高亚声速喷流噪声Reynolds数效应数值分析
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- 论文作者：冯峰 ; 王强
- 年：2016
- 作者机构：中国航天空气动力技术研究院;
- 论文关键词：喷流 ; 湍流 ; Reynolds数效应 ; FW-H方法 ; 大涡模拟 ; 气动声学
- 会议召开时间：2016-11-04
- 会议录名称：2016年度全国气动声学学术会议论文摘要集
- 语种：中文
- 分类号：V231
- 学会代码：LTLX
- 会议名称：2016年度全国气动声学学术会议
- 会议地点：中国北京
- 主办单位：中国航空学会航空声学专业委员会、中国航空学会气动声学专业委员会、中国商飞上海飞机设计研究院、北京航空航天大学
- 学会名称：北京航空航天大学流体力学教育部重点实验室
- 页数：7
- 文件大小：1870k
- 原文格式：D
- 会议级别：全国
摘要
为适应航空噪声管制规定要求,发动机喷流噪声控制成为目前气动声学研究中的重要课题,预测分析喷流噪声辐射并揭示其产生机理将为噪声控制奠定基础。采用高精度并行LES方法计算分析Mach数0.9、Reynolds数为3600,60000,400000高亚声速喷流的湍流演化和气动噪声现象。首先,仔细分析了不同Reynolds数下喷流流场中不同尺度涡结构的演化形态。其次,分析了喷流流场脉动关联性和频谱特性。最后,通过LES结合可穿透面FW-H研究喷流Reynolds数对声辐射的影响。数值结果表明不同Reynolds数下高亚声速喷流均受Kelvin-Helmhotz不稳定性主导,剪切层大尺度涡环结构向下游对流时对并、破碎形成大量小尺度湍流结构,但随Reynolds数升高,高频扰动波增长迅速并产生大量小尺度涡。当Reynolds数升高后,流场中的脉动速度空间关联区显著减小湍流特征增强,对比发现Reynolds数60000,400000喷流脉动频谱分布十分相似,且脉动强度强于Re=3600情形。随着Reynolds数升高,喷流主导声波仍在远场低方位角占优,声指向性特征变化较小,大尺度拟序结构仍是主导声源,噪声峰值方位角均在α=30°。
引文
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11 Tam C K W.Computational Aeroacoustics:Issues and Methods.AIAA J.,1995,33(10):1788-1796.
12 Berland,J.,Bogey,C.,Bailly,C.,Optimized explicit schemes:matching and boundary schemes and 4thorder Runge-Kutta algorithm.AIAA Paper 2004-2814,2004.
13 Bogey C,de Cacqueray N,Bailly C.A shock-capturing methodology based on adaptative spatial filtering for high-order non-linear computations.J.Comput.Phys.,2009,228(5):1447-1465.
14 Lyrintzis A S,Uzun A.Integral techniques for jet aeroacoustics calculations.AIAA Paper 2001-2253,2001.
15 Bogey C,Bailly C.Three-dimensional non-reflective boundary conditions for acoustic simulations:far field formulation and validation test cases.Acta Acustica,2002,88(4):463-471.
2 Lighthill M J.On sound generated aerodynamically II.Turbulence as a source of sound.Proc.R.Soc.London A,1954,222(1148):1-32.
3 Freund J B.Noise sources in a low-Reynolds-number turbulent jet at Mach 0.9.J.Fluid Mech.,2001,438:277-305.
4 Bogey C,Bailly C,JuvéD.Noise investigation of a high subsonic,moderate Reynolds number jet using a compressible LES.Theor.Comp.Fluid.Dyn.,2003,16(4):273-297.
5 Bogey C,Bailly C.Investigation of subsonic jet noise using LES:Mach and Reynolds number effects.AIAA Paper 2004-3023,2004.
6 Viswanathan K,Shur M L,Spalart P R,Strelets M K.Computation of the flow and noise of round and beveled nozzles.AIAA Paper 2006-2445,2006.
7 Tam C K W.Jet noise:since 1952.Theor.Comp.Fluid.Dyn.,1998,10:393-405.
8 Tam C K W,Golebiowski M,Seiner J M.On the two components of turbulent mixing noise from supersonic jets.AIAA Paper 1996-1716,1996.
9 Crighton D G.Acoustics as a branch of fluid mechanics.J.Fluid Mech.,1981,106:261-298.
10 Tam C K W,Webb J C.Dispersion-relation-preserving finite difference schemes for computational acoustics.J.Comput.Phys.,1993,107(2):262-281.
11 Tam C K W.Computational Aeroacoustics:Issues and Methods.AIAA J.,1995,33(10):1788-1796.
12 Berland,J.,Bogey,C.,Bailly,C.,Optimized explicit schemes:matching and boundary schemes and 4thorder Runge-Kutta algorithm.AIAA Paper 2004-2814,2004.
13 Bogey C,de Cacqueray N,Bailly C.A shock-capturing methodology based on adaptative spatial filtering for high-order non-linear computations.J.Comput.Phys.,2009,228(5):1447-1465.
14 Lyrintzis A S,Uzun A.Integral techniques for jet aeroacoustics calculations.AIAA Paper 2001-2253,2001.
15 Bogey C,Bailly C.Three-dimensional non-reflective boundary conditions for acoustic simulations:far field formulation and validation test cases.Acta Acustica,2002,88(4):463-471.