目的 针对超声速来流条件下的空腔噪声问题,提出一种基于前壁谐振腔的噪声抑制方法,并探究超声速来流条件下,上述前壁谐振腔的3个参数对空腔噪声抑制效果的影响。方法 采用大涡模拟和计算气动声学相结合的方法对超声速来流条件下开式空腔结构的气动噪声进行数值计算研究,详细分析空腔内的流场特性和声场特性,并将数值计算所得噪声频谱与试验结果进行对比分析,全面验证数值计算方法的准确性。此外,提出一种基于前壁谐振腔的空腔噪声抑制方法。结果 超声速来流条件下,在空腔前壁合理设计谐振腔可有效降低空腔噪声的总声压级幅值、各阶模态声压级幅值和随机噪声声压级幅值,能显著改善空腔内的强噪声环境,有效避免空腔结构及腔内武器装备发生振动及声疲劳破坏,并且前壁谐振腔的深度l、前缘唇厚t和开口大小d均会对其噪声抑制效果产生影响。结论 在实际工程应用时,应根据上述参数对空腔噪声抑制效果的影响进行综合权衡设计,力求使其噪声抑制效果达到最佳。
Abstract
The work aims to propose a noise suppression method based on the front-wall resonant cavity to address the issue of cavity noise under supersonic flow conditions, and explore the influence of the three parameters of the front-wall resonant cavity on the cavity noise suppression effect under supersonic flow conditions. A numerical investigation combining Large Eddy Simulation (LES) and Computational Aeroacoustics (CAA) was conducted to study the aerodynamic noise characteristics of open cavity structures under supersonic flow conditions. Detailed analyses were performed on both the flow field and acoustic field characteristics within the cavity, with comparative validation against experimental results demonstrating the accuracy of the numerical methodology. Furthermore, a novel noise suppression approach utilizing front-wall resonant cavity was proposed. The study revealed that properly designed front-wall resonant cavity in supersonic flow could effectively reduce the overall sound pressure level (OASPL), modal sound pressure level (SPL) amplitudes, and broadband SPL amplitudes within the cavity. This suppression method significantly improved the intense acoustic environment, effectively preventing vibration and acoustic fatigue failure in cavity structures and internal weapon systems. Critical design parameters including resonator depth (l), leading-edge lip thickness (t), and aperture size (d) were identified as key factors influencing noise suppression performance. For optimal engineering applications, comprehensive trade-offs between these parameters should be carefully considered during design optimization to achieve the maximum noise attenuation effect.
关键词
空腔噪声 /
超声速 /
前壁谐振腔 /
噪声抑制 /
大涡模拟 /
总声压级
Key words
cavity noise /
supersonic speed /
front-wall resonant cavity /
noise suppression /
large eddy simulation /
overall sound pressure level
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