基于HHC方法的旋翼噪声抑制机理及参数影响

doi:10.7527/S1000-6893.2017.121000

流体力学与飞行力学

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基于HHC方法的旋翼噪声抑制机理及参数影响

陈丝雨, 招启军, 倪同兵, 朱正

南京航空航天大学直升机旋翼动力学国家级重点实验室, 南京 210016

收稿日期:2016-11-28 修回日期:2017-06-06 出版日期:2017-10-15 发布日期:2017-06-06
通讯作者: 招启军 E-mail:zhaoqijun@nuaa.edu.cn
基金资助:
国家自然科学基金（11572156）；江苏省普通高校研究生科研创新计划项目（KYLX15_0250）；江苏高校优势学科建设工程基金

Rotor noise reduction mechanism and parameter analysis of HHC method

CHEN Siyu, ZHAO Qijun, NI Tongbing, ZHU Zheng

National Key Laboratory of Science and Technology on Rotorcraft Aeromechanics, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Received:2016-11-28 Revised:2017-06-06 Online:2017-10-15 Published:2017-06-06
Supported by:
National Natural Science Foundation of China (11572156);Jiangsu Innovation Program for Graduate Education (KYLX15_0250);Priority Academic Program Development of Jiangsu Higher Education Institutions

摘要/Abstract

摘要：

旋翼桨-涡干扰（BVI）噪声是旋翼气动噪声抑制的主要对象之一。其中，高阶谐波控制（HHC）是一种较为有效的噪声主动抑制方法。为探究HHC方法的降噪效果、降噪机理及参数影响规律，基于嵌套网格生成方法，采用可压雷诺Navier-Stokes方程对流场进行求解，建立了适合于模拟旋翼桨-涡干扰流场的计算流体力学（CFD）数值方法。在流场CFD分析的基础上，采用FW-H（Ffowcs Williams-Hawking）方程预测桨-涡干扰状态下的旋翼噪声，通过对施加高阶谐波控制后的BO-105模型旋翼BVI噪声进行算例验证，得到了一套可以应用于高阶谐波控制下旋翼BVI噪声估算的CFD/FW-H方法。通过对不同HHC方案的数值模拟，发现在直升机斜下降状态下，施加高阶谐波控制后的旋翼BVI噪声能够降低多达4~7 dB。进一步，细致分析了HHC方案的控制频率、输入相位以及输入幅值3个参数对旋翼BVI噪声抑制效果的影响，得到了相关参数的影响规律。并且，基于输入幅值对HHC降噪效果的影响规律，对高阶谐波控制方法的降噪机理做出了进一步的说明。

关键词: 旋翼BVI噪声, RANS方程, FW-H方程, 高阶谐波控制, 参数分析, 降噪机理

Abstract:

Rotor blade-vortex interaction (BVI) noise is one of the main objectives of rotor aerodynamic noise reduction.The higher harmonic control (HHC) method has been demonstrated to be an effective rotor noise reduction method.To obtain noise reduction effects,noise reduction mechanism and parameter effects of the HHC method,a CFD method for simulating blade-vortex interaction is established based on moving-embedded grid method and compressible Reynolds averaged Navier-Stokes (RANS) equations.Based on the previous flowfield calculations and FW-H equations,a noise prediction method CFD/FW-H is established to predict the BVI noise.The case of BO-105 rotor with HHC is calculated using the proposed method.The calculation results obtained by simulating different CFD cases demonstrate that the sound pressure levels of the case with HHC are reduced by 4-7 dB during low speed descent.The effects of the frequency,phase and the amplitude of HHC on rotor BVI noise control have been analyzed.Some conclusions about relative parameter effect rules have been obtained and the mechanism of HHC has been further explained based on the influence of amplitude on noise reduction effects of HHC.

Key words: rotor BVI noise, RANS equations, FW-H equations, higher harmonic control (HHC), parameter analysis, noise reduction mechanism

中图分类号:

V211.3

陈丝雨, 招启军, 倪同兵, 朱正. 基于HHC方法的旋翼噪声抑制机理及参数影响[J]. 航空学报, 2017, 38(10): 121000-121000.

CHEN Siyu, ZHAO Qijun, NI Tongbing, ZHU Zheng. Rotor noise reduction mechanism and parameter analysis of HHC method[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(10): 121000-121000.

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E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

基于HHC方法的旋翼噪声抑制机理及参数影响

Rotor noise reduction mechanism and parameter analysis of HHC method

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