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Numerical simulation of noise generated by shock (wave) and boundary layer interaction in aero-engine inlet

飞机进气道中激波边界层干扰引起噪音的数值模拟

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Abstract

We utilize the nonlinear acoustic solver (NLAS) and Ffowcs-Williams/Hawkings (FW-H) equation to investigate the noise generation and radiation due to shock (wave) and boundary layer interaction (SBLI) in the inlet duct. A classical benchmark for SBLI is chosen to validate the flow features and numerical results show good agreement with experimental results. In the simulation of the noise generated by SBLI, the inlet buzz phenomenon is successfully observed. The oscillation of the normal shock is a kind of little buzz and the oscillation of inner shocks is a kind of big buzz with a frequency around 100 Hz. In the far-field, frequency spectrums show a dominant frequency close to the frequency of inner shocks oscillation. This indicates that the oscillation of inner shocks determines the magnitude of the overall sound pressure level (OASPL) of the far-field noise.

摘要

我们采用非线性声学求解器(NLAS)和Ffowcs-Williams/Hawkings (FW-H)方程对飞机进气道中由激波边界层干扰产生的噪音进行了数值研究. 一个关于激波边界层干扰的标模问题用于验证流场特征, 数值结果与实验结果有很好的一致性. 在模拟激波边界层干扰产生噪音的过程中, 我们成功的观察到了喘振现象. **激波的震荡是一种小喘振, 而内激波的震荡是一种大喘振, 频率大约为100 Hz. 远场噪音频谱表明远场噪音的主导频率与内激波震荡的频率很接**, 这说明, 内激波震荡决定了远场噪音的总声压级的量级.

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Authors and Affiliations

  1. Department of Mechanics and Engineering Science, College of Engineering, Peking University, Bei**g, 100871, China

    Yuanjun Dai  (戴袁鋆) & Yiran An  (安亦然)

  2. School of Civil Engineering, Bei**g Jiaotong University, Bei**g, 100044, China

    Zhi Li  (**植) & Qunfeng Zhang  (张群峰)

Authors
  1. Yuanjun Dai  (戴袁鋆)
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  2. Yiran An  (安亦然)
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  3. Zhi Li  (**植)
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  4. Qunfeng Zhang  (张群峰)
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Corresponding author

Correspondence to Qunfeng Zhang  (张群峰).

Additional information

This work was supported by the National Natural Science Foundation of China (Grant No. 11772314), and the Basic Research Program (Grant No. JCKY2018204b054). The authors would like to acknowledge the Highperformance Computing Platform of Peking University for providing computational resources.

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Dai, Y., An, Y., Li, Z. et al. Numerical simulation of noise generated by shock (wave) and boundary layer interaction in aero-engine inlet. Acta Mech. Sin. 38, 321482 (2022). https://doi.org/10.1007/s10409-021-09009-5

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