Fluid Mechanics and Flight Mechanics

Experiment on acoustic impedance of large-thickness perforated plate

  • Chuanyang LIU ,
  • Xiaoyu WANG ,
  • Guangyu ZHANG ,
  • Xiaofeng SUN
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  • 1.Research Institute of Aero-Engine,Beihang University,Beijing 102206,China
    2.School of Energy and Power Engineering,Beihang University,Beijing 102206,China

Received date: 2024-11-04

  Revised date: 2024-12-23

  Accepted date: 2025-02-07

  Online published: 2025-02-12

Supported by

Aero Engine and Gas Turbine Basic Science Center Project (P2022-B-Ⅱ-013-001);National Natural Science Foundation of China(52476024);Taihang Laboratory Funding Project (A2053)

Abstract

Over-the-rotor liner and soft vans have received much attention as new noise reduction means, and large-thickness perforated plate is a feasible structural form for realizing these two noise reduction means. Therefore, the acoustic impedance characteristics of large-thickness perforated plates are investigated. Based on the impedance tube and flow tube test platforms, the acoustic impedance characteristics of large-thickness perforated plates are experimentally investigated in the absence and presence of grazing flow, and the applicability of the Beihang model to the prediction of acoustic impedance for large thickness perforated plates is explored. Under no grazing flow conditions, the test acoustic impedance of a solid perforated plate with a thickness of 8 mm shows good linear characteristics, and the Beihang model is able to accurately predict the acoustic impedance of the large-thickness perforated plate. Meanwhile, a honeycomb-cavity sandwich perforated plate structure is proposed for the case where the static blade has a hollow structure. Measurement results show that the acoustic impedance of this structure is mainly provided by the perforated plates on both sides, while the honeycomb-cavity in the middle provides only a small portion of the acoustic impedance. Under grazing flow conditions, the applicability of the Beihang model to the prediction of acoustic impedance for large-thickness perforated plates is investigated in terms of both acoustic impedance prediction accuracy and transmission loss. When the grazing flow velocities are 10 m/s and 20 m/s, the Beihang model can still accurately predict the acoustic impedance of large-thickness perforated plates. As the grazing flow velocity increases, the effect of plate thickness on vortex shedding in small holes begins to become apparent. When the grazing flow velocities reach 40 m/s and 60 m/s, the prediction error of the Beihang model based on the fitting of vortex shedding strength of the thin plate on the acoustic impedance of the large-thickness perforated plate starts to increase. However, in terms of the transmission loss, the transmission loss curves predicted by the Beihang model show a similar trend with that of the experimentally measured transmission loss curve. It can be seen that the Beihang model still provides valuable guiding for the engineering application of large-thickness perforated plates.

Cite this article

Chuanyang LIU , Xiaoyu WANG , Guangyu ZHANG , Xiaofeng SUN . Experiment on acoustic impedance of large-thickness perforated plate[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2025 , 46(14) : 331486 -331486 . DOI: 10.7527/S1000-6893.2025.31486

References

[1] SUTLIFF D L, BOZAK R F, JONES M G, et al. Investigations of three over-the-rotor liner concepts at various technology readiness levels[J]. International Journal of Aeroacoustics202120(5/6/7): 826-866.
[2] HUGHES C, GAZZANIGA J. Effect of two advanced noise reduction technologies on the aerodynamic performance of an ultra high bypass ratio fan: AIAA-2009-3139[R]. Reston: AIAA, 2009.
[3] JONES M G, HOWERTON B M. Evaluation of novel liner concepts for fan and airframe noise reduction: AIAA-2016-2787[R]. Reston: AIAA, 2016.
[4] SUN Y, WANG X Y, DU L, et al. On the flow-acoustic coupling of fan blades with over-the-rotor liner[J]. Journal of Fluid Mechanics2022941: A67.
[5] ELLIOTT D, WOODWARD R, PODBOY G. Acoustic performance of novel fan noise reduction technologies for a high bypass model turbofan at simulated flight conditions: AIAA-2009-3140[R]. Reston: AIAA, 2009.
[6] GAZELLA M, TAKAKURA T, SUTLIFF D L, et al. Evaluating the acoustic benefits of over-the-rotor acoustic treatments installed on the advanced noise control fan: AIAA-2017-3872[R]. Reston: AIAA, 2017.
[7] SHEN Z H, WANG X Y, SUN Y, et al. Three-dimensional effects of cascade perforations on rotor-stator interaction noise[J]. Journal of Fluid Mechanics2022952: A7.
[8] GUESS A W. Calculation of perforated plate liner parameters from specified acoustic resistance and reactance[J]. Journal of Sound and Vibration197540(1): 119-137.
[9] CUMMINGS A. The effects of grazing turbulent pipe-flow on the impedance of an orifice?[J]. Acta Acustica United with Acustica198661(4): 233-242.
[10] 辛博. 切向流对声衬声阻抗的影响及声衬表面非稳定波机理的研究[D]. 北京: 北京航空航天大学, 2019: 79-81.
  XIN B. Investigation of grazing flow effects on the acoustic liner impedance and the mechanism of hydrodynamic instability over a liner[D]. Beijing: Beihang University, 2019: 79-81 (in Chinese).
[11] TEMIZ M A, LOPEZ ARTEAGA I, EFRAIMSSON G, et al. The influence of edge geometry on end-correction coefficients in micro perforated plates[J]. The Journal of the Acoustical Society of America2015138(6): 3668-3677.
[12] TESTUD P, MOUSSOU P, HIRSCHBERG A, et al. Noise generated by cavitating single-hole and multi-hole orifices in a water pipe[J]. Journal of Fluids and Structures200723(2): 163-189.
[13] SEYBERT A F. Two-sensor methods for the measurement of sound intensity and acoustic properties in ducts[J]. The Journal of the Acoustical Society of America198883(6): 2233-2239.
[14] 廖峻锋, 景晓东, 邱祥海, 等. 新型航空金属丝网声衬掠流特性实验研究[J]. 航空学报202344(21): 528537.
  LIAO J F, JING X D, QIU X H, et al. Experimental study on grazing flow characteristics of a new aeronautical wire mesh acoustic liner[J]. Acta Aeronautica et Astronautica Sinica202344(21): 528537 (in Chinese).
[15] INGARD U. Influence of fluid motion past a plane boundary on sound reflection, absorption, and transmission[J]. Acoustical Society of America Journal195931(7): 1035-1036.
[16] MYERS M K. On the acoustic boundary condition in the presence of flow?[J]. Journal of Sound and Vibration198071(3): 429-434.
[17] JING X D, PENG S, SUN X F. A straightforward method for wall impedance eduction in a flow duct?[J]. The Journal of the Acoustical Society of America2008124(1): 227-234.
[18] QIU X H, XIN B, JING X D. Straightforward impedance eduction method for non-grazing incidence wave with multiple modes[J]. Journal of Sound and Vibration2018432: 1-16.
[19] DAI W, WANG X L, WANG X Y, et al. Acoustic scattering mechanism and noise attenuation of circumferentially non-uniform liner with spectral-wave guide method[J]. Chinese Journal of Aeronautics202336(9): 63-78.
[20] MORFEY C L. Sound transmission and generation in ducts with flow?[J]. Journal of Sound and Vibration197114(1): 37-55.
[21] 杜功焕, 朱哲民, 龚秀芬. 声学基础[M]. 3版. 南京: 南京大学出版社, 2012: 166-167.
  DU G H, ZHU Z M, GONG X F. Fundamentals of acoustic[M]. 3rd ed. Nanjing: Nanjing University Press, 2012: 166-167 (in Chinese).
[22] KUBO G, ISHII T, NAGAI K, et al. Evaluation of nonlinear impedance models for acoustic liners under the normal incident sound wave: AIAA-2024-3367[R]. Reston: AIAA, 2024.
[23] 石炜昊. 针对声衬切向流和高声强效应的声阻抗提取实验方法研究[D]. 北京: 北京航空航天大学, 2024: 75-112.
  SHI W H. An investigation of impedance eduction technique for measuring acoustic liners subjected to grazing flow and high-intensity sound[D]. Beijing: Beihang University, 2024: 75-112 (in Chinese).
[24] SHI W H, JING X D. An uncertainty investigation for liner impedance eduction methods[J]. Chinese Journal of Aeronautics202437(3): 49-59.
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