Characteristics of jet noise: A synthesis

IF 1.2 4区 工程技术 Q3 ACOUSTICS International Journal of Aeroacoustics Pub Date : 2024-05-09 DOI:10.1177/1475472x241230653
K. Viswanathan
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Abstract

It is a distinct privilege to produce this article to honor Professor Tam, the foremost authority on jet aeroacoustics. The fundamental characteristics of jet noise have been studied for 70 years, since the pioneering work of Lighthill in the 1950s. The acoustic analogy, with many variants, has served as the leading theory for nearly 50 years. Many leading researchers in the 1970s formulated theories to interpret the measured trends from subsonic and supersonic jets, using acoustic analogy and flow features as the framework. Quadrupoles, dipoles and monopoles were believed to constitute the sources of noise. The discovery of large-scale organized structures in free shear layers and jets sparked a different avenue of thinking about their importance for noise generation. Tam was the first to clearly demonstrate that these structures are efficient generators of noise and constitute the dominant noise sources, especially in the downstream direction. Now, two schools of thought emerged on the sources of jet noise. Experimental measurements showed that the mean flow as well as the turbulence statistics exhibit a self-similarity in the mixing layer and another similarity in the fully developed jet. Based on these observations, Tam proposed that since noise is generated by the turbulence of the jet, the noise spectra generated by fine-scale and large-scale turbulence should also exhibit self-similarity. By examining a large set of supersonic jet noise data acquired at NASA Langley, Tam offered evidence that the turbulent mixing noise of high-speed jets does consist of two independent self-similar components. In this paper, experimental evidence is compiled from an extensive database that quantifies the effect of several parameters that affect jet spectra. A new scaling method is developed and extended to noise predictions for realistic dual-stream nozzle geometries. The objectives of this paper are to serve as a synthesis of noise characteristics and to focus on application to real-world problems. Results from five different experimental measurements are examined: (1) farfield spectral characteristics; (2) azimuthal and polar correlations in the farfield; (3) correlations of jet turbulence fluctuations and farfield sound; (4) measurement of source distributions with an elliptic mirror; and (5) space-time correlation measurements in the nearfield with a cage array, and nearfield-farfield correlations. Two distinctly different trends are observed in the angular ranges of 50° – ∼120° and ∼120° – 165° for all the parameters investigated with the above five approaches. The salient observations are mutually supporting, and the cumulative weight lends credence to the proposition that there are two distinct sources of turbulent mixing noise.
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喷气噪声的特征:综述
能够撰写这篇文章,向喷气机航空声学领域最权威的谭教授致敬,我深感荣幸。自 20 世纪 50 年代莱特希尔的开创性工作以来,对喷气机噪声基本特征的研究已有 70 年之久。近 50 年来,声学类比以及许多变体一直是主要理论。20 世纪 70 年代,许多著名研究人员以声学类比和流动特征为框架,提出了解释亚音速和超音速喷气机测量趋势的理论。四极子、偶极子和单极子被认为是噪声的来源。在自由剪切层和喷流中发现大尺度有组织结构后,人们开始从另一个角度思考它们对噪声产生的重要性。Tam 首次清楚地证明,这些结构是高效的噪声发生器,是主要的噪声源,尤其是在下游方向。现在,关于喷气噪声的来源出现了两种观点。实验测量表明,平均流和湍流统计在混合层中表现出自相似性,而在完全发展的射流中则表现出另一种相似性。基于这些观察结果,Tam 提出,由于噪声是由喷流的湍流产生的,因此细尺度和大尺度湍流产生的噪声谱也应表现出自相似性。通过研究美国国家航空航天局兰利分局获得的大量超音速喷气机噪声数据,Tam 提供的证据表明,高速喷气机的湍流混合噪声确实由两个独立的自相似成分组成。本文从一个庞大的数据库中整理出实验证据,量化了影响喷流频谱的几个参数的效果。本文开发了一种新的缩放方法,并将其扩展到实际双流喷嘴几何形状的噪声预测中。本文的目的是对噪声特性进行综合分析,并侧重于实际问题的应用。本文研究了五种不同的实验测量结果:(1) 远场频谱特性;(2) 远场的方位角和极性相关性;(3) 喷射湍流波动与远场声音的相关性;(4) 利用椭圆镜测量声源分布;(5) 利用笼式阵列测量近场的时空相关性,以及近场与远场的相关性。在 50° - ∼120° 和 ∼120° - 165° 的角度范围内,对上述五种方法研究的所有参数观察到两种截然不同的趋势。突出的观测结果是相互支持的,累积的权重使人相信湍流混合噪声有两个不同的来源。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
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来源期刊
International Journal of Aeroacoustics
International Journal of Aeroacoustics ACOUSTICS-ENGINEERING, AEROSPACE
CiteScore
2.10
自引率
10.00%
发文量
38
审稿时长
>12 weeks
期刊介绍: International Journal of Aeroacoustics is a peer-reviewed journal publishing developments in all areas of fundamental and applied aeroacoustics. Fundamental topics include advances in understanding aeroacoustics phenomena; applied topics include all aspects of civil and military aircraft, automobile and high speed train aeroacoustics, and the impact of acoustics on structures. As well as original contributions, state of the art reviews and surveys will be published. Subtopics include, among others, jet mixing noise; screech tones; broadband shock associated noise and methods for suppression; the near-ground acoustic environment of Short Take-Off and Vertical Landing (STOVL) aircraft; weapons bay aeroacoustics, cavity acoustics, closed-loop feedback control of aeroacoustic phenomena; computational aeroacoustics including high fidelity numerical simulations, and analytical acoustics.
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