直升机涵道尾桨气动噪声特性风洞试验研究  

Experimental study on aerodynamic noise characteristics of helicopter ducted tail rotor

作　　者：丁存伟 周国成[1,2,3] 陈宝 仲唯贵[4] DING Cunwei;ZHOU Guocheng;CHEN Bao;ZHONG Weigui(AVIC Aerodynamics Research Institute,Harbin 150001,China;Heilongjiang Provincial Laboratory of Aerodynamic Noise and Control,Harbin 150001,China;Aviation Key Laboratory of Aerodynamics for Low Speed and High Reynolds Number,Harbin 150001,China;China Helicopter Research and Development Institute,Jingdezhen 333000,China)

机构地区：[1]中国航空工业空气动力研究院,哈尔滨150001 [2]黑龙江省空气动力噪声及其控制重点实验室,哈尔滨150001 [3]低速高雷诺数气动力航空科技重点实验室,哈尔滨150001 [4]中国直升机设计研究所,景德镇333000

出　　处：《实验流体力学》2023年第3期107-112,共6页Journal of Experiments in Fluid Mechanics

摘　　要：基于中国航空工业空气动力研究院FL–52航空声学风洞试验条件,对直升机涵道尾桨模型的气动噪声特性进行了试验研究。对试验数据进行了射流剪切层影响修正,获得了涵道尾桨在悬停、前飞状态下的噪声频谱及远场指向性。分析了噪声随桨尖马赫数的变化规律,结果显示涵道尾桨气动噪声符合载荷噪声特性。对比了桨叶沿桨毂周向分布规律对气动噪声频谱特征的影响。获得了悬停和前飞状态下涵道对噪声传播的遮蔽效果影响,悬停状态下尾桨旋转平面内噪声降低约2 dB,前飞状态下尾桨旋转平面内噪声降低5~8 dB。Using the FL–52 aero-acoustic wind tunnel test system of the Aerodynamics Research Institute,the experimental study on the ducted tail rotor noise characteristics is carried out.The influence of the jet shear layer on the test data is corrected,and the noise spectrum and far-field directivity of the culvert tail rotor in hover and forward flight are obtained.The variation laws of the noise with the Mach number of the tail rotor tip are analyzed,and the results show that the aerodynamic noise of the ducted tail rotor conforms to the load noise characteristics.The effects of the blade distribution along the hub on the spectral characteristics of the aerodynamic noise are compared.The shielding noise reduction effect of the duct on the noise propagation under typical working conditions is obtained in hover,the noise in the rotating plane is 2 dB lower than that in other positions in forward flight,the noise reduction in the rotating plane is 5–8 dB.

关 键 词：涵道尾桨 气动噪声 声学风洞 直升机 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]