基于边界层吹吸气技术的噪声控制研究
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- 英文论文题名：Airfoil noise reduction using boundary layer control
- 论文作者：李大伟 ; 李桂娟 ; 刘彦森
- 英文论文作者：LI Da-wei ; LI Gui-juan ; LIU Yan-sen ; Science and Technology on Underwater Test and Control Laboratory
- 年：2016
- 作者机构：水下测控技术重点实验室;
- 论文关键词：CFD ; 湍流动能 ; 吹吸气控制 ; 总声压级
- 英文论文关键词：CFD ; TKE ; Blow and Suction Control ; Over all sound pressure level
- 会议召开时间：2016-10-25
- 会议录名称：2016年中国造船工程学会水中目标特性学组学术交流会论文集
- 语种：中文
- 分类号：V214
- 学会代码：SXJS
- 会议名称：2016年中国造船工程学会水中目标特性学组学术交流会
- 会议地点：中国辽宁大连
- 主办单位：中国船舶重工集团公司第七六0研究所水中测控技术重点实验室
- 学会名称：《声学技术》编辑部
- 页数：9
- 文件大小：1481k
- 原文格式：D
- 会议级别：全国
摘要
针对增升机构在自由来流中的噪声特点,本文提出了利用计算流体力学耦合Ffowcs Williams-Hawkings声类比方程来获得模型声场及目标特性的数值研究方法,并提出了利用位于缝翼空腔内的边界层吹吸气技术来减小增升机构宽频噪声的控制手段。通过比较瞬时和平均流场可以发现,边界层吹吸气技术能够有效的稳定源自于缝翼前缘自由剪切层的涡量场及Lamb矢量场,并且能够用移除缝翼空腔内的二次分离流。计算结果显示,通过选择适当的控制参数,边界层吹吸气控制可以有效的抑制流场的压力颤振、速度颤振、湍流动能、涡量、Lamb矢量以及噪声等流场参数;该控制方法还明显改变了增升机构的远场目标特性。
The flow field and sound radiation of a three component high lift configuration in free-flight is investigated through computational fluid dynamics simulations in conjunction with a Ffowcs Williams-Hawkings acoustics solver. The boundary layer blow and suction control method on the inner slat surface has been used to suppress the broadband noise generated by the high lift configuration. By the comparison of instantaneous and time averaged results, the boundary layer control can effectively stabilize the shear layer that originates from the leading edge of the slat by removing the secondary separation flow on the inner slat surface. When the suitable boundary layer blow control parameters have been chosen, the computation results show the fluctuating of the velocity and pressure, turbulence kinetic energy, vorticity and Lamb vector in the slat cove are suppressed by the boundary layer control. The strong reduction of noise level in far-field and the steadiness of flow field in the slat cove demonstrate that the boundary layer control method is an effective way to control the noise of the high lift configuration.
The flow field and sound radiation of a three component high lift configuration in free-flight is investigated through computational fluid dynamics simulations in conjunction with a Ffowcs Williams-Hawkings acoustics solver. The boundary layer blow and suction control method on the inner slat surface has been used to suppress the broadband noise generated by the high lift configuration. By the comparison of instantaneous and time averaged results, the boundary layer control can effectively stabilize the shear layer that originates from the leading edge of the slat by removing the secondary separation flow on the inner slat surface. When the suitable boundary layer blow control parameters have been chosen, the computation results show the fluctuating of the velocity and pressure, turbulence kinetic energy, vorticity and Lamb vector in the slat cove are suppressed by the boundary layer control. The strong reduction of noise level in far-field and the steadiness of flow field in the slat cove demonstrate that the boundary layer control method is an effective way to control the noise of the high lift configuration.
引文
[1]Lockard,D.P.,and Lilley,G.M.,“The Airframe Noise Reduction Challenge,”NASA Langley Research Center TM-2004-213013,Hampton,VA,April 2004.
[2]Dobrzynski,W.,Nagakura,K.,Gehlhar,B.,and Buschbaum,A.,“Airframe noise studies on wings with deployed high-lift Devices,”AIAA Paper 1998-2337,4th AIAA/CEAS Aeroacoustics Conference,Toulouse,France,June 1998.
[3]Soderman,P.T.,Kafgeke,F.,Burnside,N.J.,Chadrasekharan,R.,Jaeger,S.M.,and Boudreau,J.,“Airframe noise study of a CRJ-700 aircraft model in the NASA Ames 7 by 10 foot wind tunnel No.1,”AIAA Paper 2002-2406,8th AIAA/CEAS Aeroacoustics Conference,Breckenridge,CO,June 2002.
[4]Guo,Y.P.,and Joshi,M.C.,“Noise characteristics of aircraft high lift systems,”AIAA Journal,Vol.41,No.7,July 2003,pp.1247-1256.
[5]Thilo Knacke and Frank Thiele.“Slat Noise Reduction using Steady Suction”.46th AIAA Aerospace Sciences Meeting and Exhibit,7-10 January 2008,Reno。
[6]Ffowcs Williams,J.E.and Hawkings,D.L.,“Sound Generated by Turbulence and Surfaces in Arbritary Motion”,Philosophical Transactions of the Royal Society,Vol.A264,No.1151,1969,pp.321-342.
[7]Peng Chen,Xin Zhang and David Angland.“Slat Noise Reduction using a Leading Edge Strip”.17th AIAA/CEAS Aeroacoustics Conference(32nd AIAA Aeroacoustics Conference)05-08 June2011,Portland,Oregon.Published by the American Institute of Aeronautics and Astronautics.
[8]Wang,M.,Freund,J.B.,and Lele,S.K.,“Computational Prediction of Flow-Generated Sound,”Annual Review of Fluid Mechanics,Vol.38,2006,pp.483–5129.
[9]QIU Sheng,SONG Wen-bin,LIU Hong.“Research on Influencing Factors of a Supercritical Airfoil Trailing Edge Noise”.Aeronautical Computing Technique.2012.42(2):52-59.
[10]Choudhari,M.,Lockard,D.P.,Macaraeg,M.G.,Singer,B.A.,Streett,C.L.,Neubert,G.R.,Stoker,R.W.,Underbrink,J.R.,Berkman,M.E.,Khorrami,M.R.,and Sadowski,S.S.,“Aeroacoustic Experiments in the Langley Low-Turbulence Pressure Tunnel,”NASA/TM 2002-211432,Feb.2002.
[11]D.Ang,L.Chen and J.Tu.Unsteady RANS Simulation of High Reynolds Number Trailing Edge Flow.15th Australasian Fluid Mechanics Conference.The University of Sydney,Australia 13-17December 2004.
[12]Haibao Hu and Baowei Song.(2008).“Research about the characteristic of drag reduction over riblets surface based on average velocity profile in the turbulent boundary layer”.Journal of aerospace power.24(5):1040-1047.
[13]Reinaldo M.Orselli,Julio R.Meneghini and Fabio Saltara.“Two and Three-Dimensional Simulation of Sound Generated by Flow Around a Circular Cylinder”.15th AIAA/CEAS Aeroacoustics Conference(30th AIAA Aeroacoustics Conference)11-13 May2009,Miami,Florida.
[14]Jenkins L N,Khorrami M R,Choudhari M.Characterization of unsteady flow structures near leading-edge slat:Part I.PIV measurements[J].AIAA paper,2004,2801:2004.
[15]Mc Ginley,C.B.,Ander,J.B.,and Spaid,F.W.,“Measurements of Reynolds stress profiles on a high-lift airfoil,”AIAA Paper1998-2620,16th Applied Aerodynamics Conference,Albuquerque,NM,June 1998.
[16]Mehdi R.Khorrami,Meelan M.Choudhari,and Luther N.Jenkins.Characterization of unsteady flow structures near leading-edge slat:Part ii.2d computations.AIAA Paper2004-2802,2004.
[17]West G S,Apelt C J.Measurements of Fluctuating Pressures and Forces on a Circular Cylinder in the Reynolds Number Range 104to 2.5×105.Journal Fluids and Structures,1993,7(3):227-244.
[18]G.M.Lilley.“The Prediction of airframe noise and comparison with experiment”.Journal of Sound and Vibration(2001)239(4),849-859.
[19]West G S,Apelt C J.Measurements of Fluctuating Pressures and Forces on a Circular Cylinder in the Reynolds Number Range 104to 2.5×105.Journal Fluids and Structures,1993,7(3):227-244.
[20]Revell J D,Prydz R A,Hays A P.Experimental Study of Airframe Noise vc.Drag Relationship for Circular Cylinders,Lockheed Report 28074,Final Report NASA Contract NAS1-14403,1977.
[21]Yokokawa,Y.,Imamura,T.,I.,Ura,H.,Uchida,H.,Ito,T.,and Yamamoto K.,“Studies on airframe noise generation at high-lift devices in relation to aerodynamic performances,”AIAA Paper2008-2960,14th AIAA/CEAS Aeroacoustics Conference,Vancouver,British Columbia,May 2008.
[2]Dobrzynski,W.,Nagakura,K.,Gehlhar,B.,and Buschbaum,A.,“Airframe noise studies on wings with deployed high-lift Devices,”AIAA Paper 1998-2337,4th AIAA/CEAS Aeroacoustics Conference,Toulouse,France,June 1998.
[3]Soderman,P.T.,Kafgeke,F.,Burnside,N.J.,Chadrasekharan,R.,Jaeger,S.M.,and Boudreau,J.,“Airframe noise study of a CRJ-700 aircraft model in the NASA Ames 7 by 10 foot wind tunnel No.1,”AIAA Paper 2002-2406,8th AIAA/CEAS Aeroacoustics Conference,Breckenridge,CO,June 2002.
[4]Guo,Y.P.,and Joshi,M.C.,“Noise characteristics of aircraft high lift systems,”AIAA Journal,Vol.41,No.7,July 2003,pp.1247-1256.
[5]Thilo Knacke and Frank Thiele.“Slat Noise Reduction using Steady Suction”.46th AIAA Aerospace Sciences Meeting and Exhibit,7-10 January 2008,Reno。
[6]Ffowcs Williams,J.E.and Hawkings,D.L.,“Sound Generated by Turbulence and Surfaces in Arbritary Motion”,Philosophical Transactions of the Royal Society,Vol.A264,No.1151,1969,pp.321-342.
[7]Peng Chen,Xin Zhang and David Angland.“Slat Noise Reduction using a Leading Edge Strip”.17th AIAA/CEAS Aeroacoustics Conference(32nd AIAA Aeroacoustics Conference)05-08 June2011,Portland,Oregon.Published by the American Institute of Aeronautics and Astronautics.
[8]Wang,M.,Freund,J.B.,and Lele,S.K.,“Computational Prediction of Flow-Generated Sound,”Annual Review of Fluid Mechanics,Vol.38,2006,pp.483–5129.
[9]QIU Sheng,SONG Wen-bin,LIU Hong.“Research on Influencing Factors of a Supercritical Airfoil Trailing Edge Noise”.Aeronautical Computing Technique.2012.42(2):52-59.
[10]Choudhari,M.,Lockard,D.P.,Macaraeg,M.G.,Singer,B.A.,Streett,C.L.,Neubert,G.R.,Stoker,R.W.,Underbrink,J.R.,Berkman,M.E.,Khorrami,M.R.,and Sadowski,S.S.,“Aeroacoustic Experiments in the Langley Low-Turbulence Pressure Tunnel,”NASA/TM 2002-211432,Feb.2002.
[11]D.Ang,L.Chen and J.Tu.Unsteady RANS Simulation of High Reynolds Number Trailing Edge Flow.15th Australasian Fluid Mechanics Conference.The University of Sydney,Australia 13-17December 2004.
[12]Haibao Hu and Baowei Song.(2008).“Research about the characteristic of drag reduction over riblets surface based on average velocity profile in the turbulent boundary layer”.Journal of aerospace power.24(5):1040-1047.
[13]Reinaldo M.Orselli,Julio R.Meneghini and Fabio Saltara.“Two and Three-Dimensional Simulation of Sound Generated by Flow Around a Circular Cylinder”.15th AIAA/CEAS Aeroacoustics Conference(30th AIAA Aeroacoustics Conference)11-13 May2009,Miami,Florida.
[14]Jenkins L N,Khorrami M R,Choudhari M.Characterization of unsteady flow structures near leading-edge slat:Part I.PIV measurements[J].AIAA paper,2004,2801:2004.
[15]Mc Ginley,C.B.,Ander,J.B.,and Spaid,F.W.,“Measurements of Reynolds stress profiles on a high-lift airfoil,”AIAA Paper1998-2620,16th Applied Aerodynamics Conference,Albuquerque,NM,June 1998.
[16]Mehdi R.Khorrami,Meelan M.Choudhari,and Luther N.Jenkins.Characterization of unsteady flow structures near leading-edge slat:Part ii.2d computations.AIAA Paper2004-2802,2004.
[17]West G S,Apelt C J.Measurements of Fluctuating Pressures and Forces on a Circular Cylinder in the Reynolds Number Range 104to 2.5×105.Journal Fluids and Structures,1993,7(3):227-244.
[18]G.M.Lilley.“The Prediction of airframe noise and comparison with experiment”.Journal of Sound and Vibration(2001)239(4),849-859.
[19]West G S,Apelt C J.Measurements of Fluctuating Pressures and Forces on a Circular Cylinder in the Reynolds Number Range 104to 2.5×105.Journal Fluids and Structures,1993,7(3):227-244.
[20]Revell J D,Prydz R A,Hays A P.Experimental Study of Airframe Noise vc.Drag Relationship for Circular Cylinders,Lockheed Report 28074,Final Report NASA Contract NAS1-14403,1977.
[21]Yokokawa,Y.,Imamura,T.,I.,Ura,H.,Uchida,H.,Ito,T.,and Yamamoto K.,“Studies on airframe noise generation at high-lift devices in relation to aerodynamic performances,”AIAA Paper2008-2960,14th AIAA/CEAS Aeroacoustics Conference,Vancouver,British Columbia,May 2008.