大型飞机增升装置气动噪声研究进展  

Developments of aeroacoustic investigation on high-lift device for large aircrafts

作　　者：刘沛清[1] 李玲[1] 邢宇[1] 郭昊[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100019

出　　处：《空气动力学学报》2017年第4期472-484,共13页Acta Aerodynamica Sinica

摘　　要：目前,机体气动噪声的研究方法分成实验和数值预测两大部分,实验包含飞行实验和风洞试验;而数值预测包含有纯理论方法、半经验方法、纯数值方法、CFD与"声类比"相结合的方法。经过大量的飞行实验,风洞试验和数值计算,研究表明在飞机起飞爬升和着陆进场阶段,除机轮气动噪声外,增升装置气动噪声是机体噪声的主要声源,经过多年的研究基本明确了增升装置气动噪声源的定位和机理,并在降噪技术方面已取得一定进展。增升装置的噪声主要是由前缘缝翼凹槽产生的低频噪声、襟翼侧缘的中频宽带噪声和前缘缝翼尾缘的高频尖峰噪声三部分组成,降噪技术主要有被动流动控制降噪技术和主动流动控制降噪技术两类,被动降噪技术有凹槽遮挡、凹槽填充、展向连续技术等;主动流动控制手段有吹吸气、等离子体激励器等。Current method for airframe acoustic study can be categorized into prediction methodologies and experimental measurements. The experimental measurements include tllgtat test and wind tunnel experiment. The noise prediction methodologies consist of fully analytic method, semi-empirical method, computational fluid dynamics （CFD） combining with acoustic analogy method, and fully numerical method. Over the last decades, a considerable amount of work has been conducted on noise source identification, noise mechanism, noise reduction techniques and so on. A high-lift device noise is generally categorized into three parts： low- frequency tones generated from the slat cove, mid-frequency broadband noise generated from the flap side edge, and high-frequency tones generated from the slat trailing edge. The noise reduction techniques for the high-lift device have active and passive types, including slat cove cover, slat cove filler, and continuous mold line for the passive one and blowing-suction air and plasma actuation for the active one.

关 键 词：气动噪声 增升装置 降噪技术 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]