苍鹰翼尾缘结构的单元仿生叶片降噪机理研究

刘小民 1; 汤虎 1; 王星 1; 席光 1; 高德康 2

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苍鹰翼尾缘结构的单元仿生叶片降噪机理研究

更新时间：2025-07-09

- 苍鹰翼尾缘结构的单元仿生叶片降噪机理研究
- Noise-Reduction Mechanism of Bionic Coupling Blade Based on the Trailing Edge of Goshawk Wing
- 西安交通大学学报 2012年46卷第1期页码：35-41
- 作者机构：
  
  西安交通大学能源与动力工程学院,西安,710049
- 作者简介：
- 基金信息：
  
  : 2011-06-24. 作者简介: 刘小民(1971-),男,副教授. 基金项目: 中央高校基本科研业务费专项基金资助项目(xjj20100073);博士后科学基金面上资助项目(20100481329);中国博士后科学基金特别资助项目(201104665)
- DOI：
  中图分类号： TB535;TH432
- 网络首发：2012-01-10，
  
  纸质出版：2012
- 稿件说明：
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刘小民 1, 汤虎 1, 王星 1, 等. 苍鹰翼尾缘结构的单元仿生叶片降噪机理研究[J]. 西安交通大学学报, 2012,46(1):35-41.

Noise-Reduction Mechanism of Bionic Coupling Blade Based on the Trailing Edge of Goshawk Wing[J]. 2012, 46(1): 35-41.
刘小民 1, 汤虎 1, 王星 1, 等. 苍鹰翼尾缘结构的单元仿生叶片降噪机理研究[J]. 西安交通大学学报, 2012,46(1):35-41. DOI：

Noise-Reduction Mechanism of Bionic Coupling Blade Based on the Trailing Edge of Goshawk Wing[J]. 2012, 46(1): 35-41. DOI：

摘要

利用逆向工程方法提取苍鹰尾缘非光滑形态的降噪特征元素

由此建立了仿生叶片结构模型; 采用基于Smagorinsky亚格子应力模型的大涡模拟

结合基于Lighthill声类比的FW-H方程

分别对仿生尾缘锯齿叶片和标准叶片的流道模型进行了三维流场及声场的数值计算; 通过分析仿生齿形结构对叶尾迹流场的影响

研究了仿生尾缘齿形结构的气流噪声控制机理.结果表明:仿生尾缘锯齿结构叶片的总A计权声压级比标准叶片降低了9.8 dB; 叶片尾缘锯齿结构可以改变流场噪声峰值的分布规律

从而降低了噪声峰值

且大部分频率范围内的气动噪声均有所降低; 仿生尾缘锯齿结构可以改变各截面尾迹涡的脱落位置

从而增大了涡心之间的距离

抑制了脱落涡对尾迹流动的扰动

进而减小了叶片表面的非定常压力脉动和尾迹涡引起的气动噪声.

Abstract

A structural model of the bionic blade was established using the reverse reconstruction technique to extract the noise reduction characteristics of the non-smooth trailing edge shape of the goshawk wing. The LES with the Smagorinsky model and the FW-H equation based on Lighthill acoustic theory were adopted to simulate the flow field and the sound field of the bionic non-smooth trailing edge blade and the smooth blade. The aerodynamic noise control mechanism of the bionic tooth shaped trailing edge blade was examined on the basis of the analysis of the influence of the bionic tooth shaped structure on the trailing edge flow field. The results show that compared with the smooth blade

the total A-weighted sound pressure level of the bionic tooth shaped trailing edge blade decreases by 9.8 dB. The bionic structure changes the distribution of the peak aerodynamic noise

reduces the peak size

and in most of the frequency range

the aerodynamic noise drops. The bionic non-smooth trailing edge of the blade changes the location of vortex shedding in the different cross-section and increases the distance between the corresponding vortex centers

thus suppressing the chaotic flow in the wake region effectively. Therefore

for the bionic blade

the unsteady pressure pulsation on the blade surface is inhibited and the aerodynamic noise caused by the wake vortex is reduced.

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references

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