分布式涵道尾桨气动噪声特性研究  

Research on Aeroacoustic Characteristics of Distributed Ducted Tail Rotor

作　　者：王菲 张威[1] 唐兴中 陈国军[1] 建志旭 WANG Fei;ZHANG Wei;TANG Xingzhong;CHEN Guojun;JIAN Zhixun(China Helicopter Research and Development Institute,Jingdezhen 333001,China;Chinese Aeronautical Establishment,Beijing 100012,China)

机构地区：[1]中国直升机设计研究所,景德镇333001 [2]中国航空研究院,北京100012

出　　处：《南京航空航天大学学报》2023年第2期202-208,共7页Journal of Nanjing University of Aeronautics & Astronautics

基　　金：中国航空研究院“五性”技术研究自立项目。

摘　　要：为研究新型分布式涵道尾桨噪声特性,建立了基于滑移网格和可穿透积分面的分布式涵道尾桨气动、噪声特性分析方法并验证了方法的有效性。流动控制方程采用非定常雷诺平均N-S方程,空间离散采用二阶逆风Roe格式,时间推进方法采用隐式LU-SGS格式,湍流模型采用S-A一方程湍流模型,噪声求解方法采用FW-H方程。基于建立的方法,对比分析了传统变总距孤立尾桨和电动变转速多涵道尾桨气动与噪声特性。结果表明:相同气动力状态下,相比于变总距孤立尾桨,在尾桨噪声主要影响方位(桨盘平面内),三涵道尾桨噪声降低5~6 dB。随着转速降低,分布式涵道尾桨噪声声压级逐渐降低。In order to study the aeroacoustic characteristics of the new distributed tail rotor,the method used for the calculation of distributed ducted tail rotor aerodynamic and acoustic is established based on the sliding mesh method and penetrable surface.The Reynolds-averaged Navier-Stokes is used as the govern equation.The second order Roe scheme is used for spatial dispersion.The implicit LU-SGS scheme is applied to the pseudo-time marching.The S-A turbulence model is selected.The FW-H equation is used to calculate the noise.By the established method,the aerodynamic and acoustic characteristics of traditional tail rotor and distributed ducted tail rotor are calculated.The results indicated that compared with the traditional tail rotor,for the typical radiation direction,namely the tip-path-plane,the noise amplitude of distributed ducted tail rotor is reduced by 5—6 dB under the same aerodynamics,and with the decrease of rotor speed,the noise amplitude is decreased further.

关 键 词：直升机 电动尾桨 分布式涵道尾桨 气动噪声 

分 类 号：V233[航空宇航科学与技术—航空宇航推进理论与工程]