目的 显著降低空腔噪声问题对先进飞行器、动力装置等研制的影响,以及提高空腔噪声数值计算精度。方法 采用大涡模拟和计算气动声学相结合的方法,对典型开式空腔噪声进行数值计算,分析空腔噪声的产生机理、总声压级分布特性和典型监测点的噪声频谱特性,研究大涡模拟不同亚格子尺度模型对数值计算结果的影响,提出一种基于空腔前后壁修形的噪声抑制方法。结果 计算采用不同亚格子尺度模型时空腔噪声的总声压级分布和噪声频谱,发现采用WALE（Wall Adapting Local Eddy Viscosity）模型时数值计算结果与试验值吻合最好,采用DSM（Dynamic Smagorinsky-Lilly）模型时次之,采用SM（Smagorinsky-Lilly）模型时误差相对最大。此外,还计算了前后壁修形对空腔噪声的抑制效果,发现其能显著改善腔内的强噪声环境。不同亚格子尺度模型会对空腔噪声数值计算结果产生影响,采用WALE模型的数值计算结果与试验值最接近。此外,空腔前后壁修形可显著抑制空腔噪声,Ma=0.85和Ma=0.6时,腔内总声压级最大降幅分别达到了7.82、6.63 dB,主模态声压级分别降低了4.56、5.65 dB,同时主模态频率向低频分别移动了27.14、27.22 Hz。结论 主模态频率的大幅移动可避开空腔声共振频率,有效避免了空腔结构及腔内武器装备发生随机振动,甚至声疲劳破坏。
Abstract
To significantly reduce the impact of cavity noise on development of advanced aircraft and propulsion systems, and to improve the numerical simulation accuracy of cavity noise, this study combines Large Eddy Simulation (LES) and Computational Aeroacoustics (CAA) to numerically investigate a typical open cavity. The generation mechanism of cavity noise, the distribution of the overall sound pressure level (OASPL), and the spectral characteristics at representative monitoring points are analyzed. The impact of different subgrid-scale (SGS) models in LES on numerical results is examined, and a noise suppression method based on geometric modifications to the front and rear cavity walls is proposed. The distribution of total sound pressure level and the noise spectrum of the space-time cavity noise using SGS models are calculated. It is reveal that the Wall Adapting Local Eddy Viscosity (WALE) model achieves the closest agreement with experimental data, followed by the Dynamic Smagorinsky-Lilly (DSM) model, while the standard Smagorinsky-Lilly (SM) model exhibits the largest discrepancies. Additionally, geometric modifications to the cavity walls demonstrate significant noise suppression effects. The results indicate that the choice of SGS models critically affects numerical accuracy, with the WALE model providing the most reliable predictions. Furthermore, the geometric modifications to the cavity walls demonstrate significant noise suppression effects: the maximum reductions in OASPL reach 7.82 dB and 6.63 dB at Mach numbers (Ma) of 0.85 and 0.6, respectively. The dominant modal sound pressure levels are reduced by 4.56 dB and 5.65 dB, while the primary modal frequencies shift toward lower frequencies by 27.14 Hz and 27.22 Hz, respectively. This substantial frequency shift effectively avoids resonance frequencies of the cavity, thereby preventing random vibrations and potential acoustic fatigue damage to the cavity structure and internal equipment.
关键词
空腔噪声 /
噪声控制 /
大涡模拟 /
亚格子尺度模型 /
噪声频谱 /
总声压级
Key words
cavity noise /
noise suppression /
Large Eddy Simulation (LES) /
subgrid-scale (SGS) model /
noise spectrum /
overall sound pressure level (OASPL)
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