留言板

尊敬的读者、作者、审稿人, 关于本刊的投稿、审稿、编辑和出版的任何问题, 您可以本页添加留言。我们将尽快给您答复。谢谢您的支持!

姓名
邮箱
手机号码
标题
留言内容
验证码

大涵道比涡扇发动机喷流降噪实验

刘常春 高亢 周驯黄

刘常春, 高亢, 周驯黄. 大涵道比涡扇发动机喷流降噪实验[J]. 航空动力学报, 2020, 35(8): 1716-1723. doi: 10.13224/j.cnki.jasp.2020.08.016
引用本文: 刘常春, 高亢, 周驯黄. 大涵道比涡扇发动机喷流降噪实验[J]. 航空动力学报, 2020, 35(8): 1716-1723. doi: 10.13224/j.cnki.jasp.2020.08.016
LIU Changchun, GAO Kang, ZHOU Xunhuang. Test of high-bypass-ratio turbofan engine jet noise reduction[J]. Journal of Aerospace Power, 2020, 35(8): 1716-1723. doi: 10.13224/j.cnki.jasp.2020.08.016
Citation: LIU Changchun, GAO Kang, ZHOU Xunhuang. Test of high-bypass-ratio turbofan engine jet noise reduction[J]. Journal of Aerospace Power, 2020, 35(8): 1716-1723. doi: 10.13224/j.cnki.jasp.2020.08.016

大涵道比涡扇发动机喷流降噪实验

doi: 10.13224/j.cnki.jasp.2020.08.016
基金项目: 国家自然科学基金青年基金(51706215)

Test of high-bypass-ratio turbofan engine jet noise reduction

  • 摘要: 对大涵道比分开排气喷管的缩比模型进行了吹风实验,模拟了双涵道喷流在加热条件下的远场噪声特性,分析了4种不同几何参数的锯齿构型对喷流噪声的影响。结果表明:喷流噪声以大尺度涡产生的低频噪声为主导,主要贡献方向为下游150°附近;锯齿喷管可以有效抑制低频部分及下游方向的噪声,最高可降低峰值声压级(SPL)约6 dB;锯齿的切入程度可以显著的影响降噪量,4种锯齿构型中切入程度高的外涵锯齿构型降噪效果最优,总声压级(OASPL)最高可降低3 dB;内涵锯齿构型的降噪效果比外涵锯齿低,总声压级最高降噪量在1 dB以内;内外涵锯齿构型可以在外涵锯齿的基础上进一步抑制低频噪声,下游方向总声压级最高降噪量为17 dB。

     

  • [1] TAM C W.Jet noise:since 1952[J].Theoretical and Computational Fluid Dynamics,1998,10(1):393-405.
    [2] TAM C W,GOLEBIOWSKI M,SIENER J M.On the two components of turbulent mixing noise from supersonic jets[R].AIAA-96-1716,1996.
    [3] BRIDGES J,WERNET M,BROWN C.Control of jet noise through mixing enhancement[R].NASA/TM-2003-212335,2003.
    [4] BRADBURY L J S,KHADEM A H.The distortion of a jet by tabs[J].Journal of Fluid Mechanics,1975,70(4):801-813.
    [5] SALIKUDDIN M,MARTENS S,JANARDAN B A,et al.Experimental study for multi-lobed mixer high bypass exhaust systems for subsonic jet noise reduction:Part 2 acoustic results[R].AIAA-99-1988,1999.
    [6] KROTHAPALLI A,KING C J.The role of streamwise vortices on sound generation of a supersonic[R].AIAA-93-4320,1993.
    [7] SAIYED N H,MIKKELSEN K L,BRIDGES J E,et al.Acoustics and thrust of separate-flow exhaust nozzles with mixing devices for high-bypass-ratio engines[R].AIAA-2000-1961,2000.
    [8] CALLENDER B,GUTMARK E J,MARTENS S.A near field acoustic investigation of chevron nozzle mechanisms[R].AIAA-2003-3210,2003.
    [9] CALLENDER B,GUTMARK E J,MARTENS S.Far-field acoustic investigation into chevron nozzle mechanisms and trends[J].AIAA Journal,2005,43(1):87-95.
    [10] CALLENDER B,GUTMARK E J,MARTENS S.A PIV flow field investigation of chevron nozzle mechanisms[R].AIAA-2004-191,2004.
    [11] BRIDGES J,BROWN C.Parametric testing of chevrons on single flow hot jets[R].AIAA-2004-2824,2004.
    [12] RASK O,GUTMARK E J,MARTENS S.Acoustic investigation of a high bypass ratio separate flow exhaust system with chevrons[R].AIAA-2004-0009,2004.
    [13] LOHEAC P,JULLIARD J,DRAVET A.CFM56 jet noise reduction with the chevron nozzle[C]∥Proceedings of the 10th AIAA/CEAS Aeroacoustics Conference.Manchester,UK:American Institute of Aeronautics and Astronautics,2004:3044-3056.
    [14] 庄家煜,李晓东.喷流噪声控制方法实验研究[J].工程热物理学报,2008,29(4):587-590. ZHUANG Jiayu,LI Xiaodong.An experimental study of jet noise suppression methods[J].Journal of Engineering Thermophysics,2008,29(4):587-590.(in Chinese)
    [15] 汪洋海,李晓东.超声速喷流啸声的控制方法[J].推进技术,2007,28(2):211-215. WANG Yanghai,LI Xiaodong.Control methods for supersonic jet screech tones[J].Journal of Propulsion Technology,2007,28(2):211-215.(in Chinese)
    [16] 何敬玉,邵万仁,许影博,等.V形槽喷管在分开式排气系统中的降噪实验[J].航空动力学报,2015,30(2):324-330. HE Jingyu,SHAO Wanren,XU Yingbo,et al.Experiment of noise reduction in separate flow system using chevron nozzles[J].Journal of Aerospace Power,2015,30(2):324-330.(in Chinese)
    [17] 何敬玉,李晓东.锯齿型喷口抑制热喷流噪声的实验研究[J].推进技术,2015,36(2):167-174. HE Jingyu,LI Xiaodong.Investigation into hot jet noise reduction mechanisms of chevron nozzles[J].Journal of Propulsion Technology,2015,36(2):167-174.(in Chinese)
    [18] 何敬玉,李晓东.吊挂安装效应对热喷流噪声影响实验[J].航空动力学报,2018,33(5):1057-1064. HE Jingyu,LI Xiaodong.Experimental of the pylon installation effect on hot jet noise[J].Journal of Aerospace Power,2018,33(5):1057-1064.(in Chinese)
    [19] TAM C W.Computational aeroacoustics-issues and methods[J].AIAA Journal,1995,33(10):1788-1796.
    [20] TAM C W,AURIAULT L.Jet mixing noise from fine-scale turbulence[J].AIAA Journal,1999,37(2):145-153.
    [21] THUROW B S,SAMIMY M,LEMPERT W R,et al.Compressibility effects on turbulence structures of axisymmetric mixing layers[J].Physics of Fluids,2003,15(6):1755-1765.
    [22] DAHL M D,PAPAMOSCHOU D.Analytical predictions and measurements of the noise radiated from supersonic coaxial jets[J].AIAA Journal,2000,38(4):584-591.
    [23] TAM C W,ZAMAN K.Subsonic jet noise from nonaxisymmetric and tabbed nozzles[J].AIAA Journal,2000,38(4):592-599.
  • 加载中
计量
  • 文章访问数:  580
  • HTML浏览量:  93
  • PDF量:  314
  • 被引次数: 0
出版历程
  • 收稿日期:  2020-02-19
  • 刊出日期:  2020-08-28

目录

    /

    返回文章
    返回