后壁倒角对开式空腔气动噪声抑制作用研究  

Effect of chamfer rear-face angle on open cavity flow aero-acoustic noise suppression

作　　者：吴继飞[1,2] 徐来武[2] 范召林[2] 罗新福[2] 

机构地区：[1]空气动力学国家重点实验室,四川绵阳621000 [2]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《空气动力学学报》2017年第5期645-649,654,共6页Acta Aerodynamica Sinica

摘　　要：在高速风洞中对空腔流场气动声学特性进行了试验研究,对空腔后壁进行倒角,以降低气流在该处的撞击强度,从而达到抑制空腔流场气动噪声的目的。试验马赫数(Ma)为0.6~1.2,空腔长深比(L/D)为4.1、4.7。试验结果表明:亚跨声速范围内,随马赫数增大,开式空腔流场气动声学环境恶劣程度加剧,最大总声压级高达170dB以上,声压频谱曲线上存在多个不同模态的单调声;后壁倒角后,腔底总声压级强度明显降低,且其降低程度随马赫数增大愈趋明显,最大可降低近7dB,空腔后壁上主噪声源附近总声压级强度可降低约1dB,声压频谱曲线上的能量峰值明显减弱。A series of experiments were conducted in a high speed wind tunnel to study aero- acoustic characteristics cavity flows . The rear w all of the tested cavity was chamfered to reduce the airflow impact strengthen, so as to suppress the cavity noise. The test Mach numbers ranged from 0. 6 to 1. 2. The length to depth ratios of the cavities were 4. 1 and 4. 7. Results indicate that aero-acoustic environment around the open cavity exacerbates w ith increasing Mach number in subsonic and transonic speed ranges. The maximal overall sound pressure level （OSPL） is more than 170dB. Several tones with different modes can be found in the sound pressure spectra. It is also indicated that the control method by chamfering the cavity rear w all is effective on suppressing the cavity noise. The overall sound pressure level on the cavity f lo o r reduced significantly,the maximum of reduced OSPL was approximately 7 dB. The reduced OSPL was about 1 dB near the main noise source on the rear w all of the cavity. The peaks of sound energy spectrum curves were also suppressed substantially due to the control method.

关 键 词：空腔 流动控制 总声压级 气动噪声 自持振荡 声压频谱 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]