本文選題：旋流分離器　切入點：數(shù)值模擬　出處：《彈箭與制導(dǎo)學(xué)報》2016年02期

【摘要】：旋流分離器產(chǎn)生的內(nèi)外雙層旋流具有穩(wěn)定火焰以及冷卻壁面的潛能,為此文中應(yīng)用雷諾應(yīng)力模型(RSM)對某種結(jié)構(gòu)的旋流冷壁燃燒室的流動特性進(jìn)行了數(shù)值仿真。結(jié)果表明:旋流冷壁燃燒室能夠?qū)崿F(xiàn)內(nèi)外雙層旋流流動,具有較好的壁面冷卻效果。冷熱態(tài)條件下,總壓損失系數(shù)為0.9%和1%,表現(xiàn)出低阻特性;內(nèi)外旋流分界面平均約占半徑的70%。燃燒區(qū)域分界隨燃料噴入速度的增大而增大,燃料噴射速度為12 m/s時,燃燒區(qū)域最大,平均約占半徑的56%。
[Abstract]:The internal and external double-layer swirl produced by the cyclone separator has the potential to stabilize the flame and cool the wall. In this paper, the Reynolds stress model (RSM) is used to simulate the flow characteristics of the swirl wall combustor with a certain structure. The results show that the swirl cold wall combustor can realize the internal and external two-layer swirl flow. Under the cold and hot conditions, the total pressure loss coefficient is 0.9% and 1%, showing a low resistance characteristic, and the internal and external swirl separation interface accounts for about 70 of the radius on the average. The combustion zone boundary increases with the increase of fuel injection velocity. When the fuel injection velocity is 12 m / s, the combustion region is the largest, accounting for about 56% of the radius on average.
【作者單位】： 南昌航空大學(xué)飛行器工程學(xué)院;上海電力學(xué)院能源與機(jī)械工程學(xué)院;
【基金】：國家自然科學(xué)基金(51066006;51266013) 航空科學(xué)基金(2013ZB56002;2013ZB56004)資助
【分類號】：V231.2
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本文編號：1683150