基于波音算法的航空发动机风扇后传噪声级适航性评估

发布时间：2018-06-03 09:40

本文选题：波音算法 + 风扇后传噪声　；参考：《中国民航大学》2016年硕士论文

【摘要】：随着大涵道比发动机的广泛应用以及发动机设计的改进,发动机尾部喷流的速度逐步降低,这使得与喷流速度成八次方比的喷流噪声不断降低。和风扇噪声相比,尾部喷流噪声在发动机总噪声中所占重要性不断减少,并且就当代大涵道比涡轮风扇发动机而言,风扇噪声已经与尾部喷流噪声相差无几。而作为风扇噪声重要组成部分的风扇后传噪声,在起飞条件下几乎成为发动机的首要噪声源,其贡献量已与喷流噪声相当。因此,风扇后传噪声逐渐成为航空声学研究的主要问题之一,它对发动机噪声水平以及飞机噪声的降低具有重要的意义。本文基于波音风扇算法,给出风扇后传噪声的预测方法,借助于科技应用软件MATLAB开发一套对涡轮风扇发动机的风扇后传噪声进行预测并进行可视化分析的平台,并运用该平台对某型发动机风扇后传噪声级进行预测,研究风扇后传噪声的传播特性,结合该型发动机静态测试数据,验证该算法的适用性及准确性。在此基础之上,利用课题组得到的该型发动机在相同条件下的其他部件噪声值,分别得到了风扇后传噪声在起飞、降落及边线转速下对发动机的整机噪声的贡献量,进而评估该型发动机风扇后传噪声的适航性。本文的研究结果可对我国航空发动机的适航审定及风扇降噪技术的发展提供一定的参考。
[Abstract]:With the wide application of the large ducted ratio engine and the improvement of engine design, the engine tail jet speed is gradually reduced, which makes the jet noise to the eighth power ratio of jet speed decreasing. Compared with the fan noise, the tail jet noise accounts for less and less importance in the total engine noise, and the fan noise is no different from the tail jet noise in the case of the modern turbo fan engine with large ducts ratio. As an important part of fan noise, fan backpropagation noise almost becomes the primary noise source of engine under take-off condition, and its contribution is equal to that of jet noise. Therefore, fan backpropagation noise has gradually become one of the main problems in the study of aero-acoustics, which is of great significance to the level of engine noise and the reduction of aircraft noise. Based on the Boeing fan algorithm, the prediction method of fan backward noise is given in this paper. With the aid of scientific and technological application software MATLAB, a platform for predicting and visualizing fan backward noise of turbine fan engine is developed. The noise level of a certain engine fan is predicted by the platform, and the propagation characteristics of the fan noise are studied. The applicability and accuracy of the algorithm are verified by combining the static test data of the engine. On this basis, using the noise values of other parts of the engine under the same conditions, the contribution of fan noise to the whole engine at take-off, landing and side speed is obtained, respectively. Furthermore, the airworthiness of the rear noise of the engine fan is evaluated. The results of this paper can be used as a reference for the airworthiness validation and the development of fan noise reduction technology in China.
【学位授予单位】：中国民航大学
【学位级别】：硕士
【学位授予年份】：2016
【分类号】：V23

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