前缘缝翼噪声特性及其控制研究

发布时间：2018-07-10 07:49

本文选题：气动声学 + 缝翼噪声　；参考：《南京航空航天大学》2016年硕士论文

【摘要】：民用飞机的噪声问题不仅关系到飞机的适航取证,还关系到其舒适性要求。前缘缝翼噪声是飞机在起飞和着陆阶段主要的机体噪声源,开展缝翼噪声分析及控制研究有着重要意义。缝翼噪声的预测、控制和降低需要彻底认识其流动和噪声机理,本文详细总结了两种翼型的缝翼空腔流动和致声机理。在此基础上,引入了两种噪声控制方法。其中一种是吸气控制,通过数值仿真验证了其有效性;另一种是基于压电材料的振动激励控制,通过实验分析了其控制效果。本文的研究工作主要由以下三个部分组成:1、综述了国内外对缝翼噪声机理、预测和控制的研究现状,并从流体动力学和声学的基本方程出发,介绍了气动声学的基本理论。2、通过数值仿真研究了三段翼型的气动和声学特性,研究结果表明缝翼再附着区域是一个强烈的噪声源。在此基础上,有针对性地提出了一种基于再附着区域吸气的噪声控制方法,并深入研究了其对流场和声场的影响。引入吸气控制并不会影响该翼型的高升力特性,能显著降低再附着区域的涡壁干扰强度,进而降低了缝翼噪声。数值结果表明缝翼的低频宽带噪声和多峰值噪声都有一定程度降低。3、通过实验研究了两段翼型的流场和声场特性,应用声强测量技术识别出了缝翼多峰值噪声,并提出和验证了一种基于振动激励的噪声控制方法。实验结果表明引入振动激励打破了缝翼空腔内的回流反馈,对缝翼的多峰值噪声有一定影响。
[Abstract]:The noise of civil aircraft is not only related to the proof of airworthiness, but also related to the requirement of comfort. The front wing noise is the main noise source in the take-off and landing stages of aircraft. It is of great significance to study the noise analysis and control of the slit wing. The prediction, control and reduction of slit noise require a thorough understanding of its flow and noise mechanism. In this paper, the cavity flow and acoustic mechanism of two airfoils are summarized in detail. On this basis, two noise control methods are introduced. One is inspiratory control, which is validated by numerical simulation, and the other is vibration excitation control based on piezoelectric material. The control effect is analyzed by experiments. The research work in this paper consists of the following three parts: 1. The research status of noise mechanism, prediction and control of slit wing at home and abroad is summarized, and the basic equations of hydrodynamics and acoustics are discussed. The basic theory of aero-acoustics. 2. The aerodynamic and acoustic characteristics of the three-stage airfoil are studied by numerical simulation. The results show that the reattachment region of the slit wing is a strong noise source. On this basis, a new noise control method based on reattachment region is proposed, and the influence of the flow field and sound field is studied. The introduction of inspiratory control does not affect the lift characteristics of the airfoil and can significantly reduce the intensity of vortex wall interference in the reattachment region and thus the slit wing noise. The numerical results show that the low frequency wideband noise and multi-peak noise of slit wing are reduced to a certain extent. The characteristics of flow field and sound field of two airfoils are studied experimentally, and the multi-peak noise of slit wing is identified by using sound intensity measurement technique. A noise control method based on vibration excitation is proposed and validated. The experimental results show that the vibration excitation breaks the reflux feedback in the slot cavity and has a certain effect on the multi-peak noise of the slit wing.
【学位授予单位】：南京航空航天大学
【学位级别】：硕士
【学位授予年份】：2016
【分类号】：V224.5

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