某型螺旋桨飞机气动噪声降噪研究
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摘要
针对某型电动螺旋桨飞机噪声过大问题,在保证螺旋桨气动特性的同时,提出了改进沿展向桨叶形状的降噪方法。采用FW-H模型、非定常滑移网格及大涡模拟方法获得了气动噪声频谱特征;通过地面远场噪声试验,得到了螺旋桨在三种转速下的气动噪声频域特性和声压强度分布规律。对比分析螺旋桨各测点声压级试验数据和数值计算结果,证明了数值计算模型的准确性。基于所建立的计算模型和方法,预测了不同螺旋桨在三个转速下的声压级分布,得出桨叶形状对螺旋桨气动噪声的影响规律。研究表明:当螺旋桨转速高于1 000r/min时,新叶片较原叶片气动噪声明显降低。这说明桨叶载荷噪声在气动噪声中起主导作用,可以通过改变沿展向桨叶形状,有效降低叶片的气动噪声。
Aimed at the problem of excessive propeller noise in a new type of electric aircraft,in order to ensure the propeller aerodynamic characteristics simultaneously,a noise reduction method to optimize the shape of the blade along the spanwise was proposed.FW-H model,unsteady slip mesh and large eddy simulation method were applied to obtain the aerodynamic noise spectrum.The aerodynamic noise experiment under three speeds was completed,and the frequency domain characteristics and sound pressure intensity distribution were obtained.The validity of the numerical calculation model method was verified by comparing the experimental data of the measuring point sound pressure level and the numerical results.Based on the established calculation model and method,the distribution law of the sound pressure level with different shape along the spanwise was analyzed under three different rotation speeds,and the influence of the blade shape on the aerodynamic noise was obtained.The research showed that the aerodynamic noise of the new blade was significantly reduced compared to the original blade when the rotation speed was up to 1 000 r/min,indicating that the blade load noise played a dominant role in the aerodynamic noise and could be effectively reduced by changing the blade shape along the spanwise,resulting in lower aerodynamic noise.
Aimed at the problem of excessive propeller noise in a new type of electric aircraft,in order to ensure the propeller aerodynamic characteristics simultaneously,a noise reduction method to optimize the shape of the blade along the spanwise was proposed.FW-H model,unsteady slip mesh and large eddy simulation method were applied to obtain the aerodynamic noise spectrum.The aerodynamic noise experiment under three speeds was completed,and the frequency domain characteristics and sound pressure intensity distribution were obtained.The validity of the numerical calculation model method was verified by comparing the experimental data of the measuring point sound pressure level and the numerical results.Based on the established calculation model and method,the distribution law of the sound pressure level with different shape along the spanwise was analyzed under three different rotation speeds,and the influence of the blade shape on the aerodynamic noise was obtained.The research showed that the aerodynamic noise of the new blade was significantly reduced compared to the original blade when the rotation speed was up to 1 000 r/min,indicating that the blade load noise played a dominant role in the aerodynamic noise and could be effectively reduced by changing the blade shape along the spanwise,resulting in lower aerodynamic noise.
引文
[1]刘沛清.空气螺旋桨理论及其应用[M].北京:北京航空航天大学出版社,2006.
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[4]OHAD G,AVIV R.Optimization of propeller based propulsion system[J].Journal of Aircraft,2009,46(1):95-106.
[5]ANTONIO P,LUIGIiF.Multi-objective aeroacoustic optimization of an aircraft propeller[C]//12th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference 10-12September 2008,Victoria,British Columbia Canada:AIAA,2008:No.5.
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[11]项松,王吉,张利国,等.一种高效率螺旋桨设计方法[J].航空动力学报,2015,30(1):136-141.
[12]尹坚平,胡章伟.地面反射和衰减效应对声源频谱的影响[J].南京航空学院学报,1990,22(3):22-28.
[13]孙晓峰.气动声学[M].北京:国防工业出版社,1994.
[14]孙晓峰,胡宗安.桨扇的气动弹性力学和气动声学[J].航空动力学报,1987(4):299-302,368.
[15]鄂秦,杨国伟,李凤,等.螺旋桨滑流对飞机气动特性影响的数值分析[J].西北工业大学学报,1997,15(4):511-516.
[16]于子文,曹义华.前飞旋翼三维湍流场的数值模拟[J].北京航空航天大学学报,2006,32(7):751-755.
[17]叶靓.基于非结构网格的直升机旋翼流场及噪声研究[D].南京:南京航空航天大学,2009.
[18]赵忠.螺旋桨特性风洞实验技术研究[D].西安:西北工业大学,2007.
[19]MOOREL M D,FREDERICKS B.Misconceptions of electric propulsion aircraft and their emergent aviation markets[R].USA:AIAA,2014.
[20]SNORRI G.General aviation aircraft design[M].Oxford,UK:Elsevier,2014.
[21]FARASSAT F,SUCCI G P.The prediction of helicopter rotor discrete frequency noise[J].Vertica,1983,7(4):309-320.
[22]FARASSAT F.Discontinuities in aerodynamics and aetosoustics:the concept and application of generlized derivatives[J].Journal of Sound and Vibration,1977,55:165-193.
[2]CHUSSEAU M,ROOZEN E.Light aircraft propeller:design parameter effects on acoustics andaerodynamics[C]//15th Aeroacoustics Conference.Canada:AIAA,2016:No.6.
[3]OHAD G.Maximum propeller efficiency estimation[J].Journal of Aircraft,2017,51(8):2035-2038.
[4]OHAD G,AVIV R.Optimization of propeller based propulsion system[J].Journal of Aircraft,2009,46(1):95-106.
[5]ANTONIO P,LUIGIiF.Multi-objective aeroacoustic optimization of an aircraft propeller[C]//12th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference 10-12September 2008,Victoria,British Columbia Canada:AIAA,2008:No.5.
[6]MARINUS B G,ROGER M.Multidisciplinary optimization of propeller blades:focus on the aeroacoustic results[C]//17th AIAA/CEAS Aeroacoustics Conference(32nd AIAAAeroacoustics Conference)Portland,Oregon:AIAA,2011,No.3.
[7]CAMPOS L M B C,LAU F J P.On propelleracoustics design synthesis using source distributions along blade span[C]//12th AIAA/CEAS Aero-acoustics Conference(27th AIAAAeroacoustics Conference)Cambridge,Massachusett:AIAA,2006:No.3.
[8]潘杰元,钱惠德.螺旋桨的数值优化设计[J].航空动力学报,1991,6(4):300-304,374.
[9]FFCOWA WILLIAMS J E,HAWKINGS D L.Sound generation by turbulence and surface in arbitrary motion[J].Proceedings of the Royal Society of London,Series A,Mathematics and Physical Sciences,1969,264:321-342.
[10]ANGELO S D,BERARDI F,MINISCI E.Aerodynamic performances of propellers with parametric considerat-ions on the optimal design[J].The Aeronautical journal,2002,106(1060):313-320.
[11]项松,王吉,张利国,等.一种高效率螺旋桨设计方法[J].航空动力学报,2015,30(1):136-141.
[12]尹坚平,胡章伟.地面反射和衰减效应对声源频谱的影响[J].南京航空学院学报,1990,22(3):22-28.
[13]孙晓峰.气动声学[M].北京:国防工业出版社,1994.
[14]孙晓峰,胡宗安.桨扇的气动弹性力学和气动声学[J].航空动力学报,1987(4):299-302,368.
[15]鄂秦,杨国伟,李凤,等.螺旋桨滑流对飞机气动特性影响的数值分析[J].西北工业大学学报,1997,15(4):511-516.
[16]于子文,曹义华.前飞旋翼三维湍流场的数值模拟[J].北京航空航天大学学报,2006,32(7):751-755.
[17]叶靓.基于非结构网格的直升机旋翼流场及噪声研究[D].南京:南京航空航天大学,2009.
[18]赵忠.螺旋桨特性风洞实验技术研究[D].西安:西北工业大学,2007.
[19]MOOREL M D,FREDERICKS B.Misconceptions of electric propulsion aircraft and their emergent aviation markets[R].USA:AIAA,2014.
[20]SNORRI G.General aviation aircraft design[M].Oxford,UK:Elsevier,2014.
[21]FARASSAT F,SUCCI G P.The prediction of helicopter rotor discrete frequency noise[J].Vertica,1983,7(4):309-320.
[22]FARASSAT F.Discontinuities in aerodynamics and aetosoustics:the concept and application of generlized derivatives[J].Journal of Sound and Vibration,1977,55:165-193.