【作者】 彭延辉；

【导师】 徐国华；

【作者基本信息】 南京航空航天大学 ， 飞行器设计， 2004， 硕士

【摘要】 旋翼桨-涡干扰噪声问题是直升机气动声学领域的一个研究热点和难点。本文应用自由尾迹涡流理论和气动声学时域方法对旋翼桨-涡干扰气动噪声进行了理论分析研究，并在航空声学实验室和外场进行了模拟旋翼桨-涡干扰噪声的实验研究。主要工作包括： 作为前提和背景，本文首先简要介绍了直升机旋翼噪声的分类，指出了旋翼桨-涡干扰噪声研究的重点和难点。 在第二章，使用Beddoes预定尾迹模型，建立了一个用于旋翼桨-涡干扰特性机理分析的简化数学模型，分别对旋翼桨-涡干扰位置、桨-涡干扰距离和声辐射方向性等进行了计算和分析，得出了有意义的结果。 基于桨叶二阶升力线理论和旋翼自由尾迹模型，本文在第三章建立了一个适合于直升机旋翼尾迹结构及桨-涡干扰气动特性分析的方法和模型。 在第四章，基于上述旋翼自由尾迹方法，并使用Farassat 1A声学时域公式，建立了适合于直升机悬停和前飞时旋翼桨-涡干扰噪声计算的模型。 应用该模型，分别以UH-1模型旋翼、本文试验的模型旋翼以及Z-8直升机旋翼为算例，对不同飞行条件下的旋翼气动噪声进行了计算，验证了本文的计算方法。 在第六章，基于桨-涡靠近通过是非共面剪刀式布置旋翼流场的一个重要特征，提出了使用剪刀式布置旋翼来模拟旋翼桨-涡干扰噪声实验的新构想，并设计了用于噪声实验的模型。 本文第七章分别在“消声室”和外场进行了模型旋翼的桨-涡干扰噪声实验，对不同马赫数、不同桨距角以及不同旋翼布置情况下的不同测点进行了噪声测量，得出了一些新的结论。更多还原

【Abstract】 The research on the rotor blade-vortex interaction (BVI) noise is a very important aspect and a very challenging subject in the rotorcraft aeroacoustics field. In this thesis, both the analytical investigation, based upon the rotor free-wake vortex theory and the aeroacoustic methodology in time domain, and the experimental investigation, simulated in an aeroacoustic laboratory and at outdoors, on the BVI noise have been performed. The major contributions of the author’s research work are as follows:As the background of the work, the classification of helicopter rotor noise sources is introduced briefly, and the important and difficult aspects in the BVI noise research are pointed out.In Chapter 2, a simplified analytical model is presented for the analysis of the BVI mechanism, adopting the Beddoes’ prescribed wake model. By this model, the azimuthal location and miss-distance of the BVI and the radiation directivity of the BVI noise are calculated and discussed, and some conclusions are obtained.In Chapter 3, based upon the blade second-order lifting-line model and rotor free-wake model, an analytical method is developed for predicting the rotor wake structure and BVI airload.Based upon the rotor free-wake analysis and the Farassat Formulation 1A in time domain, an analytical model, which can be used to predict the BVI noise in hover and in forward flight, has been developed in Chapter 4.In Chapter 5, the UH-1 model rotor, the model rotor measured in the present work and the helicopter Z-8 rotor are taken as numerical examples, the calculations on rotor noise under different flight conditions are carried out for validation purposes.In Chapter 6, a new idea for simulating rotor BVI noise experiment is presented using a scissors rotor configuration with the vertical separation between a pair of rotors, based upon the fact that the important aerodynamic feature of this scissors rotor configuration is its close blade-vortex encounter. And the models and facilities designed for the BVI noise experiment are given.Finally, the experiments on the rotor BVI noise are conducted both in an aeroacoustic laboratory and at outdoors, and the noise characteristics at different locations are measured on different blade-tip Mach numbers, collective pitch angles and rotor configurations. Based on the experimental results, some new conclusions are presented.更多还原