【摘要】：隨著科技的發(fā)展,航空技術(shù)發(fā)展的越發(fā)嫻熟,大飛機的發(fā)展越來越重要,發(fā)動機作為飛機的動力系統(tǒng)必不可少,因而飛機的輔助動力系統(tǒng)也日益受到人們的重視。輔助動力裝置的核心部件是燃燒室,燃燒室的性能直接關(guān)系到整個輔助動力系統(tǒng)的性能,本文主要針對輔助動力裝置回流燃燒室的設(shè)計與性能進(jìn)行研究分析。本文對帶頭部整流板回流燃燒室模型進(jìn)行設(shè)計改進(jìn),并針對火焰筒頭部整流板進(jìn)行設(shè)計改進(jìn)出分段形式整流板、連續(xù)形式整流板和分段連續(xù)形式整流板三種模型。利用Fluent軟件對燃燒室總體性能進(jìn)行數(shù)值計算分析,并在此方法基礎(chǔ)上利用經(jīng)過試驗驗證的半經(jīng)驗公式方法對燃燒室進(jìn)行點火、熄火以及污染物排放的性能研究。本文首先基于非預(yù)混燃燒模型對帶頭部整流板回流燃燒室進(jìn)行性能研究。針對設(shè)計出的不同火焰筒頭部整流板的回流燃燒室進(jìn)行數(shù)值計算,通過對比分析燃燒室內(nèi)流場、溫度場、出口溫度分布以及燃燒室的總體性能,得出火焰筒頭部回流區(qū)形成的主要原因是內(nèi)外環(huán)主燃孔斜向?qū)_和火焰筒頭部整流板整流的共同作用,其中外環(huán)主燃孔的沖擊和整流板的整流占主要作用,內(nèi)環(huán)主燃孔起輔助作用。同時由于火焰筒頭部整流板的導(dǎo)向作用,可以使氣流周向流動,提高燃燒室周向的聯(lián)焰能力。燃燒室火焰筒頭部整流板的改進(jìn)對燃燒效率影響不大,但對出口溫度分布OTDF改善較為明顯。接著針對燃燒室點火、熄火以及污染物排放的性能研究,本文采用經(jīng)過試驗驗證的半經(jīng)驗公式與數(shù)值計算方法對燃燒室的點火、熄火以及污染物排放的性能研究,最終得出點熄火以及污染物排放的半經(jīng)驗公式可以對燃燒室的設(shè)計與性能分析進(jìn)行預(yù)估,為燃燒室的設(shè)計與試驗提供參考。最后針對帶頭部旋流器回流燃燒室模型的性能研究,通過不同湍流模型對該燃燒室的性能進(jìn)行對比分析,最終得出大渦模擬方法計算出的燃燒室內(nèi)部流場可以更好地反映燃燒室內(nèi)部的流動情況。大渦模擬燃燒室總壓恢復(fù)系數(shù)為0.9753,燃燒室燃燒效率為0.9926,燃燒室出口溫度分布為0.32;雷諾時均方法模擬燃燒室總壓恢復(fù)系數(shù)為0.9727,燃燒室燃燒效率為0.9907,燃燒室出口溫度分布為0.37。通過對比分析,大渦模擬方法在計算燃燒室總體性能上要優(yōu)于雷諾平均方法。同時通過大渦模擬方法針對該燃燒室進(jìn)行點火、熄火以及污染物排放的性能研究。
[Abstract]:With the development of science and technology, the development of aeronautical technology is more and more skillful, the development of large aircraft is more and more important, the engine is indispensable as the aircraft power system, so the auxiliary power system of aircraft has been paid more and more attention. The core component of the auxiliary power device is the combustion chamber. The performance of the combustion chamber is directly related to the performance of the whole auxiliary power system. In this paper, the design and performance of the auxiliary power unit reflux combustor are studied and analyzed. In this paper, the model of reflux combustor with head rectifier plate is designed and improved, and three models of segmented rectifier plate, continuous rectifier board and segmented continuous rectifier board are designed and improved. The overall performance of the combustor was numerically calculated and analyzed by Fluent software. Based on this method, the performance of ignition, flameout and pollutant emission of the combustor was studied by using the semi-empirical formula method verified by the experiment. In this paper, the performance of reflux combustor with head rectifier plate is studied based on non-premixed combustion model. The flow field, temperature field, outlet temperature distribution and the overall performance of the combustor were compared and analyzed by numerical calculation for the designed reflux combustor with rectifier plate at the head of the different flame tube, and the flow field, temperature field, outlet temperature distribution and the overall performance of the combustor were analyzed. It is concluded that the main reason for the formation of the reflux zone at the head of the flame tube is the oblique hedging of the main combustion hole in the inner and outer ring and the common action of the rectifier plate at the head of the flame tube. The main combustion hole in the inner ring plays an auxiliary role. At the same time, because of the guiding action of the rectifier plate at the head of the flame tube, the flow of air can be circumferential and the flaming ability of the combustion chamber can be improved. The improvement of the head rectifier plate of the combustion chamber flame tube has little effect on the combustion efficiency, but it can obviously improve the outlet temperature distribution of OTDF. Then, aiming at the performance research of ignition, flameout and pollutant emission of combustion chamber, this paper uses the semi-empirical formula and numerical calculation method verified by experiment to study the performance of ignition, flameout and pollutant emission of combustion chamber. Finally, the semi-empirical formula of ignition extinguishment and pollutant emission can be used to predict the design and performance analysis of the combustion chamber, which provides a reference for the design and test of the combustion chamber. Finally, the performance of the reflux combustor with head hydrocyclone is studied, and the performance of the combustor is compared and analyzed by different turbulence models. Finally, it is concluded that the flow field in the combustor calculated by the large eddy simulation method can better reflect the flow situation in the combustor. The total pressure recovery coefficient of the combustor is 0.9753, the combustion efficiency of the combustor is 0.9926, and the temperature distribution at the outlet of the combustor is 0.32. The Reynolds time average method simulates the total pressure recovery coefficient of the combustor is 0.9727, the combustion efficiency of the combustor is 0.9907, and the temperature distribution at the outlet of the combustor is 0.37. By comparison and analysis, the large eddy simulation method is superior to the Reynolds average method in calculating the overall performance of the combustor. At the same time, the characteristics of ignition, flameout and pollutant emission of the combustor were studied by means of large eddy simulation.
【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2016
【分類號】：V228

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本文編號：2415171