical simulation on infrared radiation characteristics of serpentine 2-D nozzle[J].Journal of Aerospace Power,2013,28(7):1482-1488.(in Chinese)
[16]	谢象春.湍流射流理论与计算[M].北京:科学出版社,1975.
[17]	阿勃拉莫维奇.实用气体动力学[J].梁秀彦,译.北京:商务印书馆,1953.