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AEROACOUSTIC SOURCE OF MULTIPLE CAVITIES AND PREDICTION OF SELF-EXCITED OSCILLATIONS

机译:多腔的航空声源和自激振荡的预测

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Self-sustaining oscillations of flow over ducted cavities and corrugated pipes proved to be a potential source of tonal noise and possible failure in industrial applications. Most of the recent studies focused on the flow over a single cavity to simplify the problem and establish basic understanding of the phenomenon. This paper investigates experimentally the flow over multiple cavities, specifically two and three-cavity configurations, and the results are compared with those of a single cavity. Two different categories of experiments were performed in this study. The first category of measurements quantified the aeroacoustic source of various cavity configurations as a function of Strouhal numbers and acoustic velocity of the resonant pipe mode. The cavities are situated at the acoustic pressure node of a piping system which was sufficiently long to maintain the acoustic velocity fairly constant along the test section. The second category involved self-excited oscillations where the cavities were tested in a short piping system. The flow velocity was gradually increased and the acoustic pressure amplitude and frequency were measured and the lock-in ranges for different shear layer modes were identified. A semi-empirical model is then developed to use the measured source to predict the self-excited oscillation amplitude.
机译:事实证明,在管腔和波纹管上流动的自我维持振荡是潜在的色调噪声源,并可能在工业应用中引起故障。最近的大多数研究都集中在单个腔体上的流动,以简化问题并建立对该现象的基本理解。本文通过实验研究了多个腔体(特别是两个和三个腔体)上的流动,并将结果与​​单个腔体进行了比较。在这项研究中进行了两种不同类别的实验。第一类测量将各种腔体构造的空气声源量化为斯托鲁哈尔数和共振管道模式的声速的函数。空腔位于管道系统的声压节点处,该声压节点的长度足够长,可以使沿着测试部分的声速保持相当恒定。第二类涉及自激振荡,其中在短管道系统中对空腔进行了测试。逐渐增加流速,并测量声压幅值和频率,并确定不同剪切层模式的锁定范围。然后建立一个半经验模型,以使用测得的源来预测自激振荡幅度。

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