边界层厚度对腔体气动声学特性影响数值模拟

张群峰; 闫盼盼; 黎军

doi:10.13224/j.cnki.jasp.2016.03.024

边界层厚度对腔体气动声学特性影响数值模拟

doi: 10.13224/j.cnki.jasp.2016.03.024

1. 北京交通大学土木建筑工程学院, 北京 100044;
2. 中国航空工业集团公司沈阳飞机设计研究所, 沈阳 110035

基金项目:

国家自然科学基金(11172283)

详细信息

作者简介:
张群峰(1972-),男,浙江富阳人,讲师,博士,研究方向为应用计算流体力学.

中图分类号: V211.3
计量
- 文章访问数: 929
- HTML浏览量: 0
- PDF量: 455
- 被引次数: 0
出版历程
- 收稿日期: 2015-06-22
- 刊出日期: 2016-03-28

Numerical simulation on influence of boundary-layer thickness on the cavity aero-acoustic characteristics

1. School of Civil Engineering, Beijing Jiaotong University, Beijing 100044, China;
2. Shenyang Aircraft Design and Research Institute, Aviation Industy Corporation of China, Shenyang 110035, China

摘要

摘要: 为了研究来流边界层厚度对开式腔体气动声学特性的影响,基于分离涡模拟方法,计算了来流马赫数为2.0条件下,不同来流边界层厚度与腔体深度比时,长深比为5.88的腔体流动特性,得到了该腔体声压级的频谱特性.计算结果表明:随着来流边界层厚度增加,形成的剪切层稳定性增强,失稳后上下摆动幅度减少,失稳生成的大尺度涡与超声速主流的相互作用减弱,使得大尺度涡发展到腔体后缘时所具有的平动动能和转动动能降低.大尺度涡撞击腔体后缘在腔体内形成的气动噪声的声压级降低,最大减小幅度达7.5dB.同时各阶模态的频率也发生偏移,偏移值在100Hz左右.基于新的假设重新推导了Rossiter公式,明确了经验常数的物理意义,并以此解释了频率偏移现象.
- 边界层厚度 /
- 声压级 /
- 分离涡模拟 /
- 腔体 /
- 剪切层
Abstract: To analyze the aero-acoustic characteristics in open cavity influenced by inflow boundary-layer thickness, the cavity with length-to-depth ratio of 5.88 was simulated under conditions of different ratios of inflow boundary-layer thickness to cavity depth and inflow Mach number of 2.0, based on detached eddy simulation method; and the features of sound pressure level spectrum were obtained. The results show that increase of inflow boundary-layer thickness leads to enhanced stability in shear layer and decreased the oscillation amplitude stemmed from shear layer instability. This weakens the interaction between large scale vortex and supersonic main flow, causing the decrease in translational kinetic energy and rotation kinetic energy of large scale vortex. Responding to the energy decrease of large scale vortex, the maximum reduction of the sound pressure level inside the cavity is 7.5dB. Meanwhile, the tone frequencies have about 100Hz shift. A new formula with clarified physical meanings of empirical constant has been deduced from the Rossiter formula based on a new hypothesis. And the frequencies shift phenomenon can be illustrated by the new formula.
- boundary-layer thickness /
- sound pressure level /
- detached eddy simulation /
- cavity /
- shear layer

HTML

参考文献(29)

[1]	黎军,李天,张群峰.开式流动腔体的流动机理与控制[J].实验流体力学,2008,22(1):80-83. LI Jun,LI Tian,ZHANG Qunfeng.The mechanism and control of open cavity flow[J].Journal of Experiments in Fluid Mechanics,2008,22(1):80-83.(in Chinese)
[2]	Beresh S J,Wagner J L,Pruett B O M.Supersonic flow over a finite-width rectangular cavity[J].AIAA Journal,2015,53(2):296-310.
[3]	ZHUANG Ning,Alvi F S,Shih C.Another look at super-sonic cavity flows and their control[J].AIAA-2005-2803,2005.
[4]	ZHUANG Ning,Alvi F S,Alkislar M B C.Supersonic cavity flows and their control[J].AIAA Journal,2006,44(9):2118-2128.
[5]	Gai S L,Kleine H,Neely A J,et al.Supersonic flow over a shallow open rectangular cavity[J].Journal of Aircraft,2014,52(2):609-616.
[6]	Handa T,Miyachi H,Kakuno H,et al.Modeling of a feedback mechanism in supersonic deep-cavity flows[J].AIAA Journal,2015,53(2):420-425.
[7]	Li W,Nonomura T,Oyama A,et al.Feedback mechanism in supersonic laminar cavity flows[J].AIAA Journal,2013,51(1):253-257.
[8]	杨党国,李建强,范召林.超声速来流边界层厚度对浅腔声学特性的影响[J].航空动力学报,2010,25(4):907-911. YANG Dangguo,LI Jianqiang,FAN Zhaolin.Shallow cavity noise influencing by boundary-layer thickness at supersonic speeds[J].Journal of Aerospace Power,2010,25(4):907-911.(in Chinese)
[9]	谭玉婷,伍贻兆,田书玲.基于DES的二维和三维空腔流动特性研究[J].航空计算技术,2010,40(1):67-70. TAN Yuting,WU Yizhao,TIAN Shuling.Numerical simulation of 2D/3D cavity flows using DES[J].Aeronautical Computing Technique,2010,40(1):67-70.(in Chinese)
[10]	司海青,王同光.边界条件对三维空腔流动振荡的影响[J].南京航空航天大学学报,2006,38(5):67-70. SI Haiqing,WANG Tongguang.Influence of boundary condition on 3-D cavity flow-induced oscillaions[J].Journal of Nanjing University of Aeronautics and Astronautics,2006,38(5):67-70.(in Chinese)
[11]	Boydston J D,Squires K D,Forsythe J R.Detached eddy simulation of high reynolds number flow over a rectangular cavity[R].AIAA-2008-606,2008.
[12]	Ryan F,Janmes E.Nonlinear feedback mechanisms inside a rectangular cavity[J].AIAA Journal,2014,52(10):2127-2141.
[13]	Jonathan G,Lawrence U.Detached eddy simulation of a supersonic cavity flow with and without passive flow control[R].AIAA-2011-3844,2011.
[14]	Ahuja K K,Mendoza J.Effects of cavity dimensions,boundary layer,and temperature on cavity noise with emphasis on benchmark data to validate computational aeroacoustic codes[R].NASA Report CR-4654,1995.
[15]	杨党国,罗新福,李建强.来流边界层厚度对开式空腔气动声学特性的影响分析[J].空气动力学学报,2011,29(4):486-490. YANG Dangguo,LUO Xinfu,LI Jianqiang.Analysis of aeroacoustic characteristics in open cavities influenced by boundary-layer thickness[J].Acta Aerodynamica Sinica,2011,29(4):486-490.(in Chinese)
[16]	李晓东,刘靖东,高军辉.空腔流激震荡发生的数值模拟研究[J].力学学报,2006,38(5):599-604. LI Xiaodong,LIU Jingdong,GAO Junhui.Numerical simulation of flow-induced oscillation and sound generation in a cavity[J].Chinese Journal of Theoretical and Applied Mechanics,2006,38(5):599-604.(in Chinese)
[17]	Blazek J.Computational fulid dynamics principles and applications[M].London:Elsevier,2005:16-18.
[18]	Spalart P R.Detached eddy simulation[J].Annual Review of Fluid Mechanics,2009,41(1):203-229.
[19]	Spalart P R,Jou W H,Strelets M,et al.Comments on the feasibility of LES for wings,and on a hybrid RANS/LES approach[R].Ruston,US:International Conference on DNS/LES,1997.
[20]	Spalart P R,Deck S,Shur M L,et al.A new version of detached-eddy simulation,resistant to ambiguous grid densities[J].Theoretical and Computational Fluid Dynamics,2006,20(3):181-195.
[21]	Shur M L,Spalart P R,Strelets M K,et al.A hybrid RANS-LES approach with delayed-DES and wall-modelled LES capabilities[J].International Journal of Heat and Fluid Flow,2008,29(6):1638-1649.
[22]	Strelets M.Detached eddy simulation of massively separated flows[R].AIAA-2001-0879,2001.
[23]	Gritskevich M S,Garbaruk A V,Schütze J,et al.Development of DDES and IDDES formulations for the k-ω shear stress transport model[J].Flow,Turbulence and Combustion,2012,88(3):431-449.
[24]	Venkatakrishnan V.On the convergence of limiters and convergence to steady state solutions[R].AIAA 93-0880,1993.
[25]	Rossiter J E.Wind tunnel experiments on the flow over rectangular cavities at subsonic and transonic speeds[R].Farnborough,UK:Aeronautical Research Council,1964.
[26]	Heller H H,Holmes D G,Covert E E.Flow induced pressure oscillations in shallow cavities[J].Journal of Sound and Vibration,1971,18(4):545-546.
[27]	Heller H H,Bliss D B.The physical mechanism of flow induced pressure fluctuations in cavities and concepts of their suppression[R].AIAA 75-491,1975.
[28]	陈懋章.粘性流体动力学基础[M].北京:高等教育出版社,2002:128-129.
[29]	李震,张锡文,何枫.基于速度梯度张量的四元分解对若干涡判据的评价[J].物理学报,2014,63(5):054704.1-054704.7. LI Zhen,ZHANG Xiwen,HE Feng.Evaluation of vortex criteria by virtue of the quadruple decomposition of velocity gradient tensor[J].Acta Physica Sinica,2014,63(5):054704.1-054704.7.(in Chinese)