不同翼型厚度和来流马赫数下的桨涡干扰噪声分析  

Analysis on Rotor Vortex Interference Noise Under Different Airfoil Thickness and Free-stream Mach Number

作　　者：相倩 余启梁 王钢林 刘勇[2] 叶海剑 Xiang Qian;Yu Qiliang;Wang Ganglin;Liu Yong;Ye Haijian(Chinese Aeronautical Establishment,Beijing 100029,China;Nanchang Hangkong University,Nanchang 330063,China)

机构地区：[1]中国航空研究院,北京100029 [2]南昌航空大学,江西南昌330063

出　　处：《航空科学技术》2023年第6期11-19,共9页Aeronautical Science & Technology

基　　金：国家自然科学基金(11962018,12262023)。

摘　　要：桨涡干扰噪声是直升机气动噪声主要组成之一,为了正确预测和降低直升机噪声,必须开展气动噪声相关物理参数研究。在对声场进行计算流体力学(CFD)直接数值模拟的基础上,分析了不同厚度和来流马赫数下二维平行桨涡干扰噪声传播特性和声源位置,分析了翼型厚度和来流马赫数对桨涡干扰噪声的影响,并得到了可压缩情况下远场声压预测公式。研究表明,低马赫数下,翼型厚度对噪声指向性影响不大,高马赫数下,翼型厚度对噪声指向性影响程度增大;噪声强弱主要随来流马赫数变化,翼型厚度对其影响较小;翼型厚度和来流马赫数变化不会改变声源点位置。开展不同翼型厚度和来流马赫数下的桨涡干扰噪声分析可以为进一步了解并控制直升机桨涡干扰噪声提供一定的参考。Blade-vortex interaction noise is one of the main components of helicopter aerodynamic noise.In order to correctly predict and reduce helicopter noise,it is necessary to conduct research on physical parameters related to aerodynamic noise.Based on the direct numerical simulation of the acoustic field using Computational Fluid Dynamics(CFD),the propagation characteristics and sound source location of two-dimensional parallel propeller blade-vortex interference noise under different thicknesses and free-stream Mach numbers are analyzed.The effects of airfoil thickness and free-stream Mach number on propeller blade-vortex interference noise are analyzed,and the prediction formula for far field sound pressure in compressible cases is obtained.The research shows that at low Mach number,the influence of airfoil thickness on noise directivity is not significant,while at high Mach number,the influence of airfoil thickness on noise directivity increases;The noise intensity mainly varies with the free-stream Mach number,and the influence of airfoil thickness is small;Variations of airfoil thickness and free-stream Mach number do not change the location of the sound source point.This research provides a certain reference value for further study on controlling the blade-vortex interaction noise of helicopters.

关 键 词：翼型厚度 来流马赫数 二维平行BVI 气动噪声 直接法 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]