Vortex Ring Input in Subsonic Jet Noise
Vortex Ring Input in Subsonic Jet Noise
复制标题
亚音速射流噪声中的涡环输入
DOI：
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发表时间：
2007
期刊：
影响因子：
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通讯作者：
N. Ostrikov
中科院分区：
文献类型：
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作者：
V. Kopiev;M. Zaitsev;S. Chernyshev;N. Ostrikov
本文的主要目的是在选定的频带（Sh = 0.2-0.45）内评估大尺度涡对亚音速湍流射流（M = 0.35，Re = 3.2·105）噪声的贡献。声辐射的机制，根据一个单独的涡结构本身可以是一个重要的声源被认为是。根据这种机理，涡核本征模态是噪声辐射的主要原因。该工作分为三个耦合项：（i）分离涡环噪声辐射的理论研究（特别是鲜为人知的八极子对声辐射的贡献），（ii）激发射流中大涡的可视化;（iii）湍流射流噪声的实验研究（速度为120 m/s的亚音速射流，激励频率为2000 Hz），利用方位角分解技术（ADT），将射流分解到各个方位角分量上。在最后阶段，这些结果的仔细比较给出了在所考虑的音调激励湍流射流中涡环对射流噪声的贡献的定量评估。
The main goal of the paper is to assess the contribution of large-scale vortices to the noise of the subsonic turbulent jet (M = 0.35, Re = 3.2·105) in the selected frequency bands (Sh∼0.2–0.45). The mechanism of sound radiation according to which a separate vortex structures itself can be a significant sound source is considered. Vortex core eigen-modes are responsible for noise radiation according to this mechanism. The work is subdivided on three coupling items: (i) theoretical investigation of noise radiation of separate vortex ring (especially little-known octupole contribution to sound radiation), (ii) visualization of large vortices in excited jet and (iii) experimental investigation of turbulent jet noise (subsonic jet with velocity 120m/s excited at 2000Hz) decomposed on the separate azimuthal components with the help of azimuthal decomposition technique (ADT). On the final stage the careful comparison of these results gives the quantitative assessment of the contribution of vortex rings to the jet noise in a tone-excited turbulent jet under consideration.