【摘要】：噪聲是現(xiàn)代大型民用客機(jī)設(shè)計(jì)的關(guān)鍵指標(biāo)之一,民航飛機(jī)噪聲的主要來(lái)源包括機(jī)體噪聲和發(fā)動(dòng)機(jī)噪聲,隨著現(xiàn)代大涵道比發(fā)動(dòng)機(jī)飛機(jī)的發(fā)展,發(fā)動(dòng)機(jī)的噪聲水平已經(jīng)有了明顯的降低,但仍然是大型民用飛機(jī)的主要噪聲源之一。隨著世界航空對(duì)航空發(fā)動(dòng)機(jī)的噪聲要求的日益嚴(yán)格,對(duì)于大涵道比渦扇發(fā)動(dòng)機(jī)的噪聲控制變的尤為重要。因此,針對(duì)航空渦扇發(fā)動(dòng)機(jī),本文開展了噪聲源分析和噴流噪聲抑制技術(shù)的研究。在噪聲源分析方面,分析了發(fā)動(dòng)機(jī)不同部位的噪聲源(包括葉輪機(jī)機(jī)噪聲、燃燒噪聲和噴流噪聲),首先對(duì)發(fā)動(dòng)機(jī)葉輪機(jī)噪聲進(jìn)行分析,了解了風(fēng)扇噪聲的產(chǎn)生機(jī)理以及產(chǎn)生的噪聲類型,分清風(fēng)扇噪聲中的主要次要噪聲;其次對(duì)發(fā)動(dòng)機(jī)燃燒室噪聲進(jìn)行分析,由于航空發(fā)動(dòng)機(jī)燃燒室噪聲的復(fù)雜性,本文主要分析了燃燒室噪聲產(chǎn)生的機(jī)理以及燃燒室噪聲的影響因素;最后對(duì)發(fā)動(dòng)機(jī)的噴流噪聲的機(jī)理及特性進(jìn)行了介紹。在噪聲抑制方面,針對(duì)上述噪聲產(chǎn)生的機(jī)理及特性,分析了幾種噪聲抑制技術(shù),首先,本文在現(xiàn)有文獻(xiàn)的參考下,分析了四種葉輪機(jī)噪聲的抑制技術(shù),對(duì)噪聲抑制方面均有良好的效果,并且對(duì)其中增加轉(zhuǎn)靜子距離噪聲抑制技術(shù)通過(guò)Ansys軟件進(jìn)行建摸,通過(guò)速度云圖和聲功率云圖得到,增加5mm的轉(zhuǎn)靜子距離,噪聲可以降低大約4.2dB;其次由于航空發(fā)動(dòng)機(jī)燃燒室環(huán)境條件苛刻以及國(guó)內(nèi)外學(xué)者對(duì)燃燒室噪聲抑制技術(shù)方面研究不多,本文針對(duì)發(fā)動(dòng)機(jī)燃燒室噪聲影響因素進(jìn)行了分析,采用吸聲技術(shù)是燃燒室目前最有效的噪聲抑制方法;最后,在噴流噪聲抑制技術(shù)方面,本文選取了鋸齒形噴管降噪技術(shù),通過(guò)Ansys軟件對(duì)一個(gè)發(fā)動(dòng)機(jī)模型進(jìn)行模擬計(jì)算,得出其噴流的溫度、速度和噪聲分布,并通過(guò)圖像分析和對(duì)比,得出了鋸齒型尾噴管大概能夠降低噴流噪聲4-5dB,證明了鋸齒形噴管噴流噪聲抑制技術(shù)的可行性,在此基礎(chǔ)上,本文研究了鋸齒形噴管齒數(shù)對(duì)噴流噪聲抑制效果的影響,得出了優(yōu)化齒輪數(shù)的結(jié)果。
[Abstract]:Noise is one of the key indexes of modern civil airliner design. The main sources of civil aircraft noise include airframe noise and engine noise. The engine noise level has been obviously reduced, but it is still one of the main noise sources of large civil aircraft. With the increasingly stringent noise requirements of aero-engines in the world, it is particularly important to control the noise of turbofan engines with large ducts. Therefore, the noise source analysis and jet noise suppression technology are studied for the aero-turbofan engine. In the aspect of noise source analysis, the noise sources of different parts of engine (including impeller noise, combustion noise and jet noise) are analyzed. Firstly, the noise of engine impeller is analyzed. The generation mechanism and types of fan noise are understood, and the main secondary noise in fan noise is distinguished. Secondly, the noise of engine combustor is analyzed. Because of the complexity of combustor noise, the mechanism of combustor noise and the influence factors of combustor noise are analyzed in this paper. Finally, the mechanism and characteristics of engine jet noise are introduced. In the aspect of noise suppression, according to the mechanism and characteristics of the above noise, several noise suppression techniques are analyzed. Firstly, four kinds of impeller noise suppression techniques are analyzed under the reference of existing literatures. It has a good effect on noise suppression, and the noise suppression technology of increasing transposon distance is built by Ansys software, and obtained by velocity cloud diagram and acoustic power cloud diagram, which can increase the transposon distance of 5mm. Noise can be reduced by about 4.2 dB; Secondly, due to the harsh environmental conditions of the aero-engine combustion chamber and the lack of research on the noise suppression technology of the combustion chamber, this paper analyzes the influence factors of the engine combustion chamber noise. Sound absorption technology is the most effective noise suppression method for combustion chamber at present. Finally, in the aspect of noise suppression technology of jet flow, this paper selects the noise-reducing technology of sawtooth nozzle, simulates and calculates an engine model by Ansys software, and obtains the temperature, velocity and noise distribution of jet flow. Through image analysis and comparison, it is concluded that the jagged tail nozzle can reduce the noise of jet from 4 to 5 dB, which proves the feasibility of the noise suppression technology of the jagged nozzle. In this paper, the influence of the number of jagged nozzle teeth on the effect of jet noise suppression is studied, and the results of optimizing the gear number are obtained.
【學(xué)位授予單位】：中國(guó)民航大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2015
【分類號(hào)】：V231.92

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