本文選題：加力燃燒室 + 振蕩燃燒　； 參考：《南京航空航天大學(xué)》2016年碩士論文

【摘要】：加力燃燒室內(nèi)容易出現(xiàn)自激的振蕩燃燒,振蕩燃燒出現(xiàn)時會影響加力燃燒室的正常工作,嚴(yán)重時還可能導(dǎo)致結(jié)構(gòu)的損壞。在全尺寸加力燃燒室上按照實際運行狀態(tài)來深入研究振蕩燃燒過程及內(nèi)在機(jī)制是不現(xiàn)實的,為此本文根據(jù)相似原理簡化了加力燃燒室,在模型加力燃燒室上研究振蕩燃燒的影響因素和抑制技術(shù),具體的工作包括:首先,通過對原型加力燃燒室進(jìn)行三維穩(wěn)態(tài)數(shù)值模擬研究,得到了加力燃燒室內(nèi)的平均流場參數(shù),依據(jù)相似原理對加力燃燒室進(jìn)行了簡化,設(shè)計了模型加力燃燒室,為后續(xù)的研究奠定基礎(chǔ)。其次,在模型加力燃燒室上開展了振蕩燃燒機(jī)制的研究,通過數(shù)值模擬和實驗的方法,研究了進(jìn)氣壓力、當(dāng)量比、供油位置、穩(wěn)定器結(jié)構(gòu)等參數(shù)的變化對振蕩燃燒的頻率、振幅以及熱聲耦合相位的影響。研究發(fā)現(xiàn):當(dāng)量比對振蕩燃燒有很大的影響,隨著當(dāng)量比的增加,振蕩燃燒強(qiáng)度先增加后減小,在富油的時候受到抑制,振蕩燃燒的頻率剛開始隨著當(dāng)量比的增加有略微的提升,但是在當(dāng)量比很大的時候,振蕩的模式發(fā)生變化,振蕩燃燒的頻率發(fā)生巨大變化;在一定當(dāng)量比下,振蕩燃燒的幅值隨著氣流速度的增加而增大到最大值后,隨速度增加而下降;供油位置變化會改變摻混段的距離,摻混段距離和進(jìn)氣速度共同影響混合物到達(dá)火焰前沿的流動時間,從而使放熱脈動和壓力脈動的相位關(guān)系發(fā)生變化,使振蕩燃燒受到激勵或是抑制。最后討論了加力燃燒室振蕩燃燒的抑制技術(shù),在實驗中出現(xiàn)的大多是低頻的縱向振蕩模式,而基于亥姆霍茲共振吸聲原理的多孔板,對低頻振蕩的抑制效果有限。采用周向和徑向組合的穩(wěn)定器進(jìn)行實驗發(fā)現(xiàn),傾斜的徑向穩(wěn)定器可以使得火焰在空間上形成多層分布,從而使一個穩(wěn)定器就能達(dá)到類似于多排穩(wěn)定器的效果,可以使得加力燃燒室內(nèi)的放熱脈動頻率多樣化,破壞熱聲耦合,對抑制振蕩燃燒有較為明顯的抑制效果。
[Abstract]:Self-excited oscillatory combustion is easy to occur in the afterburner, which will affect the normal operation of the afterburner and may lead to structural damage when the oscillation combustion occurs. It is not realistic to study the oscillatory combustion process and its inherent mechanism in the full-scale afterburner according to the actual operating state. Therefore, the afterburner is simplified according to the similarity principle in this paper. The influence factors and suppression techniques of oscillatory combustion in the model afterburner are studied. The specific work includes: firstly, through the three-dimensional steady numerical simulation of the prototype afterburner, the average flow field parameters in the afterburner are obtained. According to the similarity principle, the afterburner is simplified and the model afterburner is designed, which lays a foundation for further research. Secondly, the oscillatory combustion mechanism is studied in the model afterburner. By means of numerical simulation and experiment, the frequency of oscillatory combustion is studied by the change of inlet pressure, equivalent ratio, fuel supply position, stabilizer structure and so on. The effect of amplitude and thermoacoustic coupling phase. It is found that the equivalent ratio has a great influence on the oscillatory combustion. With the increase of the equivalent ratio, the intensity of the oscillatory combustion increases first and then decreases, and is restrained at the time of oil enrichment. The frequency of oscillatory combustion has just started to increase slightly with the increase of equivalent ratio, but when the ratio of equivalent is very large, the mode of oscillation changes and the frequency of oscillating combustion changes greatly. The amplitude of the oscillatory combustion increases to the maximum with the increase of the flow velocity, and decreases with the increase of the velocity, and the distance of the mixing section changes with the change of the fuel supply position. The mixing distance and the inlet velocity affect the flow time of the mixture to the front of the flame, which changes the phase relationship between the exothermic pulsation and the pressure pulsation, and the oscillatory combustion is stimulated or suppressed. In the end, the suppression technology of oscillatory combustion in the afterburner is discussed. The low frequency longitudinal oscillation mode appears mostly in the experiment, but the perforated plate based on Helmholtz resonance absorption principle has limited effect on the suppression of low frequency oscillation. Experimental results show that the inclined radial stabilizer can make the flame form a multi-layer distribution in space, so that a stabilizer can achieve a similar effect as a multi-row stabilizer. The frequency of exothermic pulsation in the afterburner can be diversified, the thermoacoustic coupling can be destroyed, and the vibration combustion can be inhibited obviously.
【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】：V231.2

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