脊状结构用于翼型自噪声控制试验  

Experimental on self-noise control of airfoil with ridge-like structure

作　　者：程文 张成春 孙潇伟[3] 沈淳 吴正阳 陈正武 CHENG Wen;ZHANG Cheng-chun;SUN Xiao-wei;SHEN Chun;WU Zheng-yang;CHEN Zheng-wu(Key Laboratory of Aerodynamic Noise Control,China Aerodynamics Research and Development Center,Mianyang 621000,China;Key Laboratory of Bionics Engineering(Ministry of Education),Jilin University,Changchun 130022,China;Weihai Junming Power Technology Co.,Ltd.,Weihai 264200,China;Weihai Institute of Bionics,Jilin University,Weihai 264200,China)

机构地区：[1]中国空气动力学研究开发中心空气动力噪声控制重点实验室,四川绵阳621000 [2]吉林大学工程仿生教育部重点实验室,长春130022 [3]威海峻铭动力科技有限公司,山东威海264200 [4]吉林大学威海仿生研究院,山东威海264200

出　　处：《吉林大学学报（工学版）》2024年第8期2385-2392,共8页Journal of Jilin University:Engineering and Technology Edition

基　　金：国家重点研发计划项目(2018YFA0703300);气动噪声控制重点实验室开放课题(ANCL20210205);国家自然科学基金项目(52275289,51875243,52305306);吉林省科技发展计划项目(20220508144RC);山东省自然科学基金项目(ZR2023QE209);泰山产业领军人才项目.

摘　　要：本文研究了NACA0012翼型在0°和10°攻角时不同来流速度下的声学性能,声学风洞试验显示,10°攻角时,翼型在30~60 m/s速度范围内产生明显单音噪声,其频率与Arbey声反馈模型预测结果接近。以有效降低单音噪声为导向,本文提出采用脊状结构打破声反馈回路的设想,并探讨脊状结构位置及排布形式对降噪性能的影响规律。结果表明:脊状结构越靠前,降噪效果越明显;随着速度的增加,靠后位置的脊状结构依次不再具有降噪效果。另外,单音噪声的产生只和压力面的流动状态有关,当压力面的流动状态被脊状结构打破后,便无法形成有效的反馈回路。最后,基于Arbey声学反馈理论,探讨了不同位置的脊状结构的降噪性能差异,发现当脊状结构位于叶片压力面最大速度点之前时,可以有效干预流场从而抑制单音噪声的产生。This paper presents an experiment investigation of acoustic properties for NACA0012 airfoil at different freestream velocities with 0°and 10°angle of attack(AOA).The acoustic wind tunnel test results show that at the freestream velocities of 30-60 m/s and AOA=0°,the dominant noise is broadband noise,but at AOA=10°,the dominant noise is switched into tonal noise,and the tonal frequency is close to the Arbey acoustic feedback model.In order to eliminate the tonal noise of airfoil,a flow control method using a ridge-like structure to break the acoustic feedback loop is proposed,and the influence of the position and arrangement of the structure on the noise reduction performance is discussed.The results show that the closer the structure is to the leading edge of the airfoil,the more obvious the noise reduction effect is.With the increase of speed,the ridge-like structure in the back position no longer has a noise reduction effect in turn.In addition,the generation of tonal noise seems to be only related to the flow state of the pressure surface.When the flow state of the pressure surface is broken by the ridge-like structure,an effective feedback loop cannot be formed.Finally,based on the Arbey acoustic feedback theory,the differences in noise reduction performance of ridge-like structures are explored.It was found that when the ridge-like structure is located before the maximum speed point of the blade pressure surface,it can effectively intervene in the flow field to suppress the generation of monophonic noise.

关 键 词：流动噪声控制 脊状结构 翼型噪声实验 翼型自噪声 声反馈回路 

分 类 号：TB53[理学—物理]