旋翼桨涡干扰噪声特性试验技术研究  

Study on Characteristic of Rotor-Blade Vortex Interaction Noise

作　　者：刘正江 黄建萍[1] 陈焕[1] 汪文涛 LIU Zhengjiang;HUANG Jianping;CHEN Huan;WANG Wentao(Science & 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》2019年第1期43-47,42,共6页Helicopter Technique

基　　金：国防基础科研计划(***0110047)资助

摘　　要：利用改进的涡发生器,在全消声试验室进行桨涡干扰噪声特性试验;随后采用多圈整周期平均和阶次分析方法对桨涡干扰噪声频谱特性和声场分布特性进行了分析。结果显示多圈整周期平均不仅能够抑制无关噪声,同时能很好地保持桨涡干扰噪声特征波形。选择最大声压对应的阶次进行分析,获得了规律明显的不同出涡速度下的声场分布图,从而证明了相关试验技术的有效性。With the improved design of vortex generator, rotor blade vortex interaction noise test was completed in anechoic chamber. When analysis, the test data was cut out to 100 complete period data according with speed signal, and averaged to one period data , and then took with order analysis, and finally the characteristic of spectral and sound field distribution was also gave out. Furthest, the validity of the complete period average and the regularity of sound field distribution was stable and reliable through the analysis results.

关 键 词：涡发生器 消声试验室 桨涡干扰 整周期平均 声场分布 

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] V216.54