大型飞机增升装置气动噪声研究进展
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摘要
对于现代大型商用飞机而言,在飞机进场和降落阶段,由于飞机发动机处于低功率状态而起落架和增升装置全部打开,此时的机体噪声十分明显,在飞机总的噪声中所占的比重不容忽视。近几十年的大量研究,已经对增升装置的气动噪声特性和机理有相当程度的认识,并在流动控制和降噪技术方面取得丰硕成果。本文主要介绍国内外在大型飞机增升装置气动噪声领域所取得的研究成果和最新进展。增升装置的噪声主要是由前缘缝翼凹槽产生的低频离散噪声、襟翼侧缘的中频宽带噪声和前缘缝翼尾缘涡脱落的高频离散噪声三部分组成。目前,降噪技术主要分成被动流动控制降噪技术和主动流动控制降噪技术两类,被动降噪技术有前缘凹槽遮挡、前缘凹槽填充、前缘下垂等;主动流动控制手段有吹吸气、等离子体激励器等。
For the modern large commercial aircrafts,during the phases of approach and landing,when the engines are at low operate with the high-lift devices and landing gears all deployed,the airframe noise,the majority of the aircraft total noise,is notable. Over the last decades,a considerable amount of work has been conducted on the noise characteristics,noise mechanism,noise reduction techniques for the high-lift device noise. The high-lift device noise is generally categorized into three parts,low-frequency tones generated from the slat cove,midfrequency broadband noise generated from flap side edge,and high-frequency tones generated from the slat trailing edge. The noise reduction techniques have active and passive flow control and noise reduction methods,such as slat cove cover,slat cove filler,droop nose and blowing-suction air,plasma actuation,etc.
For the modern large commercial aircrafts,during the phases of approach and landing,when the engines are at low operate with the high-lift devices and landing gears all deployed,the airframe noise,the majority of the aircraft total noise,is notable. Over the last decades,a considerable amount of work has been conducted on the noise characteristics,noise mechanism,noise reduction techniques for the high-lift device noise. The high-lift device noise is generally categorized into three parts,low-frequency tones generated from the slat cove,midfrequency broadband noise generated from flap side edge,and high-frequency tones generated from the slat trailing edge. The noise reduction techniques have active and passive flow control and noise reduction methods,such as slat cove cover,slat cove filler,droop nose and blowing-suction air,plasma actuation,etc.
引文
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[2]DOBRZYNSKI W.. Almost 40 years of airframe noise research:what did we achieve?[J]. Journal of Aircraft,2010,V47(2):353-367.
[3]朱自强,陈迎春,吴宗成,陈泽民.高升力系统外形的数值模拟计算[J].航空学报:2005,16(3):257-262.
[4]CHOUDHARI M.,KHORRAMI M,Slat cove unsteadiness:effect of 3D flow structures[C]. 44th AIAA Aerospace Sciences Meeting and Exhibit,AIAA Paper 2006-0211.
[5]TAKEDA K,ASHCROFT G,ZHANG Xiaohei,Philip Nelson,Unsteady Aerodynamics of Slat Cove Flow in a High-lift Device Configuration[C]. 39th AIAA Aerospace Sciences Meeting and Exhibit. AIAA Paper 2001-0706.
[6]KAEPERNICKK.,KOOP L.,EHRENFRIED K.,Investigation of the Unsteady Flow Field inside a Leading Edge Slat Cove[C]. 11th AIAA/CEAS Aeroacoustics Confer-ence(26th AIAA Aeroacoustics Conference). AIAA Paper 2005-2813.
[7]KHORRAMI M. R.,BERKMAN M. E.,CHOUDHARI M. Unsteady Flow Computations of a Slat with a Blunt Trailing Edge[J]. AIAA Journal,2000,V38(11):2050-2058.
[8]PASCHAL K.,JENKINS L.,YAO Chungsheng,Unsteady Slat-Wake Characteristics of a High-Lift Configura-tion[C].38th Aerospace Sciences Meeting and Exhibit, AIAA Paper2000-0139.
[9]STORMS B. L, ROSS J. C, HORNE W. C. An aeroacous-tic study of an unswept wing with a three-dimensional high-lift system[R]. NASA,1998.
[10]TAM C. K. W.,PASTOUCHENKO N. Gap Tones:A Component of Airframe Noise[C]. 38th Aerospace Sciences Meeting and Exhibit. AIAA Paper 2000-0606.
[11]TAM C. K. W.,PASTOUCHENKO N. Gap tones[J].AIAA Journal,2001,V39(8):1442-1448.
[12]CHOUDHARI M. M.,LOCKARD D. P.,MACARAEG M. G.,et al. Aeroacoustic Experiments in the Langley LowTurbulence Pressure Tunnel[R]. NASA,2002.
[13]SINGER B. A.,LOCKARD D. P.,BRENTNER K. S.Computational aeroacoustic analysis of slat trailing-edge flow[J]. AIAA Journal,2000,V38(9):1558-1558.
[14]TAKEDA K.,ZHANG X.,NELSON P. A. Unsteady aerodynamics and aeroacoustics of a high-lift device configuration[C]. 40th AIAA Aerospace Sciences Meeting and Exhibit.AIAA Paper 2002-570.
[15]TERRACOL M.,MANOHA E.,LEMOINE B. Investigation of the Unsteady Flow and Noise Generation in a Slat Cove[J],AIAA Journal,2016,V54(2):469-489.
[16]MAKIYA S.,INASAWA A.,ASAI M. Vortex Shedding and Noise Radiation from a Slat Trailing Edge[J]. AIAA Journal,2010,V48(2):502-509
[17]KOLB A.,FAULHABER P.,DROBIETZ R.,et al. Aeroacoustic Wind Tunnel Measurements on a 2D High-Lift Configuration[C]. 13th AIAA/CEAS Aeroacoustics Conference(28th AIAA Aeroacoustics Conference). AIAA Paper 2007-3447.
[18]POTT-POLLENSKE M., ALVAREZ-GONZALEZ J.,DOBRZYNSKI W. Effect of Slat Gap/Overlap on Farfield Radiated Noise[C]. 9th AIAA/CEAS Aeroacoustics Confer-ence and Exhibit. AIAA Paper 2003-3228.
[19]ROGER M., PERENNES S. Low-Frequency Noise Sources in Two-Dimensional High-Lift Devices[C]. 5th AIAA/CEAS Aeroacoustics Conference. AIAA Paper 2000-1972.
[20]ROSSITER J. E. Wind Tunnel Experiments of the Flowover Rectangular Cavities at Subsonic and Transonic Speeds[R]. Ministry of Aviation; Royal Aircraft Establish-ment; RAE Farnborough,1964.
[21]IMAMURA T.,URA H.,YOKOKAWA Y.,et al. A Far-Field Noise and Near-Field Unsteadiness of a Simplified High-Lift-Configuration Model(Slat)[C]. 47th AIAA Science Meeting. AIAA Paper 2009-1239.
[22]FINK M. R.,SCHLINKER R. H. Airframe noise component interaction studies[J]. Journal of Aircraft,1979,V17(2):99-105.
[23]AHTYE W. F.,MILLER W. R.,MEECHAM W. C.Wing and Flap noise measured by near and field cross-correlation techniques[C]. AIAA Paper 79-0667.
[24]MILLER W. R.,MEECHAM W. C. Large scale model measurements of airframe noise using cross-correlation techniques[J]. Journal of The Acoustical Society of America,1982,V71(3):591-599.
[25]STREETT,C. L.,Numerical Simulation of Fluctuations Leading to Noise in a Flap-Edge Flowfield[C],AIAA Paper1998-0628.
[26]RADEZRSKY R. H.,SINGER B. A.,KHORRAMI M.R. Detailed measurements of a flap side-edge flow field[C].AIAA Paper 98-0700.
[27]RACKL R. G.,MILLER G.,GUO Y. P.,et al. Airframe Noise Studies-Review and Future Direction[R]. NASA,2005.
[28]HARDIN J. C. Noise radiation from the side edges of flaps[J]. AIAA Journal,1980,V18(5):549-552.
[29]SEN R. Vortex-oscillation model of airfoil side-edge noise[J]. AIAA Journal,1997,V35(3):441-449.
[30]KHORRAMI M. R.,SINGER B. A. Stability analysis for noise source modeling of a part-span flap[J]. AIAA Journal,1989,V37(10):1206-1212.
[31]HOWE M. S. On the generation of side-edge flap noise[J]. Journal of Sound and Vibration,1982,V80(4):555-573.
[32]GUO Y. P. RETRACTED:Flap side edge noise modeling and prediction[J]. Journal of Sound and Vibration,2013,V332(16):3846-3868.
[33]MURAYAMA M.,YOKOKAWA Y.,YAMAMOTO K.,et al. Numerical Investigation on Change of Airframe Noise by Flap Side-edge Shape[C]. 19th AIAA/CEAS Aeroacous-tics Conference. AIAA Paper 2013-2067.
[34]WALLER G. C. Prediction of flap-edge noise using STAR-CD[A]. 14th AIAA/CEAS Aeroacoustics Confer-ence[C]. 14th AIAA/CEAS Aeroacoustics Conference(29th AIAA Aeroacoustics Conference). AIAA Paper 2008-2863.
[35]DONG T. Z.,TARN C. K. W.,REDDY N. N. Direct Numerical Simulations of Flap Side Edge Noise[C]. AIAA Paper 99-1803.
[36]LANTRY R. B.,GREN E. A.,LARSSEN J. V.,et al.Evaluation of structured and unstructured grids for detached eddy simulation of flap edge noise[C]. 15th AIAA/CEAS Aeroacoustics Conference(30th AIAA Aeroacoustics Confer-ence)AIAA Paper 2009-3102.
[37]PATERSON R. W.,VOGT P. G.,FINK M. R.,et al.Vor-tex noise of isolated airfoils[J]. Journal of Aircraft,2012,V10(10):296-302.
[38]TAM C. K. W. Discrete tones of isolated airfoils[J].Journal of the Acoustical Society of America,1974,V55(6):1173.
[39]ARBEY H.,BATAILLE J. Noise generated by airfoil profiles placed in a uniform laminar flow[J]. Journal of Fluid Mechanics,1983,V134(134):33-47.
[40]BROOKS T. F.,POPE D. S.,MARCOLINI M. A. Airfoil self-noise and prediction[R]. NASA,1989.
[41]LOWSON M. V.,FIDDED S. P.,NASH E. C. Laminar boundary layer aero-acoustic instabilities[C]. 32nd Aerospace Sciences Meeting and Exhibit. AIAA Paper 1994-358.
[42]NASH E. C.,LOWSON M. V.,MCALPINE A. Boundary-layer instability noise on aerofoils[J]. Journal of Fluid Mechanics,1999,V382(382):27-61.
[43]MCALPINE A.,NASH E. C.,LOWSON M. V. On the Generation of Discrete Frequency Tones by the Flow around an Aerofoil[J]. Journal of Sound and Vibration,1999,V222(5):753-779.
[44]DESQUESNES G.,TERRACOL M.,SAGAUT P. Numerical investigation of the tone noise mechanism over lami-nar airfoils[J]. Journal of Fluid Mechanics,2007,V591(9):155-182.
[45]MOREAU D. J.,TETLOW M.,BROOKS L. A.,et al.Acoustic analysis of flat plate trailing edge noise[C]. International Congress on Acoustics. 2010.
[46]MOREAU D. J,BROOKS L. A,DOOLAN C. J. On the aeroacoustic tonal noise generation mechanism of a sharp-edged plate[J]. Journal of the Acoustical Society of America,2011,V129(4):154-160.
[47]MOREAU D. J,BROOKS L. A,DOOLAN C. J. The effect of boundary layer type on trailing edge noise from sharpedged flat plates at low-to-moderate Reynolds number[J]. Journal of Sound and Vibration,2012,V331(17):3976-3988.
[48]GRUBER M.,JOSEPH P.,CHONG T. P. Experimental Investigation of Airfoil Self Noise and Turbulent Wake Re-duction by the use of Trailing Edge Serrations[C]. AIAA/CEAS Aeroacoustics Conference. 2010.
[49]IKEDA T.,ATOBE T.,FUJIMOTO D.,et al. SelfNoise Effects on Aerodynamics of Cambered Airfoils at Low Reynolds Number[J]. AIAA Journal,2015,V53(8):1-14.
[50]CLEMONS H.,WLEZIEN R. W. Modification of Flow Structures Associated with Broadband Trailing Edge Noise[C].46th AIAA Fluid Dynamics Conference[C]. AIAA Paper 2016-3627.
[51]ANDERS S. G.,SELLERS W. L.,WASHBURN A. E.Active Flow Control Activities at NASA Langley[C]. AIAA Paper 2004-2623.
[52]BOWER W.,KIBENS V. An Overview of Active Flow Control Applications at The Boeing Company[C]. AIAA Flow Control Conference&2nd AIAA Flow Control Confer-ence. AIAA Paper 2004-2624.
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