Tip Leakage Experiment - Part One: Aerodynamic And Acoustic Measurements
Tip Leakage Experiment - Part One: Aerodynamic And Acoustic Measurements
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尖端泄漏实验 - 第 1 部分：空气动力学和声学测量
DOI：
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发表时间：
2007
期刊：
影响因子：
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通讯作者：
G. Caputi
中科院分区：
文献类型：
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作者：
J. Grilliat;Marc C. Jacob;R. Camussi;G. Caputi
低马赫数 (∼ 0.2) 尖端泄漏流的气动声学特性是在里昂中央理工学院的消声风洞设施中进行的。结果表明，叶尖泄漏涡流在翼型上引起的压力脉动在后缘处分散成声音，而另一个高频源似乎与冲击吸力侧主流的喷射状泄漏流有关。这些特征通过 PIV、不稳定壁和远场压力测量以及间隙区域中的两点 PIV-PIV、PIV-压力、HWA-压力和压力-压力交叉统计来证明。该实验是在位于静止介质中的凸缘射流的潜在核心中的单个翼型上进行的。通过加载高弯度箔片获得泄漏流，对攻角、间隙尺寸和流速的参数研究表明，前两者对流动结构有显着影响，而速度主要决定非定常流型的大小。
An aeroacoustic characterisation of Low Mach number (∼ 0.2) tip leakage flows is carried out at the anechoic wind tunnel facility of the Ecole Centrale de Lyon. Results suggest that the pressure fluctuations induced on the airfoil by the tip leakage vortex are scattered into sound at the trailing edge whereas another high frequency source seems to be related to the jet-like leakage flow impinging the main flow on the suction side. These features are evidenced by PIV, unsteady wall and far field pressure measurements as well two points PIV-PIV, PIV-pressure, HWA-Pressure and pressure-pressure cross-statistics in the gap region. The experiment is carried out on a single airfoil located in the potential core of a flanged jet in a medium at rest. The leakage flow is obtained by loading the high camber foil and a parametric study of the angle of attack, the gap size and the flow velocity shows that the two former have a significant impact onto the flow structure whereas the velocity mainly sets the magnitudes of the unsteady flow patterns.