旋翼气动噪声快速计算方法研究  

Research on the Rapid Calculation Method of Rotor Aerodynamic Noise

作　　者：李志彬 孙伟[1] 袁明川[1] LI Zhibin;SUN Wei;YUAN Mingchuan(Science and Technology on Rotorcraft Aeromechanics Laboratory,China Helicopter Research and Development Institute,Jingdezhen 333001,China)

机构地区：[1]中国直升机设计研究所直升机旋翼动力学重点实验室,江西景德镇333001

出　　处：《直升机技术》2021年第1期1-7,共7页Helicopter Technique

基　　金：国防基础科研计划资助(JCKY2019205D002)

摘　　要：基于紧致源模型和FW-H方程,建立了一个旋翼气动噪声快速计算模型。其中,采用三维网格对桨叶外形进行精确描述,并结合Farassat 1A公式中的厚度噪声计算公式,以准确计算旋翼桨叶厚度噪声;载荷噪声计算方面,则采用Camrad Ⅱ进行旋翼非定常载荷的计算,并结合Farassat 1A公式的载荷噪声计算公式进行计算;最后将厚度噪声和载荷噪声进行时域叠加来计算旋翼的总噪声。在此基础上,与基于CFD/FW-H方程的旋翼噪声模型进行了计算对比,结果表明:本文方法计算效率远高于CFD/FW-H模型,且在总噪声主要传播方向上,悬停状态下的差值在0.6dB以内,前飞状态下差值在1.0dB以内,具有较好的可靠性,能够用于旋翼噪声的快速评估。Based on the compact source model and FW-H equation,a rapid aerodynamic noise calculation model of rotor was established. Among them,in order to accurately calculate the rotor blade thickness noise,the three-dimensional grid for the blade geometry accurately described,and combined with the thickness noise formula of Farassat 1 A formula,which was the time domain solution of FW-H equation. For computing load noise,this method used Camrad Ⅱ for rotor load calculation,and combined with load noise formula of Farassat 1 A formula. Finally,the thickness noise and load noise were superimposed in time domain to calculate the total noise of the rotor. On this basis,compared with the results based on CFD/FW-H equation of rotor noise model,the results showed that computational efficiency of the method in this paper was much higher than the CFD/FW-H model. The total noise difference on the main direction of propagation was within 0. 6 dB in hover condition and within 1. 0 dB in forward flight condition. The method in this paper had good reliability and could be used for rapid assessment of rotor noise.

关 键 词：紧致源模型 FW-H方程 气动噪声 快速计算 

分 类 号：V211.52[航空宇航科学与技术—航空宇航推进理论与工程]