發(fā)布時間：2018-07-02 10:14

  本文選題：超聲速燃燒 + 小支板��； 參考：《航空動力學報》2016年01期

【摘要】：為分析小支板前/后噴射在超聲速燃燒室中的流動特性,運用數(shù)值模擬方法研究了小支板對乙烯噴射冷流場的作用規(guī)律.對比分析了有無小支板、不同噴射位置、不同噴射角對流場的影響.研究發(fā)現(xiàn)小支板增強摻混的機制主要在于在小支板后端形成了流向渦與低壓區(qū);在一定范圍內,噴孔距離支板尾部越遠越處于湍流強度較大的流向渦中,更有利于摻混增強,但同時也距離小支板后緣的低壓區(qū)更遠,這將導致總壓損失變大;綜合考慮,小支板與噴孔的距離為2.2d,噴射角為90°時燃料穿透深度、混合效率較好,總壓損失也相對較小.
[Abstract]:In order to analyze the flow characteristics of small branched front / rear jet in supersonic combustor, the effect of small branch plate on the cold flow field of ethylene is studied by numerical simulation method. The effect of small branch plate, different injection position and different jet angle on the flow field is compared and analyzed. At the back end of the plate, the flow direction vortex and low pressure region are formed. In a certain range, the farther the tail of the branch is in the flow direction, the farther the flow direction is in the flow vortex, which is more conducive to mixing and strengthening, but it is also far away from the low pressure area of the rear edge of the small branch plate, which will cause the loss of the total pressure, and the distance between the small branch plate and the jet hole is 2.2d. When the angle is 90 degrees, the penetration depth of fuel is higher, the mixing efficiency is better, and the total pressure loss is relatively small.
【作者單位】： 空軍工程大學防空反導學院;
【基金】：航空科學基金項目(20130196004)
【分類號】：TK401

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