基于流道优化的局部进气高速涡轮机气动噪声控制实验研究
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摘要
动静叶干涉是涡轮机气动噪声的主要来源之一。针对局部进气高速涡轮机,为了抑制由动静叶干涉引起的单音辐射噪声,提出了增大喷嘴的几何出气角、喷嘴下俯、喷嘴单侧修型和增大动静叶间距的流道优化设计方法以控制涡轮机内的流动状况进而降低噪声辐射,并设计了涡轮机气动噪声测试实验台,测量并分析了优化措施的降噪效果。结果表明,涡轮机流道优化设计方法有效抑制了单音辐射噪声,使各个转子谐频处的离散噪声均得到降低,并在3125Hz处实现了最高达7d B的降噪量;在大部分的三分之一倍频程内,优化设计的涡轮机噪声幅值低于原始设计的涡轮机,最大降噪量为2.1d B。
The rotor-stator interaction is one of the main sources of turbomachine' s aerodynamic noise.For high-speed partial admission turbine,the fluid path optimal design methods including increasing the geometric exit flow angle of nozzle,nozzle pitchdown,sigle-side modification for nozzle,and increasing the distance between rotor and stator were proposed to improve the flow state to control the discrete noise induced by rotor-stator interaction. The test rig for turbine acoustic measurement was designed,and the noise reduction performance was measured and analysed for these optimal design methods. The results show that the distinctive noise is controlled significantly by the adopted optimal design methods,the sound pressure level at every rotating harmonic frequency is decreased,and the maximum reduction is about 7d B at 3125 Hz. In most 1/3 octive frequencies,the noise amplitude is lower for optimal turbine,and the maximum decrease is 2.1d B.
The rotor-stator interaction is one of the main sources of turbomachine' s aerodynamic noise.For high-speed partial admission turbine,the fluid path optimal design methods including increasing the geometric exit flow angle of nozzle,nozzle pitchdown,sigle-side modification for nozzle,and increasing the distance between rotor and stator were proposed to improve the flow state to control the discrete noise induced by rotor-stator interaction. The test rig for turbine acoustic measurement was designed,and the noise reduction performance was measured and analysed for these optimal design methods. The results show that the distinctive noise is controlled significantly by the adopted optimal design methods,the sound pressure level at every rotating harmonic frequency is decreased,and the maximum reduction is about 7d B at 3125 Hz. In most 1/3 octive frequencies,the noise amplitude is lower for optimal turbine,and the maximum decrease is 2.1d B.
引文
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[20]纪良,乔渭阳,王良峰,等.普通室内机翼尾缘噪声降噪的实验研究[J].推进技术,2015,36(5):703-712.(JI Liang,QIAO Wei-yang,WANG Liangfeng,et al.Experimental Investigation of Airfoil Trailing-Edge Noise Reduction in a Normal Indoor Test Bed[J].Journal of Propulsion Technology,2015,36(5):703-712.)
[2]Lavin S P,Ho P Y,Chamberlin R.Measurements and Predictions of Energy Efficient Engine Noise[R].AIAA84-2284.
[3]Lars Enghardt,Antoine Moreau,Ulf Tapken,et al.Radial Mode Decomposition in the Outlet of a LP TurbineEstimation of the Relative Importance of Broadband Noise[R].AIAA 2009-2186.
[4]Tyler J M,Sofrin T G.Axial Flow Compressor Noise Studies[J].SAE Transactions,1962,70:309-332.
[5]Lowson M V.Reduction of Compressor Noise Radiation[J].Journal of the Acoustical Society of Sound and Vibration,1967,6(2):230-236.
[6]Cooper A J,Peake N.Rotor-Stator Interaction Noise in Swirling Flow:Stator Sweep and Lean Effects[J].AIAA Journal,2006,44(5):981-991.
[7]Woodward R P,Gazzaniga J A,Bartos L J,et al.Acoustic Benefits of Stator Sweep and Lean for a High Tip Speed Fan[R].AIAA 2002-1034.
[8]Nallasamy M,Envia E.Computaion of Far-Field Tone Noise Levels for Radial and Swept&Leaned Stators[R].AIAA 99-1865.
[9]Schulten J B H M.Sound Generated by Rotor Wakes Interacting with a Leaned Vane Stator[J].AIAA Journal,1982,20(10):1352-1358.
[10]Dominik Broszat,Fritz Kennepohl,Ulf Tapken,et al.Validation of an Acoustically 3-D Designed Turbine Exit Guide Vane[R].AIAA 2010-3806.
[11]Waitz I A,Brookfield J M,Sell J,et al.Preliminary Assessment of Wake Management Strategies for Reduction of Turbomachinery Fan Noise[J].Journal of Propulsion and Power,1996,12(5):958-966.
[12]Matthew D Langford,Christopher M Minton,Wing F Ng,et al.Fan Flow Control for Noise Reduction Part 2:Investigation of Wake-Filling Techniques[R].AIAA2005-3026.
[13]Steger M,Michel U,Ashcroft G,et al.Turbofan Tone Noise Reduction by Flow-Induced Unsteady Blade Forces[J].Active Flow Control II,2010,108:157-170.
[14]Steger M,Michel U,Ashcroft G,et al.Tone Noise Reduction of a Turbofan Engine by Additional Aerodynamical Blade Forces[R].AIAA 2010-3982.
[15]吴亚东.带尾缘吹气的叶轮机械内部流动和气动噪声问题的研究[D].上海:上海交通大学,2009.
[16]Lowson M V.The Sound Field for Singulanties in Motion[C].London:Proceeding of the Royal Society in London.Series A,1965,286:559-572.
[17]Lowson M V.Theoretical Analysis of Compressor Noise[J].The Journal of the Acoustical Society of America,1970,47(1B):371-386.
[18]Fukano T,Kodama Y,Sendoo Y.Noise Generated by Low Pressure Axial Flow Fans I:Modelling of the Turbulent Noise[J].Journal of Sound and Vibration,1977,50(1):63-74.
[19]Fukano T,Kodama Y,Sendoo Y.Noise Generated by Low Pressure Axial Flow Fans II:Effects of Number of Blades,Chord Length and Camber of Blade[J].Journal of Sound and Vibration,1977,50(1):75-88.
[20]纪良,乔渭阳,王良峰,等.普通室内机翼尾缘噪声降噪的实验研究[J].推进技术,2015,36(5):703-712.(JI Liang,QIAO Wei-yang,WANG Liangfeng,et al.Experimental Investigation of Airfoil Trailing-Edge Noise Reduction in a Normal Indoor Test Bed[J].Journal of Propulsion Technology,2015,36(5):703-712.)