基于多物理场的涡扇发动机尾喷口近场噪声模拟研究  

Simulation Study on the Near Field Noise of Turbofan Engine Tail Nozzle Based on Multiphysical Field

作　　者：闫国华[1] 汪霁洁 Yan Guohua;Wang Jijie(Civil Aviation University of China,Tianjin 300300,China)

机构地区：[1]中国民航大学,天津300300

出　　处：《航空科学技术》2018年第12期29-33,共5页Aeronautical Science & Technology

摘　　要：本文通过简化尾喷口模型,针对喷管涵道内流场中的不同周向模态数对噪声的传播影响进行研究,基于COMSOL多物理场建立计算流体力学(CFD)数值计算模型,得到了不同周向模态数的尾喷口近场压力变化图、声压级变化图。研究结果表明,在以涡轮风扇为噪声源的基础上,声波从喷管内涵道的入口端到出口端,波的反射清晰可见,对于模态数m=10和m=18尤为明显,噪声波的衍射效应在m=18时不是很显著。另外,由声压级等值线图可知,周向模态数越小,内涵道内近壁面辐射声压级越小,但在喷口后缘处,声压级传播基本以5～7d B的幅度在减小。In this paper,the influence of different weeks on the noise in the flow field of the nozzle was studied by simplifying the tail nozzle model.The CFD numerical calculation model is established based on COMSOL Multiphysics,and the near field pressure variation diagram and the sound pressure level variation diagram of the tail nozzle were obtained with the change of the weekly direction mode number in the flow field.The research results show that based on the turbine fan as the noise source,the reflection of the sound wave is clearly visible from the entrance end to the exit end of the nozzle connotation channel,especially for the modal Numbers m=10 and m=18,the diffraction effect of the noise wave is not very significant in m=18.In addition,it can be seen from the sound pressure level contour map that the smaller the number of circumferential modes,the smaller the radiation sound pressure level in the near wall of the channel,but at the trailing edge of the jet,sound pressure level propagation is basically reduced by 5-7dB.

关 键 词：喷流噪声 周向模态数 COMSOL 近场声压级 衍射 

分 类 号：TU385.3[建筑科学—结构工程]