基于 DDES 算法的有扰流片腔体气动噪声分析  

DDES of aeroacoustic over an open cavity with and without a spoiler

作　　者：刘瑜[1] 童明波[1] Zhiwei Hu 

机构地区：[1]南京航空航天大学航空宇航学院,江苏南京210016 [2]University of Southampton,Southampton UK SO17 1BJ

出　　处：《空气动力学学报》2015年第5期643-648,共6页Acta Aerodynamica Sinica

基　　金：江苏省高校优势学科建设工程资助项目;江苏省研究生培养创新工程KYLX_0296;中央高校基本科研业务费专项资金资助

摘　　要：为了进一步了解腔体流场的物理特性以及锯齿形扰流片这种被动控制方法对腔体噪声振荡的抑制效果,对马赫数0.85下、长深比为5∶1的矩形腔体进行了气动声学分析。分析过程采用了基于Spalart-Allmaras单方程模型的延迟分离涡模拟(DDES)的CFD方法。计算结果以声压级(SPL)形式与英国QinetiQ基地进行的实验研究结果进行比较。计算准确地预测出了第二阶和第三阶主导模态的声调噪声幅值,其误差均不超过2dB。为了验证腔体前缘安装扰流片这种广泛应用的腔体噪声被动控制方法,计算重点分析了带有锯齿形扰流片的腔体结构噪声等级。计算分析结果与空腔结果对比分析后认为前缘锯齿形扰流片可以降低第二阶主导模态的峰值噪声等级10dB以上,其它频率下的腔体噪声等级可降低接近5dB,降噪效果较好。In order to obtain a further understanding of the cavity aeroacoustics and test the noise suppression effect using a saw tooth spoiler,aeroacoustics characteristic over an open cavity with a length to depth ratio of 5∶1 at Mach 0.85 are investigated in the present study.The CFD simulations are performed by delayed detached eddy simulation （DDES）based on Spalart-Allma-ras one equation turbulence model.The results obtained from clean cavity prediction are com-pared with experimental sound pressure level （SPL）data from QinetiQ,UK.It can be observed from the results that the tone amplitude of the 2 nd and 3 rd dominant modes are generally well pre-dicted （within 2 dB）,whilst the 1 st and the 4 th tones are not so well resolved.In order to evaluate leading-edge spoiler which is widely used as a passive control method on cavity noise suppression, the main focuses are sound pressure level of cavity with a leading-edge saw tooth spoiler.Accord-ing to the comparison of computational SPL results between cavity with spoiler and clean cavity, the saw tooth spoiler reduce the 2 nd dominant tone amplitude over 10dB,and the over-all SPL a-bout 5dB,significant noise suppression effect for open cavity is validated.

关 键 词：腔体 气动噪声 扰流片 声压级 DDES 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]