基于DES模型翼型尾缘气动噪声数值研究
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摘要
为获得高气动性能、低噪声水平的风力机翼型,基于分离涡模拟(DES)模型和声学类比方程建立混合模拟法预测噪声,以S809翼型为基础翼型进行数值模拟,研究尾缘厚度及其分配比对风力机翼型气动性能及气动噪声的影响规律。通过样条函数参数化处理针对翼型S809尾缘改型进行气动噪声计算。结果表明:钝尾缘翼型与原始翼型相比,气动性能得到明显改善,当尾缘厚度为1. 5%c的改型翼型,其升阻比高于其他尾缘厚度的改型翼型升阻比;在不同攻角及不同尾缘厚度分配比下翼型噪声呈现明显的偶极子形状;钝尾缘翼型能够导致气动噪声增加,但其中尾缘厚度为1. 5%c,尾缘分配比为1∶3的钝尾缘翼型气动噪声增加较小。
In order to obtain the wing type of high aerodynamic performance and low noise level,hybrid simulation method for predicting noise based on DES model and acoustic analogy equation is used,and the numerical simulation of airfoil based on airfoil S809 is carried out to study on the influences of trailing edge thickness and its distribution ratio on aerodynamic performance and aerodynamic noise of airfoil.Aerodynamic noise calculation for airfoil S809 with tail edge modifications is performed by spline function parameterization. Results indicate: The aerodynamic performance of the blunt trailing edge airfoil is significantly improved compared with that of the original airfoil. The modified airfoil with the 1. 5% c thickness of the trailing edge has higher lift drag ratio than those of other trailing edge thicknesses. With different angle of attack and different trailing edge thickness distribution,the apparent dipole shape of the lower airfoil noise is presented. The airfoil with blunt trailing edge can increase the aerodynamic noise,but the aerodynamic noise of the blade is relatively low with the trailing edge thickness of 1. 5% c,and the trailing edge ratio of 1∶ 3.
In order to obtain the wing type of high aerodynamic performance and low noise level,hybrid simulation method for predicting noise based on DES model and acoustic analogy equation is used,and the numerical simulation of airfoil based on airfoil S809 is carried out to study on the influences of trailing edge thickness and its distribution ratio on aerodynamic performance and aerodynamic noise of airfoil.Aerodynamic noise calculation for airfoil S809 with tail edge modifications is performed by spline function parameterization. Results indicate: The aerodynamic performance of the blunt trailing edge airfoil is significantly improved compared with that of the original airfoil. The modified airfoil with the 1. 5% c thickness of the trailing edge has higher lift drag ratio than those of other trailing edge thicknesses. With different angle of attack and different trailing edge thickness distribution,the apparent dipole shape of the lower airfoil noise is presented. The airfoil with blunt trailing edge can increase the aerodynamic noise,but the aerodynamic noise of the blade is relatively low with the trailing edge thickness of 1. 5% c,and the trailing edge ratio of 1∶ 3.
引文
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[21] SINGER B A,BRENTNER K S,LOCKARD D P,et al. Simula-tion of acoustic scattering from a trailing edge[J]. Journal ofSound&Vibration,2000,23(3):541-560.
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[24] Rupprecht C E,Hamir A N,Johnston D H,et al. Efficacy of aVaccinia-Rabies Glycoprotein Recombinant Virus Vaccine inRaccoons(Procyon lotor)[J]. Reviews Infectious Diseases,1988,10 Suppl 4(Supplement 4):S803-9,
[25]刘杰平,陈培,张卫民.后缘加厚方式对典型风力机翼型气动性能的影响[J].太阳能学报,2009,30(8):1092-1096.LIU Jie-ping,CHEN Pei,ZHANG Wei-min. The influence of thetrailing edge thickening mode on the aerodynamic performance oftypical wind airfoil[J]. Acta Energiae Solaris Sinica,2009,30(8):1092-1096.
[26] SOMERS D M. Design and experimental results for the S809 airfoil[R]. Pennsylvania:National Renewable Energy Laboratory,1997.
[27] HOWE M S. Noise produced by a sawtooth trailing edge[J]. A-coustical Society of America Journal,1991,90(1):482-487.
[2]李春,叶舟,高伟,等.现代陆海风力机计算与仿真[M].上海:上海科学技术出版社,2012.LI Chun,YE Zhou,GAO Wei,et al. Calculation and simulation ofmodern land-sea wind turbine[M]. ShangHai:Shanghai Scienceand Technology publishers,2012.
[3] LI Jun-feng,CAI Feng-bo,QIAO Li-ming,et al. 2014 China windpower review and outlook[R]. Chinese Renewable Energy Indus-tries Association,2014.
[4] JACKSON K,ZUTECK M,VAN DAM C P,et al. Innovative designapproaches for large wind turbine blades[J]. Wind Energy,2005,8(2):141-171.
[5] Ramsay R F,Hoffman M J,Gregorek G M. Effects of grit roughnessand pitch oscillation on the S809 airfoil[R]. National RenewableEnergy Lab,1996.
[6] YANG Q,CHEN G Q,ZHAO Y H,et al. Energy cost and green-house gas emissions of a Chinese wind farm[J]. Procedia Environ-mental Sciences,2011(5):25-28.
[7] HAO Wen-xing,LI Chun,YE Zhou,et al. Computational study onwind turbine airfoils based on active control for deformable flaps[J]. Journal of Mechanical Science&Technology,2017,31(2):565-575.
[8] NII Y,GOTANDA T. Aerodynamic noise source localization sys-tem for wind turbine rotor blade[J]. Journal of Mechanical Engi-neering Laboratory,1996,50:88-97.
[9]胡昊.风力机叶片气动噪声特性与降噪方法研究[M].北京:中国水利水电出版社,2016.HU Hao. Research on characteristic and noise reduction method ofaerodynamic noise from wind turbine blades[M]. Beijing:ChinaWater&Power Press,2016.
[10] WAGNER D I S,BAREID I R,GUIDATI D I G. Wind turbinenoise[M]. Springer Berlin Heidelberg,1996.
[11]李东旭,梁鹏程,戴龙侠,等.大型风电叶片翼型气动噪声数值模拟研究[J].大功率变流技术,2017(2):42-46.LI Dong-xu,LIANG Peng-cheng,DAI Long-xia,et al. Numericalsimulation of aerodynamic noise generated by large wind bladeairfoil[J]. High Power Converter Technology,2017(2):42-46.
[12] ARANA M,MACHN J,MARTN R S. Measurement and analy-sis of mechanical noise in wind turbines[J]. Acoustics Austral-ia,2015,43(3):1-8.
[13]戈尔茨坦.气动声学[M].北京:国防工业出版社,2014.GOLDSTEIN. Acoustics[M] Beijing:National Defense IndustryPress,2014.
[14] Meyer R,Hage W,Bechert D W,et al. Separation Control by Self-Activated Movable Flaps[J]. AIAA Journal,2007,45(1):191-199.
[15] BROOKS T F,POPE D S,MARCOLINI M A. Airfoil self-noiseand prediction[J]. NASARP-1218,1989.
[16]许影博,李晓东.锯齿型翼型尾缘噪声控制实验研究[J].空气动力学学报,2012,30(1):120-124.XU Ying-bo,LI Xiao-dong. An experiment study of the serratededge noise[J]. Acta Aerodynamica Sinica,2012,30(1):120-124.
[17]刘雄,陈严,叶枝全.增加风力机叶片翼型后缘厚度对气动性能的影响[J].太阳能学报,2006,27(5):489-495.LIU Xiong,CHEN Yan,YE Zhi-quan. Effect of increasing windturbine blade airfoil trailing edge thickness on aerodynamic per-formance[J]. Acta Energiae Solaris Sinica,2006,27(5):489-495.
[18] EWERT R,SCHRDER W. On the simulation of trailing edgenoise with a hybrid LES/APE method[J]. Journal of Sound&Vibration,2004,27(3):509-524.
[19] YU J.,JOSHI M. On sound radiation from the trailing edge of anisolated airfoil in a uniform flow[J]. AIAA Journal,1979,83(4):701-705.
[20]梁俊宇.涡轮叶片气膜冷却孔绕流的实验与数值模拟研究[D].北京:华北电力大学,2012.LIAN Jun-yu. Experimental and numerical investigation of flow a-round film cooling hole of turbine blade[D]. Beijing:North ChinaElectric Power University,2012.
[21] SINGER B A,BRENTNER K S,LOCKARD D P,et al. Simula-tion of acoustic scattering from a trailing edge[J]. Journal ofSound&Vibration,2000,23(3):541-560.
[22] SPALART P R,JOU W H,STRELETS M,et al. Comments on thefeasibility of LES for wings,and on a Hybrid RANS/LES ap-proach[C]//Advances in DNS/LES,1997.
[23] WILLIAMS J E,HALL L H. Aerodynamic sound generation byturbulent flow in the vicinity of a scattering half plane[J]. Jour-nal of Fluid Mechanics,1970,40(4):657-670.
[24] Rupprecht C E,Hamir A N,Johnston D H,et al. Efficacy of aVaccinia-Rabies Glycoprotein Recombinant Virus Vaccine inRaccoons(Procyon lotor)[J]. Reviews Infectious Diseases,1988,10 Suppl 4(Supplement 4):S803-9,
[25]刘杰平,陈培,张卫民.后缘加厚方式对典型风力机翼型气动性能的影响[J].太阳能学报,2009,30(8):1092-1096.LIU Jie-ping,CHEN Pei,ZHANG Wei-min. The influence of thetrailing edge thickening mode on the aerodynamic performance oftypical wind airfoil[J]. Acta Energiae Solaris Sinica,2009,30(8):1092-1096.
[26] SOMERS D M. Design and experimental results for the S809 airfoil[R]. Pennsylvania:National Renewable Energy Laboratory,1997.
[27] HOWE M S. Noise produced by a sawtooth trailing edge[J]. A-coustical Society of America Journal,1991,90(1):482-487.