翼型前缘宏观点阵结构气动噪声控制方法

doi:10.13229/j.cnki.jdxbgxb.20240669

吉林大学学报(工学版) ›› 2026, Vol. 56 ›› Issue (1): 86-95.doi: 10.13229/j.cnki.jdxbgxb.20240669

翼型前缘宏观点阵结构气动噪声控制方法

沈淳¹(),李壮¹,孟晋¹,孙潇伟²,张成春²(),陈正武³,梁东⁴

^1.吉林大学汽车工程学院长春 130022
^2.吉林大学工程仿生教育部重点实验室长春 130022
^3.中国空气动力学研究开发中心空气动力噪声控制重点实验室，四川绵阳 621000
^4.中国航空发动机集团有限公司中国航空发动机研究院，北京 101304

收稿日期:2024-05-15 出版日期:2026-01-01 发布日期:2026-02-03
通讯作者: 张成春 E-mail:shench@jlu.edu.cn;jluzcc@jlu.edu.cn
作者简介:沈淳（1983-），男，副教授，博士.研究方向：飞行器噪声预测控制.E-mail： shench@jlu.edu.cn
基金资助:
吉林省科技发展计划项目(SKL202602016JC);长春市科技发展计划项目(25ZSLX11);国家自然科学基金项目(52275289)

Controlling aerodynamic noise of macroscopic point array structure on leading edge of airfoil

Chun SHEN¹(),Zhuang LI¹,Jin MENG¹,Xiao-wei SUN²,Cheng-chun ZHANG²(),Zheng-wu CHEN³,Dong LIANG⁴

^1.College of Automotive Engineering，Jilin University，Changchun 130022，China
^2.Key Laboratory of Engineering Bionics，Ministry of Education，Jilin University，Changchun 130022，China
^3.Key Laboratory of Aerodynamic Noise Control，China Aerodynamics Research and Development Center，Mianyang 621000，China
^4.Aero-Engine Academy of China，Aero-Engine Corporation of China，Beijing 101304，China

Received:2024-05-15 Online:2026-01-01 Published:2026-02-03
Contact: Cheng-chun ZHANG E-mail:shench@jlu.edu.cn;jluzcc@jlu.edu.cn

摘要/Abstract

摘要：

在标准NACA0012翼型前缘设计了点阵（点阵列）扰流结构，在来流攻角0°、速度20 m/s和30 m/s的条件下，在声学风洞测试验证了凸点阵列具有明显降噪效果。与标准翼型相比，20 m/s来流条件下点阵前缘翼型总声压级降噪量达3.6 dB；30 m/s来流条件下点阵翼型噪声频谱曲线各处均低于声学风洞背景噪声，而标准翼型总声压级与背景噪声相比高1.5 dB，即在30 m/s来流条件下，点阵翼型总声压级降噪量至少为1.5 dB。采用大涡模拟（Large eddy simulation， LES）/FW-H（Ffowcs williams hawkings）声学比拟混合预测方法，从翼型表面压力扰动源展向相干性角度阐释了前缘点阵翼型降噪机制。针对30 m/s来流条件下声学风洞测试结果无法完全反映点阵翼型真实降噪效果的问题，采用数值方法比较了20 m/s和30 m/s两种来流条件声压级频谱特征，发现点阵结构在两种速度下具有几乎相同的降噪效果。最后，系统分析了前缘阵列结构高度和排数等参数对降噪效果的影响规律，为前缘阵列扰流结构工程参数化设计提供了支撑。

关键词: 流动噪声控制, 翼型叶片, 混合预测, 气动噪声, 流动控制, 展向相干性

Abstract:

In this paper， a point array turbulence structure is designed at the leading-edge of the standard NACA0012 airfoil， and the bump array has obvious noise reduction effect under the condition of 20 m/s and 30 m/s at the 0° angle of attack of the incoming flow， and the speed of 20 m/s and 30 m/s. Compared with the standard airfoil， the noise reduction of the total sound pressure level of the lattice leading edge airfoil is 3.6 dB under the condition of 20 m/s incoming flow， and the noise spectrum curve of the point array airfoil is lower than that of the acoustic wind tunnel background noise at 30 m/s， while the total sound pressure level of the standard airfoil is 1.5 dB higher than that of the background noise， that is， the noise reduction of the total sound pressure level of the point array airfoil is at least 1.5 dB under the condition of 30 m/s incoming flow. The LES （Large eddy simulation）/FW-H （Ffowcs williams hawkings） acoustic comparison hybrid prediction method is used to illustrate the noise reduction mechanism of the leading-edge array airfoil from the perspective of the spread coherence of the source of airfoil surface pressure disturbance. In order to solve the problem that the acoustic wind tunnel test results under the 30 m/s incoming flow condition cannot fully reflect the real noise reduction effect of the lattice airfoil， the spectral characteristics of the sound pressure level under the 20 m/s and 30 m/s incoming flow conditions are compared by numerical methods， and it is found that the lattice structure has almost the same noise reduction effect at the two speeds. Finally， the influence of parameters such as height and number of rows on the noise reduction effect of the leading-edge array structure was systematically analyzed， which provided support for the engineering parametric design of the leading-edge array turbulence structure.

Key words: flow noise control, airfoil blades, hybrid forecasting, aerodynamic noise, flow control, directional coherence

中图分类号:

TP27

沈淳,李壮,孟晋,孙潇伟,张成春,陈正武,梁东. 翼型前缘宏观点阵结构气动噪声控制方法[J]. 吉林大学学报(工学版), 2026, 56(1): 86-95.

Chun SHEN,Zhuang LI,Jin MENG,Xiao-wei SUN,Cheng-chun ZHANG,Zheng-wu CHEN,Dong LIANG. Controlling aerodynamic noise of macroscopic point array structure on leading edge of airfoil[J]. Journal of Jilin University(Engineering and Technology Edition), 2026, 56(1): 86-95.

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模型	速度 v/（m·s^-1）	柱体结构	高度 H/mm	排数
M0（BAS）	20	无	0	0
M1	20	有	0.75	5
M2（BAS）	30	有	0	0
M3	30	有	0.75	5
M4	20	有	0.5	5
M5	20	有	0.25	5
M6	20	有	0.75	3

试验数据来源	本文	参考文献［16］
峰值噪声降噪量/dB	8.67	11.29
总声压级降噪量/dB	1.49	1.75

翼型前缘宏观点阵结构气动噪声控制方法

Controlling aerodynamic noise of macroscopic point array structure on leading edge of airfoil

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