Volume 35 Issue 2
Feb.  2020
Turn off MathJax
Article Contents
Article Navigation >  Journal of Aerospace Power  > 2020  >  35(2): 272-279
HUO Shiyu, YANG Jiafeng, DENG Yunhua. Acoustic characteristics test on aft-fan duct with titanium alloy annular acoustic liner[J]. Journal of Aerospace Power, 2020, 35(2): 272-279. doi: 10.13224/j.cnki.jasp.2020.02.006
Citation: HUO Shiyu, YANG Jiafeng, DENG Yunhua. Acoustic characteristics test on aft-fan duct with titanium alloy annular acoustic liner[J]. Journal of Aerospace Power, 2020, 35(2): 272-279. doi: 10.13224/j.cnki.jasp.2020.02.006
shu

Acoustic characteristics test on aft-fan duct with titanium alloy annular acoustic liner

doi: 10.13224/j.cnki.jasp.2020.02.006
  • 1.

    Aircraft Strength Research Institute of China,Aviation Industry Corporation of China Limited,Xi’an 710065,China

  • 2.

    School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics,Beijing 100191,China

  • 3.

    Manufacturing Technology Institute,Aviation Industry Corporation of China Limited,Beijing 100024,China

  • Received Date: 2019-08-18
  • Publish Date: 2020-02-28
    Abstract
  • Considering the potential application environment properties of titanium alloy honeycomb acoustic liner, an experimental method of the acoustic test of the annular acoustic liner with the influence of temperature gradient was proposed, and a simulated engine aft-fan duct acoustic test rig was developed. Then the acoustic test on titanium alloy annular acoustic liner was carried out. In view of the noise of 2 500 Hz and 2nd-order circumferential mode and the grazing flow with Mach number of 02, a titanium alloy annular acoustic liner was designed and prepared. The acoustic characteristics of the titanium alloy annular acoustic liner were studied by the means of duct acoustic mode test and far-field directivity test, respectively. Results showed that the noise reduction of the designed titanium alloy liner in the duct was 319 dB under the target operating conditions, and the 1 m far-field noise reduction appeared to be over 20 dB between 30° to 120°. Increasing the velocity of grazing flow expanded the bandwidth of the noise reduction spectrum and shifted the peak value of the spectrum from low frequency to high frequency. Increasing the temperature of the backplane of liner had little effect on the bandwidth of noise, but it shifted the peak value of noise reduction spectrum from low frequency to high frequency.

     

    • FullText(HTML)
  • loading
    • References(20)
  • [1]
    ENVIA E.Fan noise reduction:an overview［J］.Aeroacoustics,2002,1(1):43-64.
    [2]
    陈云永,杨小贺,卫飞飞.大涵道比风扇设计技术发展趋势［J］.航空学报,2017,38(9):520953.1-520953.8. CHEN Yunyong,YANG Xiaohe,WEI Feifei.Development trend of high bypass ratio turbofans design technology［J］.Acta Aeronautica et Astronautica Sinica,2017,38(9):520953.1-520953.8.(in Chinese)
    [3]
    陈超,闫照华,李晓东.风扇后传声降噪声衬设计方法及实验验证［J］.航空动力学报,2018,33(12):3041-3047. CHEN Chao,YAN Zhaohua,LI Xiaodong.Design method of acoustic liner applied to aft-fan noise reduction and experimental validation［J］.Journal of Aerospace Power,2018,33(12):3041-3047.(in Chinese)
    [4]
    纪双英,郝巍,刘杰.共振吸声结构在航空发动机上的应用进展［J］.航空工程进展,2019,10(3):302-308. JI Shuangying,HAO Wei,LIU Jie.Resonance absorbing structure and its application in aero engines［J］.Advances in Aeronautical Science and Engineering,2019,10(3):302-308.(in Chinese)
    [5]
    岳喜山,欧阳小龙,侯金保.钛合金蜂窝壁板结构制造技术研究［C］∥第16届全国钎焊及特种连接技术交流会论文集.北京:中国机械工程学会,2009:239-242.
    [6]
    谢宗蕻,岳喜山,孙俊锋.钛合金蜂窝壁板隔热性能试验研究［J］.南京航空航天大学学报,2016,48(1):16-20. XIE Zonghong,YUE Xishan,SUN Junfeng.Experimental study on thermal insulation performance of titanium honeycomb sandwich panels［J］.Journal of Nanjing University of Aeronautics and Astronautics,2016,48(1):16-20.(in Chinese)
    [7]
    RICE E J.Theoretical study of the acoustic impedance of orifices in the presence of a steady grazing flow［R］.NASA TMX-71903,1976.
    [8]
    景晓东,孙晓峰,吴景枢,等.基于声涡转化对穿孔板切向流效应的研究［J］.力学学报,2002,34(5):657-665. JING Xiaodong,SUN Xiaofeng,WU Jingshu,et al.An investigation of grazing flow effect on the impedance of a perforated plate based on sound-vortex interaction［J］.Chinese Journal of Theoretical and Applied Mechanics,2002,34(5):657-665.(in Chinese)
    [9]
    黄伟稀,侯宏,李斌,等.基于切向流效应的宽频带穿孔板声衬的研究［J］.航空动力学报,2012,27(4):770-776. HUANG Weixi,HOU Hong,LI Bing,et al.Broadband sound-absorption of perforated lining in the presence of grazing flow［J］.Journal of Aerospace Power,2012,27(4):770-776.(in Chinese)
    [10]
    QIU X,XIN B,WU L,et al.Investigation of straightforward impedance eduction method on single-degree-of-freedom acoustic liners［J］.Chinese Journal of Aeronautics,2018,31(12):2221-2233.
    [11]
    NORDIN P,SARIN S,RADEMAKER E.Development of new liner technology for application in hot stream areas of aero-engines［C］∥Proceedings of the 10th AIAA/CEAS Aeroacoustics Conference.Manchester:AIAA,2004:1-13.
    [12]
    ELNADY T,BODEN H,KONTIO T.Impedance of SDOF perforated liners at high temperatures［C］∥Proceedings of the 10th AIAA/CEAS Aeroacoustics Conference.Manchester:AIAA,2004:505-519.
    [13]
    KABRAL R,BODEN H,ELNADY T.Determination of liner impedance under high temperature and grazing Flow conditions［C］∥Proceedings of the 20th AIAA/CEAS Aeroacoustics Conference.Atlanta:AIAA,2014:1-10.
    [14]
    MERY F,PIOTY E,SEBBANEZ D,et al.Experimental assessment of the effect of temperature gradient across an aeroacoustic liner［J］.Journal of Aircraft,2019,56(5):1-13.
    [15]
    高翔,薛东文,燕群,等.涡扇发动机旋转声模态发生与测试试验研究［J］.科学技术与工程,2018,18(23):128-133. GAO Xiang,XUE Dongwen,YAN Qun,et al.Research on acoustic spinning mode synthesizer and measurement of turbofan engine method validating experiment［J］.Science Technology and Engineering,2018,18(23):128-133.(in Chinese)
    [16]
    GUESS W.Calculation of perforated plate liner parameters from specified acoustic resistance and reactance［J］.Journal of Sound and Vibration,1975,40(1):119-137.
    [17]
    YU J,KWAN H W,CHIOU S.Microperforate Plate Acoustic Property Evaluation［C］∥Proceedings of the 5th AIAA/CEAS Aeroacoustics Conference and Exhibit.Bellevue:AIAA,1999:547-557.
    [18]
    YU J,RUIZ M,KWAN H W.Validation of goodrich perforate liner impedance model using NASA Langley test data［C］∥Proceedings of the 14th AIAA/CEAS Aeroacoustics Conference.Vancouver:AIAA,2008:1-11.
    [19]
    QIU X H,DU L,JING X D.The cremer concept for annular ducts for optimum sound attenuation［J］.Journal of Sound and Vibration,2019,438(1):383-401.
    [20]
    王良锋,乔渭阳,纪良,等.轴流风扇/压气机管道周向声模态的测量［J］.航空动力学报,2014,29(4):917-926. WANG Liangfeng,QIAO Weiyang,JI Liang,et al.In-duct circumferential acoustic mode measurement of axial fan/compressor［J］ Journal of Aerospace Power,2014,29(4):917-926.(in Chinese)
    • Relative Articles
    • Supplements(0)
    • Cited By
  • 加载中

Catalog

    通讯作者: 陈斌, bchen63@163.com
    • 1. 

      沈阳化工大学材料科学与工程学院 沈阳 110142

    1. 本站搜索
    2. 百度学术搜索
    3. 万方数据库搜索
    4. CNKI搜索
    Get Citation
    PDF(2672.0KB)
    XML

    Article Metrics

    Article views (827) PDF downloads(667) Cited by()
    Proportional views
    Related

    Copyright © 《Journal of Aerospace Power》 All Rights Reserved.

    Supported by: Beijing Renhe Information Technology Co., Ltd.  

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return