高亚声速喷流近场的流-声关联

王庆宇; 刘琪麟; 赖焕新

doi:10.13224/j.cnki.jasp.2020.12.007

高亚声速喷流近场的流-声关联

doi: 10.13224/j.cnki.jasp.2020.12.007

基金项目: 国家自然科学基金(51976061)

计量
- 文章访问数: 62
- HTML浏览量: 6
- PDF量: 90
- 被引次数: 0
出版历程
- 收稿日期: 2020-04-22
- 刊出日期: 2020-12-28

引用格式：王庆宇,刘琪麟,赖焕新.高亚声速喷流近场的流-声关联［J］.航空动力学报,2020,35(12):2532-2542.WANG Qingyu,LIU Qilin,LAI Huanxin.Flow-acoustics correlations in near-fields of high subsonic jet［J］.Journal of Aerospace Power,2020,35(12):2532-2542.Flow-acoustics correlations in near-fields of high subsonic jet

School of Mechanical and Power Engineering,East China University of Science and Technology,Shanghai 200237,China

摘要

摘要: 针对马赫数为0.9的圆口喷流,采用大涡模拟计算流场与声场,在与直接数值模拟(DNS)和实验数据比对验证的基础上,分析了中心线和剪切层湍流脉动信号与声信号的相关性,并进一步对中心线上温度信号进行相关性研究。结果表明:相关系数在中心线上势流核末端附近出现峰值,说明该处的湍流脉动信号对声压信号有重要贡献,而这一区域的流动的间歇性与对流速度均较高。同时,声压与中心线上的温度脉动和温度梯度径向分量的脉动也有较高相关性,但与温度梯度轴向分量的脉动相关性较低,表明在模拟的温度比下轴向温度梯度对近场声压贡献较小。
- 亚声速喷流 /
- 大涡模拟 /
- 流-声关联 /
- 势流核末端 /
- 温度信号
Abstract: Large eddy simulation was carried out to predict the flow and acoustic near fields of a subsonic jet at Mach number of 0.9. The calculation was validated by available DNS and experimental data. Then the correlations between turbulent fluctuations along the center line and shear layer of the jet and the monitored sound pressure signals were analyzed. Furthermore, attentions were also paid to temperature signals on center line so as to unveil their contribution to sound. Results showed that the correlation coefficient peaks near the end of the potential core, indicating that the turbulence signals here contributed the most to the near-field sound pressure signal,and the flow in this area also had high intermittent and convective velocity. The near field sound pressure was also strongly correlated with the fluctuations of the temperature on the center line. But for the gradient of the temperature, only the radial component was intensely correlated with the sound pressure, while the correlation between axial component of the temperature gradient and the sound signal was relatively weak，indicated that the axial temperature gradient contributed little to the near field sound pressure under the simulated temperature ratio.
- subsonic jet flow /
- large eddy simulation /
- flow-acoustics correlations /
- ,end of potential core /
- signals of temperature

HTML

参考文献(20)

[1]	李晓东,徐希海,高军辉,等.喷流噪声研究进展与展望［J］.空气动力学学报,2018,36(3):398-409. LI Xiaodong,XU Xihai,GAO Junhui,et al.Progress and prospect on jet noise study［J］.Acta Aerodynamica Sinica,2018,36(3):389-409.(in Chinese)
[2]	JORDAN P,GERVAIS Y.Subsonic jet aeroacoustics:associating experiment,modelling and simulation［J］.Experiments in Fluids,2008,44(1):1-21.
[3]	BOGEY C,BARRE S,JUVE D,et al.Simulation of a hot coaxial jet:direct noise prediction and flow-acoustics correlations［J］.Physics of Fluids,2009,21(3):1-14.
[4]	FORTUNE V,GERVAIS Y.Numerical investigation of the noise radiated from hot subsonic turbulent jets［J］.AIAA Journal,1999,37(9):1055-1061.
[5]	TANNA H K.An experimental study of jet noise:Part Ⅰ turbulent mixing noise［J］.Journal of Sound and Vibration,1977,50(3):405-428.
[6]	LEW P T,BLAISDELL G A,LYRINTZIS A S.Investigation of noise sources in turbulent hot jets using large eddy simulation data［C］∥Proceedings of the 45th AIAA aerospace sciences meeting and exhibit.Reno:American Institute of Aeronautics and Astronautics,2007:65-96.
[7]	BOGEY C,BAILLY C.An analysis of the correlations between the turbulent flow and the sound pressure field of subsonic jets［J］.Journal of Fluid Mechanics,2007,583:71-97.
[8]	FREUND J B.Noise sources in a low-Reynolds-number turbulent jet at Mach 0.9［J］.Journal of Fluid Mechanics,2001,438:277-305.
[9]	BOGEY C,BAILLY C,JUVE D.Noise investigation of a high subsonic,moderate Reynolds number jet using a compressible large eddy simulation［J］.Theoretical and Computational Fluid Dynamics,2003,16(4):273-297.
[10]	何诚,赖焕新.伴流速度对平行喷口射流影响的数值研究［J］.航空动力学报,2018,33(8):2006-2015. HE Cheng,LAI Huanxin.Numerical investigation of influence of co-flow velocity on plane jet［J］.Journal of Aerospace Power,2018,33(8):2006-2015.(in Chinese)
[11]	YEE H C,SANDHAM N D,DJOMEHRI M J.Low dissipative high order shock capturing methods using characteristic based filters［J］.Journal of Computational Physics,1999,150(1):199-238.
[12]	SANDHAM N D,MOREFEY C L,HU Z W.Nonlinear mechanisms of sound generation in a perturbed parallel jet flow［J］.Journal of Fluid Mechanics,2006,565:1-23.
[13]	TULLIO N D,SANDHAM N D.Direct numerical simulation of breakdown to turbulence in a Mach 6 boundary layer over a porous surface［J］.Physics of Fluids,2010,22(9):1-15.
[14]	WARY A A.Very low storage time-advancement schemes［R］.Moffett Field,US:NASA-Ames Research Center,1986.
[15]	SANDHAM N D,LI Qinlin,YEE H C.Entropy splitting for high order numerical simulation of compressible turbulence［J］.Journal of Computational Physics,2000,178(2):307-322.
[16]	THOMPSON K W.Time dependent boundary conditions for hyperbolic systems［J］.Journal of Computational Physics,1987,68(1):1-24.
[17]	HUSSEIN H J,CAPP S P,GEORGE W K.Velocity measurements in a high-Reynolds-number,moment-conserving axisymmetric,turbulent jet［J］.Journal of Fluid Mechanics,1994,258:31-75.
[18]	PANCHAPAKESAN N R,LUMLEY J L.Turbulence Measurements in axisymmetric jets of air and helium:Part 1 air jets［J］.Journal of Fluid Mechanics,1993,246:197-223.
[19]	CANDEL S M.Numerical solution of conservation equations arising in linear wave theory:application to aeroacoustics［J］.Journal of Fluid Mechanics,1977,83(3):465-493.
[20]	林健,赖焕新.亚音速圆口喷流的大涡模拟［J］.华东理工大学学报(自然科学版),2016,42(5):715-721,742.