旋翼桨-涡干扰噪声特性风洞试验研究  

Wind tunnel test research on the characteristics of rotor blade-vortex interaction noise

作　　者：刘向楠 刘少腾 周国成[1,2,3] 邵天双[1,2,3] 陈宝[1,2,3] LIU Xiangnan;LIU Shaoteng;ZHOU Guocheng;SHAO Tianshuang;CHEN Bao(AVIC Aerodynamics Research Institute,Harbin 150001,China;Low Speed High Reynolds Number Aeronautical Key Laboratory,AVIC Aerodynamics Research Institute,Harbin 150001,China;Aerodynamic Noise and Control Key Laboratory of Heilongjiang Province,AVIC Aerodynamics Research Institute,Harbin 150001,China)

机构地区：[1]中国航空工业空气动力研究院,哈尔滨150001 [2]中国航空工业空气动力研究院低速高雷诺数航空科技重点实验室,哈尔滨150001 [3]中国航空工业空气动力研究院黑龙江省空气动力噪声及其控制重点实验室,哈尔滨150001

出　　处：《实验流体力学》2023年第3期84-91,共8页Journal of Experiments in Fluid Mechanics

摘　　要：在中国航空工业空气动力研究院FL–10风洞中开展了旋翼桨–涡干扰噪声传播特性试验,对BO–105主旋翼40%缩比模型中等前飞速度爬升、平飞、斜下降状态的气动噪声进行了测量。首先采用Heyson洞壁干扰修正方法确定风洞试验时的旋翼下滑角,通过气流内测量阵列移动获得了桨盘平面下方完整的噪声辐射场,然后对不同飞行状态下的桨–涡干扰噪声传播特性进行了分析,得到了典型状态的声压–时间历程、频谱和声压级云图。结果表明:旋翼斜下降飞行状态出现了明显的桨–涡干扰噪声,干扰较强时桨叶前行侧和后行侧都会产生桨–涡干扰噪声,且其传播具有明显的方向性,即前行侧指向桨盘上游和桨盘下方,后行侧指向桨盘下游。The propagation characteristics of the blade–vortex interaction(BVI)noise were tested in the FL–10 wind tunnel of AVIC Aerodynamics Research Institute.The aerodynamic noise of climb,level flight and descent at medium forward speed was measured on a 40%scale model of BO−105 main rotor.Firstly,the“Heyson”wall interference correction method was used to determine the descent angle of the rotor in the wind tunnel,and the complete noise radiation field under the rotor tip–path–plane was obtained through the movement of the measurement array in the airflow.Furthermore,the BVI noise characteristics of the rotor under different flight condition were studied,and the sound pressure time history,spectrum and sound pressure level contour were given.The results indicate that the BVI phenomena occur on both the advancing and retreating side under the descent flight condition.The noise has strong directivity,and radiates toward upstream under the rotor disk toward the advancing side and the downstream on the retreating side.

关 键 词：直升机 风洞试验 桨–涡干扰 气动噪声 旋翼 斜下降飞行 

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]