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首页> 外文期刊>Journal of Engineering for Gas Turbines and Power >Jet-Surface Interaction Test: Far-Field Noise Results
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Jet-Surface Interaction Test: Far-Field Noise Results

机译:喷射表面相互作用测试:远场噪声结果

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Many configurations proposed for the next generation of aircraft rely on the wing or other aircraft surfaces to shield the engine noise from the observers on the ground. However, the ability to predict the shielding effect and any new noise sources that arise from the high-speed jet flow interacting with a hard surface is currently limited. Furthermore, quality experimental data from jets with surfaces nearby suitable for developing and validating noise prediction methods are usually tied to a particular vehicle concept and, therefore, very complicated. The Jet-Surface Interaction Tests are intended to supply a high quality set of data covering a wide range of surface geometries and positions and jet flows to researchers developing aircraft noise prediction tools. The initial goal is to measure the noise of a jet near a simple planar surface while varying the surface length and location in order to: (1) validate noise prediction schemes when the surface is acting only as a jet noise shield and when the jet-surface interaction is creating additional noise, and (2) determine regions of interest for future, more detailed, tests. To meet these objectives, aflat plate was mounted on a two-axis traverse in two distinct configurations: (1) as a shield between the jet and the observer and (2) as a reflecting surface on the opposite side of the jet from the observer. The surface length was varied between 2 and 20 jet diameters downstream of the nozzle exit. Similarly, the radial distance from the jet centerline to the surface face was varied between 1 and 16 jet diameters. Far-field and phased array noise data were acquired at each combination of surface length and radial location using two nozzles operating at jet exit conditions across several flow regimes: subsonic cold, subsonic hot, underexpanded, ideally expanded, and overexpanded supersonic. The far-field noise results, discussed here, show where the jet noise is partially shielded by the surface and where jet-surface interaction noise dominates the low frequency spectrum as a surface extends downstream and approaches the jet plume.
机译:为下一代航空器提出的许多配置都依靠机翼或其他航空器表面来屏蔽来自地面观察者的发动机噪音。但是,目前,预测屏蔽效果以及由高速射流与坚硬表面相互作用产生的任何新噪声源的能力受到限制。此外,来自附近具有适于开发和验证噪声预测方法的表面的喷射器的高质量实验数据通常与特定的车辆概念相关,因此非常复杂。喷射表面相互作用测试旨在为开发飞机噪声预测工具的研究人员提供涵盖范围广泛的表面几何形状和位置以及喷射流的高质量数据集。最初的目标是在改变平面长度和位置的同时测量简单平面附近的射流噪声,以便:(1)当表面仅充当射流噪声屏障并且当射流产生噪声时,验证噪声预测方案表面相互作用会产生额外的噪声,并且(2)确定感兴趣的区域,以便将来进行更详细的测试。为了达到这些目的,将平板以两种不同的方式安装在两轴导线板上:(1)作为射流与观察者之间的屏蔽,(2)作为射流与观察者相对的一侧的反射面。表面长度在喷嘴出口下游的2到20个喷嘴直径之间变化。类似地,从喷嘴中心线到表面的径向距离在1到16个喷嘴直径之间变化。使用在两个流态下的射流出口条件下运行的两个喷嘴,在表面长度和径向位置的每种组合下获取远场和相控阵噪声数据:亚音速冷,亚音速热,膨胀不足,理想膨胀和超音速超音速。此处讨论的远场噪声结果显示,喷射噪声被表面部分屏蔽,并且当表面向下游延伸并接近喷射羽流时,喷射表面相互作用噪声主导低频频谱。

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