V形尾缘分开排气喷管喷流流场的数值模拟

康冠群; 王强

V形尾缘分开排气喷管喷流流场的数值模拟

康冠群,
王强

北京航空航天大学能源与动力工程学院,北京 100191

计量
- 文章访问数: 1940
- HTML浏览量: 198
- PDF量: 17
- 被引次数: 0
出版历程
- 收稿日期: 2009-12-04
- 修回日期: 2010-03-08
- 刊出日期: 2011-01-28

Numerical simulation on jet flow field of separate flow nozzles with chevron trailing edge

School of Jet Propulsion, Beijing University of Aeronautics and Astronautics,Beijing 100191,China

摘要

摘要: 采用二阶迎风离散格式并选用RNG(renormalization group) k-ε湍流模型,对轴对称分开排气喷管和核心喷管上采用V形尾缘的分开排气喷管的喷流流场进行三维数值模拟.结果表明,相对基准轴对称分开排气喷管,V形尾缘一方面引入了流向涡,另一方面增加了核心喷流与风扇喷流之间的混合层长度,强化了喷流的混合,有效地缩短了热核心区的长度,降低了喷流中心线附近的最大速度.此外,V形尾缘随着偏转角度的增加在一定的轴向范围内显著地减小了喷流速度和总温,相对而言,V形尾缘长度的增加对喷流混合的加强作用并不明显.
- 分开排气 /
- V形尾缘 /
- 喷流流场 /
- 数值模拟 /
- 强化混合
Abstract: Three-dimensional numerical simulations for the jet flow field of separate flow nozzles with/without chevrons on core nozzle were carried out.Calculation was conducted by employing second order upwind discretization scheme and RNG(renormalization group) k-ε turbulent model.As compared with baseline axisymmetric separate flow nozzle,addition of chevrons can strengthen the jet mixing since chevrons introduce streamwise vortices and increase the length of the mixing layer between core stream and fan stream,resulting in obvious reduction of hot potential core length and the decay of jet maximum velocity near the centerline.Moreover,increment of chevron deflection angle greatly enhances vortex strength so as to decrease jet velocity and total temperature substantially in a certain axial range.Relatively,reinforcement of jet mixing with increment of chevron length is not evident.
- separate flow /
- chevron trailing edge /
- jet flow field /
- numerical simulation /
- mixing enhancing

HTML

参考文献(12)

[1]	Janardan B A,Hoff G E,Barter J W,et al.AST critical propulsion and noise reduction technologies for future commercial subsonic engines;separate-flow exhaust system noise reduction concept evaluation .NASA/CR-2000-210039,2000.
[2]	Low J K C,Schweiger P S,Premo J W,et al.Advanced subsonic technology(AST) separate-flow high-bypass ratio nozzle noise reduction program test report .NASA/CP-2000-210040,2000.
[3]	Saiyed N.Separate flow nozzle test status meeting .NASA/CP-2000-210524,2000.
[4]	Golub R A,Rawls J W,Russell J W.Evaluation of the advanced subsonic technology program noise reduction benefits .NASA/TM-2005-212144,2005.
[5]	Shin H W,Babbitt R.Experimental study of exhaust system mixers for a subsonic jet noise reduction .AIAA Paper 96-2650,1996.
[6]	Koch L D,Bridges J,Khavaran A.Mean flow and noise prediction for a separate flow jet with chevron mixers .AIAA-2004-189,2004.
[7]	Peace A J.A method for calculating axisymmetric afterbody flows[J].Journal of Propulsion and Power,1987,3(4):357-364.
[8]	Peery K M,Forester C K.Numerical simulation of multistream nozzle flows .AIAA-1979-1549,1979.
[9]	Abdol-Hamid K S,Uenishi K,Keith B D,et al.Commercial turbofan engine exhaust nozzle flow analyses[J].Journal of Propulsion and Power,1993,9(3):431-436.
[10]	Saiyed N H,Mikkelsen K L,Bridges J E.Acoustics and thrust of separate-flow exhaust nozzles with mixing devices for high-bypass-ratio engines .AIAA-2000-1961,2000.
[11]	Georgiadis N J,Yoder D A,DeBonis J R.A comparison of three navier-stokes solvers for exhaust nozzle flowfields .AIAA-99-0748,1999.
[12]	邵万仁,尚守堂,张力,等.大涵道比涡扇发动机排气喷管技术分析 //中国航空学会2007年学术年会论文集.深圳:中国航空学会,2007.