發(fā)布時間：2018-06-03 09:40

  本文選題：波音算法 + 風(fēng)扇后傳噪聲��； 參考：《中國民航大學(xué)》2016年碩士論文

【摘要】：隨著大涵道比發(fā)動機(jī)的廣泛應(yīng)用以及發(fā)動機(jī)設(shè)計(jì)的改進(jìn),發(fā)動機(jī)尾部噴流的速度逐步降低,這使得與噴流速度成八次方比的噴流噪聲不斷降低。和風(fēng)扇噪聲相比,尾部噴流噪聲在發(fā)動機(jī)總噪聲中所占重要性不斷減少,并且就當(dāng)代大涵道比渦輪風(fēng)扇發(fā)動機(jī)而言,風(fēng)扇噪聲已經(jīng)與尾部噴流噪聲相差無幾。而作為風(fēng)扇噪聲重要組成部分的風(fēng)扇后傳噪聲,在起飛條件下幾乎成為發(fā)動機(jī)的首要噪聲源,其貢獻(xiàn)量已與噴流噪聲相當(dāng)。因此,風(fēng)扇后傳噪聲逐漸成為航空聲學(xué)研究的主要問題之一,它對發(fā)動機(jī)噪聲水平以及飛機(jī)噪聲的降低具有重要的意義。本文基于波音風(fēng)扇算法,給出風(fēng)扇后傳噪聲的預(yù)測方法,借助于科技應(yīng)用軟件MATLAB開發(fā)一套對渦輪風(fēng)扇發(fā)動機(jī)的風(fēng)扇后傳噪聲進(jìn)行預(yù)測并進(jìn)行可視化分析的平臺,并運(yùn)用該平臺對某型發(fā)動機(jī)風(fēng)扇后傳噪聲級進(jìn)行預(yù)測,研究風(fēng)扇后傳噪聲的傳播特性,結(jié)合該型發(fā)動機(jī)靜態(tài)測試數(shù)據(jù),驗(yàn)證該算法的適用性及準(zhǔn)確性。在此基礎(chǔ)之上,利用課題組得到的該型發(fā)動機(jī)在相同條件下的其他部件噪聲值,分別得到了風(fēng)扇后傳噪聲在起飛、降落及邊線轉(zhuǎn)速下對發(fā)動機(jī)的整機(jī)噪聲的貢獻(xiàn)量,進(jìn)而評估該型發(fā)動機(jī)風(fēng)扇后傳噪聲的適航性。本文的研究結(jié)果可對我國航空發(fā)動機(jī)的適航審定及風(fēng)扇降噪技術(shù)的發(fā)展提供一定的參考。
[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.
【學(xué)位授予單位】：中國民航大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2016
【分類號】：V23

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本文編號：1972323