外涵偏轴分开排气喷管的流场和声场数值计算

张正伟; 张靖周; 邵万仁; 单勇; 吴飞

外涵偏轴分开排气喷管的流场和声场数值计算

1.
南京航空航天大学能源与动力学院, 南京 210016
2.
中国航空工业集团公司沈阳发动机设计研究所, 沈阳 110015

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出版历程
- 收稿日期: 2011-06-12
- 刊出日期: 2012-05-28

Numerical caculation of flow and acoustics fields for separated exhaust nozzle with bypass offset

1.
College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
2.
Shenyang Aeroengine Design and Research Institute, Aviation Industry Corporation of China, Shenyang 110015, China

摘要

摘要: 以某型涡扇发动机为原型,建立了1/10缩比的分开排气式涡扇发动机排气喷管物理模型,采用大涡模拟(LES)计算了不同外涵偏轴距离的排气喷管非稳态流场,利用FW-H(Ffows Williams-Hawkings)声学模型和傅里叶变换得到了排气喷流噪声声压级空间分布特征.计算结果表明:外涵偏轴式分开排气喷管有抑制排气喷流噪声的作用.喷流噪声整体抑制效果与偏轴距离有关,在偏轴距离为0.15D时,排气喷管下方的噪声降低达到最大,且排气噪声峰值由原型的146.7dB降低到139.5dB,降低了7.2dB.研究的排气结构和数值计算方法可作为分开排气式涡扇发动机降噪设计的参考.
- 涡扇发动机 /
- 分开排气式排气系统 /
- 外涵偏轴 /
- 大涡模拟 (LES) /
- FW-H (Ffows Williams-Hawkings) 方程 /
- 气动噪声
Abstract: Based on large eddy simulation and FW-H(Ffows Williams-Hawkings) acoustics simulation,the unsteady flow field and the jet noise distribution of overall sound pressure level(OASPL) were obtained for one 1/10 scaled turbofan engine with separated exhaust system at various bypass offset distances.It shows that the structure of bypass offset has the ability of depressing the exhaust jet noise.The noise depression effects have relation with the bypass offset distance.Exhaust jet noise is reduced from 146.7dB to139.5dB at the offset distance of 0.15D which is the maximal noise reduction.The configuration and the numerical method mentioned can be taken into consideration in the design of the separated exhaust for turbo-fan engine.
- turbo-fan engine /
- separated exhaust system /
- bypass offset /
- large eddy simulation(LES) /
- FW-H(Ffows Williams-Hawkings) equation /
- jet noise

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参考文献(13)

[1]	Silva C R I.Numerical and empirical approaches for jet noise reduction investigation of co-flow effects.AIAA 2009-3405,2009.
[2]	穆宁 A F.航空声学[M].曹传钧,译.北京:北京航空航天大学出版社,1993.
[3]	郑礼宝.二元喷管热喷流噪声特性试验研究[J].空气动力学学报,2006,18(2):241-246. ZHENG Libao.Investigation of noise characteristics of hot exhaust from two dimensional nozzles[J].Acta Aerodynamica Sinica,2006,18(2):241-246.(in Chinese)
[4]	梁春华.GE90发动机的降噪技术[J].航空发动机,2004,30(4):40.
[5]	Callender B,Gutmark E.Far-field acoustic investigation into chevron nozzle mechanisms and trends.AIAA-6150-656,2005.
[6]	Henderson B,Kinzie K.Aeroacoustic improvements to fluidic chevron nozzles.AIAA-2006-2706,2006.
[7]	Calkins F T,Butler G W.Variable geometry chevrons for noise reduction.AIAA-2006-2546,2006.
[8]	Elkoby E N,Ronen.Bhat T R S.Correlating model-scale and full-scale test resulets of dual flow nozzle jets.AIAA-2002-2487,2002.
[9]	Papamoschou D.Noise suppression in moderate-speed multistream jets[J].AIAA-2002-2557,2002.
[10]	Lyrintzis A U A S.Coupling of integral acoustics methods with LES for jet noise prediction.AIAA-2004-0517,2004.
[11]	肖军生.高速轿车外流场气动噪声研究.吉林:吉林大学,2006. XIAO Junsheng.Study of aerodynamic noise for the vehicle with high speed in the exterior flow.Jilin:Jilin University,2006.(in Chinese)
[12]	韩忠华,宋文萍,乔志德.基于FW-H方程的旋翼气动声学计算研究[J].航空学报,2003,24(5):400-404.(in Chinese) HAN Zhonghua,SONG Wenping,QIAO Zhide.Aeroa-coustic calculation for helicopter rotor in hover and in forward flight based on FW-H equation[J].Acat Aeronautica et Astronautica Sinica,2003,24(5):400-404.
[13]	张楠,沈泓萃,姚惠之,等.孔穴流激噪声的计算与验证研究[J].船舶力学,2008,12(5):799-805.(in Chinese) ZHANG Nan,SHEN Hongcui,YAO Huizhi,et al.Validation and calculation of flow-induced noise of cavity[J].Journal of Ship Mechanics,2008,12(5):799-805.(in Chinese)