直升机尾桨噪声特性研究
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摘要
随着直升机日益深入研究和广泛应用,直升机噪声的大小已经成为衡量其质量和性能的重要标志之一。尾桨是直升机的主要噪声源之一,研究尾桨噪声特性对控制直升机的噪声水平具有重要意义。
本文以直升机尾桨噪声为研究对象,通过对尾桨噪声的机理进行分析,建立了孤立尾桨噪声的计算模型,采用三维非定常面元法计算桨叶表面压力,利用Farassat 1a公式对孤立尾桨的噪声特性进行了数值模拟。构建了一套试验系统,在消声室里进行了孤立尾桨噪声、尾桨与涡干扰噪声的试验研究,测量了不同转速、不同桨叶片数、不同总距角、不同涡干扰角以及不同剪刀角下的尾桨噪声特性。试验结果表明:尾桨叶与涡相互作用时噪声明显增加,而且在尾桨叶与涡正交情况下产生的噪声最大;剪刀式尾桨对尾桨噪声具有调频作用,能够降低尾桨的噪声水平。最后将孤立尾桨噪声的计算结果和试验结果进行了对比分析,验证了计算模型。这些结论为预估直升机的尾桨噪声和指导降低噪声尾桨设计提供了依据。
With wide applications of helicopters, helicopter noise level has become one of substantial indexes of helicopter performance and acceptability. Helicopter tail rotor is a major source of the noise; therefore investigation of tail rotor noise characteristics becomes very valuable and important to control the helicopter noise level.
This article focuses on researching the helicopter tail rotor noise and analyzing its mechanism to establish the computation model of the isolated tail rotor noise. The three-dimensional unsteady panel method is adopted to calculate the pressure on the surface of the blades and the Farassat la formula is used to simulate the numerical value of the isolated tail rotor noise property. A set of test system has been established, through the experiment of the isolated tail rotor noise, the tail rotor and the vortex interference which are carried out in the anechoic chamber, Test parameters include rotor speed, number of blades, blade pitch angle, vortex interference angle and tail rotor blade azimuth arrangement. The result shows that the noise is markedly increased when the tail blades interacted with the vortex, the noise level under the orthogonal interference is highest.Besides, the scissors-type arrangement of tail rotor can change the noise spectrum and lower the noise level. Last, by contrastive analysis between the results of the isolated tail rotor noise and the experiment, the computation model is being proven. These conclusions can be used to estimate the helicopter tail rotor noise and help to guide tail rotor noise reduction design.
本文以直升机尾桨噪声为研究对象,通过对尾桨噪声的机理进行分析,建立了孤立尾桨噪声的计算模型,采用三维非定常面元法计算桨叶表面压力,利用Farassat 1a公式对孤立尾桨的噪声特性进行了数值模拟。构建了一套试验系统,在消声室里进行了孤立尾桨噪声、尾桨与涡干扰噪声的试验研究,测量了不同转速、不同桨叶片数、不同总距角、不同涡干扰角以及不同剪刀角下的尾桨噪声特性。试验结果表明:尾桨叶与涡相互作用时噪声明显增加,而且在尾桨叶与涡正交情况下产生的噪声最大;剪刀式尾桨对尾桨噪声具有调频作用,能够降低尾桨的噪声水平。最后将孤立尾桨噪声的计算结果和试验结果进行了对比分析,验证了计算模型。这些结论为预估直升机的尾桨噪声和指导降低噪声尾桨设计提供了依据。
With wide applications of helicopters, helicopter noise level has become one of substantial indexes of helicopter performance and acceptability. Helicopter tail rotor is a major source of the noise; therefore investigation of tail rotor noise characteristics becomes very valuable and important to control the helicopter noise level.
This article focuses on researching the helicopter tail rotor noise and analyzing its mechanism to establish the computation model of the isolated tail rotor noise. The three-dimensional unsteady panel method is adopted to calculate the pressure on the surface of the blades and the Farassat la formula is used to simulate the numerical value of the isolated tail rotor noise property. A set of test system has been established, through the experiment of the isolated tail rotor noise, the tail rotor and the vortex interference which are carried out in the anechoic chamber, Test parameters include rotor speed, number of blades, blade pitch angle, vortex interference angle and tail rotor blade azimuth arrangement. The result shows that the noise is markedly increased when the tail blades interacted with the vortex, the noise level under the orthogonal interference is highest.Besides, the scissors-type arrangement of tail rotor can change the noise spectrum and lower the noise level. Last, by contrastive analysis between the results of the isolated tail rotor noise and the experiment, the computation model is being proven. These conclusions can be used to estimate the helicopter tail rotor noise and help to guide tail rotor noise reduction design.
引文
[1] Ffowcs Williams,J. E.,Hawking,D.L. Sound Generated by Turbulence and Surfaces in Arbitrary Motion.Philosophical Transactions of the Royal Society,1969,Vol. A264(1511):p321-342.
[2] Farassat,F. Pegg, R. J. Hiltion,D.A.. Thickness Noise of Helicopter Rotors at High Tip Speed. AIAA Paper. p75-453.
[3] Farassat,F. Linear Acoustic Formulas for Calculation of Rotating Blade Noise.AIAA Paper 83-688.
[5] Robert H., Schlinker Roy K. Amie.Rotor-Vortex Interaction Noise. NASA Contractor Report 3744.
[6] Kenneth,W. McAlister, James T. Heineck.Measurements of the Early Development of Trailing Vorticity from a Rotor.NASA/TP-2002-211848.
[7] R. H. Schlinker and R. K. Amiet.Tail rotor blade-vortex interaction niose.AIAA,April 1983.
[8] David R. Suttie, Frank N. Coton , Roderick A.McD. Galbraith. Development of an indicial model of helicopter tail rotor orthogonal blade vortex interaction. AIAA 2005-469.
[9] Bruce J. Wendt,Julianne C. Dudek. A computational-experimental development of vortex generator use for a transitioning s-diffuser.NASA Technical Memorandum 107357.
[10] B. J. Wendt,W. R. Hingst. Measurements and modeling of flow structure in the wake of a low profile "wishbone" vortex generator,NASA Technical Memorandum 106468.
[11] Lowson, M. V. .The Sound Field for Singularities in Motion, Proceedings of the Royal Society, London, 1965, Vol. 286A: 559-572
[12]孙晓锋,周盛.气动声学,北京:国防工业出版社,1994.
[13] Sudarshan N. Koushik. A New Experimental Approach to Study Helicopter Blade-Vortex Interaction Noise. PHD thesis, American: University of Maryland, 2007.
[14]尹坚平.直升机噪声及其控制技术的研究.博士学位论文,南京:南京航空航天大学,1996.
[15]彭延辉.直升机旋翼桨-涡干扰气动噪声的研究.硕士学位论文,南京:南京航空航天大学,2004.
[16]徐国华,高正.悬停状态下模型旋翼噪声试验的初步研究,空气动力学报,Vol.14,No.1,1996.
[17]王华明,张强,胡章伟等.AS350直升机飞行噪声的试验研究,声学学报(中文版),2001:p65～69.
[18] J.A. Lieser,D. Lohmann, K.J. Schultz.Prediction of Rotor Aeroacoustics in Forward Flight by a Lifting Surface Method,50th AHS Annual Forum,May 1994.
[19] Brian Maskew.Program VSAERO Theory Document,NASA Constractor Report 4023.
[20] Joseph Katz,Allen Plotkin.Low-speed Aerodynamics,From Wing Theory to Panel Methods,McGraw-Hill,1991.
[21]仲唯贵.直升机旋翼尾涡与尾桨干扰噪声研究,硕士学位论文.南京:南京航空航天大学,2006.
[22]李晓东.亚音速螺旋桨声场预测理论、实验及工程应用,硕士学位论文,北京:北京航空航天大学,1992.
[23] Farassat F,Brown TJ.A New Capability for Predicting Helicopter Rotor and Propeller Noise Including the Effect of Forward Motion,NASA TM74037,June 1977.
[24]陈廷楠,王平军.应用流体力学,航空工业出版社,1999.5.24:p109～167.
[25]钱翼稷.空气动力学.北京航空航天大学出版社,2005.2.18:p45～63.
[26]王适存.直升机空气动力学,北京:航空专业教材编审组,1983:p10~117.
[27]俞元亮,胡章伟,陈玉清等.航空声学,北京:航空专业教材编审组,1986:p45~110.
[28]姚起杭.飞机噪声工程,西北工业大学出版社,1998.
[29]杨小林,严敬.PIV测速原理与应用.西华大学学报,Jan.2005:p19~30.
[30] J. Gordon Leishman.Principles of Helicopter Aerodynamics,Cambridge University Press,2001:p269~288.
[31]李启.直升机尾桨噪声预测方法的研究,硕士学位论文,南京,南京航空航天大学,2006.
[32]杜功焕,朱哲民,龚秀芬.声学基础,南京大学出版社,2001.3:p308~340.
[33]应怀樵.现代振动与噪声技术(第五卷).航空工业出版社,2007.10.
[34]陈克安,曾向阳,李海英.声学测量.科学出版社,2005.8.
[35]龚秀芬,孙广荣,吴启学.噪声测量和控制.江苏科学技术出版社,1985.
[36] B. W.-C. Sim,F. H. Schmitz.Acoustic Phasing and Amplification Effects of Single-Rotor Helicopter Blade-Vortex Interactions,American Helicopter Society 55th Annual Forum,1998.
[37] Schulz K J.Model Tail Rotor Noise Study in the DNW,Measured Acoustics,Blade Pressure,Noise Prediction,18th European Rotorcraft Forum,1992.
[38] Leverton J W. Reduction of Helicopter Noise by Use of a Quiet Tail Rotor, Paper No.46th European Rotorcraft Forum,1980:p203~210.
[39] Smith Michael J T. Aircraft Noise [M],Cambridge University Press,1989:255~351.
[40] Farassat,F. .Generalized Functions and Kirchhoff Formulas,AIAA 96-1705.
[41] Farassat, F., Brentner, K.S.A Study of Supersonic Surface Sources-The Ffowcs Willliams-Hawkings Equation and the Kirchhoff Formula,AIAA 98-2375.
[42] Farassat, F.,Myers,M. K. The Kirchhoff Formula for a Supersonically Moving Surface,16th AIAA Conference,June 12-15,1995, Munich,Germany.
[2] Farassat,F. Pegg, R. J. Hiltion,D.A.. Thickness Noise of Helicopter Rotors at High Tip Speed. AIAA Paper. p75-453.
[3] Farassat,F. Linear Acoustic Formulas for Calculation of Rotating Blade Noise.AIAA Paper 83-688.
[5] Robert H., Schlinker Roy K. Amie.Rotor-Vortex Interaction Noise. NASA Contractor Report 3744.
[6] Kenneth,W. McAlister, James T. Heineck.Measurements of the Early Development of Trailing Vorticity from a Rotor.NASA/TP-2002-211848.
[7] R. H. Schlinker and R. K. Amiet.Tail rotor blade-vortex interaction niose.AIAA,April 1983.
[8] David R. Suttie, Frank N. Coton , Roderick A.McD. Galbraith. Development of an indicial model of helicopter tail rotor orthogonal blade vortex interaction. AIAA 2005-469.
[9] Bruce J. Wendt,Julianne C. Dudek. A computational-experimental development of vortex generator use for a transitioning s-diffuser.NASA Technical Memorandum 107357.
[10] B. J. Wendt,W. R. Hingst. Measurements and modeling of flow structure in the wake of a low profile "wishbone" vortex generator,NASA Technical Memorandum 106468.
[11] Lowson, M. V. .The Sound Field for Singularities in Motion, Proceedings of the Royal Society, London, 1965, Vol. 286A: 559-572
[12]孙晓锋,周盛.气动声学,北京:国防工业出版社,1994.
[13] Sudarshan N. Koushik. A New Experimental Approach to Study Helicopter Blade-Vortex Interaction Noise. PHD thesis, American: University of Maryland, 2007.
[14]尹坚平.直升机噪声及其控制技术的研究.博士学位论文,南京:南京航空航天大学,1996.
[15]彭延辉.直升机旋翼桨-涡干扰气动噪声的研究.硕士学位论文,南京:南京航空航天大学,2004.
[16]徐国华,高正.悬停状态下模型旋翼噪声试验的初步研究,空气动力学报,Vol.14,No.1,1996.
[17]王华明,张强,胡章伟等.AS350直升机飞行噪声的试验研究,声学学报(中文版),2001:p65～69.
[18] J.A. Lieser,D. Lohmann, K.J. Schultz.Prediction of Rotor Aeroacoustics in Forward Flight by a Lifting Surface Method,50th AHS Annual Forum,May 1994.
[19] Brian Maskew.Program VSAERO Theory Document,NASA Constractor Report 4023.
[20] Joseph Katz,Allen Plotkin.Low-speed Aerodynamics,From Wing Theory to Panel Methods,McGraw-Hill,1991.
[21]仲唯贵.直升机旋翼尾涡与尾桨干扰噪声研究,硕士学位论文.南京:南京航空航天大学,2006.
[22]李晓东.亚音速螺旋桨声场预测理论、实验及工程应用,硕士学位论文,北京:北京航空航天大学,1992.
[23] Farassat F,Brown TJ.A New Capability for Predicting Helicopter Rotor and Propeller Noise Including the Effect of Forward Motion,NASA TM74037,June 1977.
[24]陈廷楠,王平军.应用流体力学,航空工业出版社,1999.5.24:p109～167.
[25]钱翼稷.空气动力学.北京航空航天大学出版社,2005.2.18:p45～63.
[26]王适存.直升机空气动力学,北京:航空专业教材编审组,1983:p10~117.
[27]俞元亮,胡章伟,陈玉清等.航空声学,北京:航空专业教材编审组,1986:p45~110.
[28]姚起杭.飞机噪声工程,西北工业大学出版社,1998.
[29]杨小林,严敬.PIV测速原理与应用.西华大学学报,Jan.2005:p19~30.
[30] J. Gordon Leishman.Principles of Helicopter Aerodynamics,Cambridge University Press,2001:p269~288.
[31]李启.直升机尾桨噪声预测方法的研究,硕士学位论文,南京,南京航空航天大学,2006.
[32]杜功焕,朱哲民,龚秀芬.声学基础,南京大学出版社,2001.3:p308~340.
[33]应怀樵.现代振动与噪声技术(第五卷).航空工业出版社,2007.10.
[34]陈克安,曾向阳,李海英.声学测量.科学出版社,2005.8.
[35]龚秀芬,孙广荣,吴启学.噪声测量和控制.江苏科学技术出版社,1985.
[36] B. W.-C. Sim,F. H. Schmitz.Acoustic Phasing and Amplification Effects of Single-Rotor Helicopter Blade-Vortex Interactions,American Helicopter Society 55th Annual Forum,1998.
[37] Schulz K J.Model Tail Rotor Noise Study in the DNW,Measured Acoustics,Blade Pressure,Noise Prediction,18th European Rotorcraft Forum,1992.
[38] Leverton J W. Reduction of Helicopter Noise by Use of a Quiet Tail Rotor, Paper No.46th European Rotorcraft Forum,1980:p203~210.
[39] Smith Michael J T. Aircraft Noise [M],Cambridge University Press,1989:255~351.
[40] Farassat,F. .Generalized Functions and Kirchhoff Formulas,AIAA 96-1705.
[41] Farassat, F., Brentner, K.S.A Study of Supersonic Surface Sources-The Ffowcs Willliams-Hawkings Equation and the Kirchhoff Formula,AIAA 98-2375.
[42] Farassat, F.,Myers,M. K. The Kirchhoff Formula for a Supersonically Moving Surface,16th AIAA Conference,June 12-15,1995, Munich,Germany.