风扇前传噪声及声衬特性研究
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摘要
为了探究航空发动机的风扇噪声,通过试验研究了缩尺风扇前传噪声在不同转速工况下的频谱特性和周向模态特性,并对所设计的环形声衬降噪效果进行了验证。研究结果表明,基于试验测量数据分析得到的频谱特性和周向模态特性满足转静干涉噪声理论。随着转速的提高,风扇纯音噪声越显著,高转速工况下纯音噪声的能量约占风扇前传噪声的85%。在所研究的工况范围内,该声衬对目标频率及模态均有显著的降噪效果,且在85%转速工况时的纯音降噪效果最优,其主模态的传声损失约为59dB。该声衬对于设计频率附近的宽频噪声也有一定降噪效果,在85%转速时的宽频噪声平均传递损失约为3dB。
To analyze the fan noise of an aviation engine,spectrum characteristic and circular modal characteristic for forward noise of the scaled fan at different rotational speeds were investigated experimentally. And noise reduction performance of the acoustic liner was also verified. Results indicate that the frequency spectrum and circular mode decomposition results of the measured data meet the theory of rotor-stator interference. The tonal noise becomes larger with the rotational speed increasing,which amounts about 85% of forward fan noise energy at the high rotational speed. For the cases studied in this paper,the acoustic liner has significant effect for the target blade passing frequency and mode,and its optimal transmission loss of 59 dB for the dominant mode can be achieved at 85% rotational speed. Also,the acoustic liner has certain broadband noise reduction characteristic,average transmission loss of broadband noise obtained by the acoustic liner is about 3 dB at 85% rotational speed.
To analyze the fan noise of an aviation engine,spectrum characteristic and circular modal characteristic for forward noise of the scaled fan at different rotational speeds were investigated experimentally. And noise reduction performance of the acoustic liner was also verified. Results indicate that the frequency spectrum and circular mode decomposition results of the measured data meet the theory of rotor-stator interference. The tonal noise becomes larger with the rotational speed increasing,which amounts about 85% of forward fan noise energy at the high rotational speed. For the cases studied in this paper,the acoustic liner has significant effect for the target blade passing frequency and mode,and its optimal transmission loss of 59 dB for the dominant mode can be achieved at 85% rotational speed. Also,the acoustic liner has certain broadband noise reduction characteristic,average transmission loss of broadband noise obtained by the acoustic liner is about 3 dB at 85% rotational speed.
引文
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[15]Tyler J M,Sofrin T G.Axial Flow Compressor Noise Studies[J].SAE Trans,1962,70:309-331.
[16]Holste F,Neise W.Noise Source Identification in a Propfan Model by Means of Acoustical near Field Measurements[J].Journal of Sound&Vibration,1997,203(4):641-665.
[17]Tapken U,Bauers R,Arnold F,et al.Turbomachinery Exhaust Noise Radiation Experiments,Part 2:In-Duct and Far-Field Mode Analysis[R].AIAA 2008-2858.
[18]Xu J,Xu Y,Liu C H,et al.Numerical Investigation of Inlet Acoustic Liner Optimization Based on RSM[C].Shanghai:2017 Global Power and Propulsion Forum,2017.
[2]乔渭阳.航空发动机气动声学[M].北京:北京航空航天大学出版社,2010.
[3]王良锋,乔渭阳,纪良,等.风扇进口噪声预测模型的改进[J].推进技术,2015,36(2):226-231.(WANG Liang-feng,QIAO Wei-yang,JI Liang,et al.An Improved Prediction Model for Fan Inlet Noise[J].Journal of Propulsion Technology,2015,36(2):226-231.)
[4]Achunche I,Astley J,Sugimoto R,et al.Prediction of Forward Fan Noise Propagation and Radiation from Intakes[R].AIAA 2009-3239.
[5]Schuster B,Lieber L,Vavalle A.Optimization of a Seamless Inlet Liner Using an Empirically Validated Prediction Method[R].AIAA 2010-3824.
[6]季川子,宋文滨.基于时域LEE方法的发动机进气道声衬降噪优化[J].科学技术与工程,2014,14(4):143-149.
[7]Sun X,Wang X,Du L,et al.A New Model for the Prediction of Turbofan Noise with the Effect of Locally and Non-Locally Reacting Liners[J].Journal of Sound&Vibration,2008,316(1):50-68.
[8]李志彬,王叙理,王晓宇,等.基于传递单元方法的局域反应声衬设计与实验研究[J].航空学报,2018,39(8).
[9]许坤波,乔渭阳,霍施宇,等.风扇单音噪声模态识别及其误差传递特性研究[J].推进技术,2018,39(1):185-195.(XU Kun-bo,QIAO Wei-yang,HUOShi-yu,et al.Research of Mode Identification and Error Transfer Property on Fan Tonal Noise[J].Journal of Propulsion Technology,2018,39(1):185-195.)
[10]仝帆,乔渭阳,王良锋,等.风扇湍流宽频噪声特性的数值计算分析[J].航空动力学报,2015,30(2):455-462.
[11]徐珺,李晓东.高声强下多狭缝共振腔的吸声性能[J].航空动力学报,2016,31(3):548-554.
[12]Tapken U,Enghardt L.Optimisation of Sensor Arrays for Radial Mode Analysis in Flow Ducts[R].AIAA 2006-2638.
[13]Munjal M L.Acoustics of Ducts and Mufflers[M].New York:John Wiley&Sons,1997.
[14]Enghardt L,Tapken U,Neise W,et al.Turbine Blade/Vane Interaction Noise:Acoustic Mode Analysis Using In-Duct Sensor Rakes[R].AIAA 2001-2153.
[15]Tyler J M,Sofrin T G.Axial Flow Compressor Noise Studies[J].SAE Trans,1962,70:309-331.
[16]Holste F,Neise W.Noise Source Identification in a Propfan Model by Means of Acoustical near Field Measurements[J].Journal of Sound&Vibration,1997,203(4):641-665.
[17]Tapken U,Bauers R,Arnold F,et al.Turbomachinery Exhaust Noise Radiation Experiments,Part 2:In-Duct and Far-Field Mode Analysis[R].AIAA 2008-2858.
[18]Xu J,Xu Y,Liu C H,et al.Numerical Investigation of Inlet Acoustic Liner Optimization Based on RSM[C].Shanghai:2017 Global Power and Propulsion Forum,2017.
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