摘要
针对带管式减涡器的径向内流共转盘腔结构,为了研究导流管出口角度对盘腔内流场结构、压力损失的影响规律,数值模拟了不同转速和出口角度下的盘腔内部流场,获得了不同工况下的总压损失分布柱状图。结果表明:在相同转速下,直管式与60°弯管式减涡器降低压力损失的效果相近,90°弯管式降低压力损失的效果最好,30°弯管式降低压力损失的效果最差;在所有转速下,压力损失随出口角度的变化分布存在1个最高点;增加转速,压力损失总体减小。
In order to study the influence of the outlet angle of the honeycomb duct on the disc cavities flow field structure and pressure loss in the co-rotating disc cavities for the radial inflow with tubed vortex reducer,the flow field in the disc cavities under different rotational speed and outlet angle was simulated numerical,and the histogram of the total pressure loss distribution under different working conditions was obtained.The results show that the effect of reducing pressure loss between straight pipe and 60°curved tube is similar,90°bend pipe is the best,and 30°bend pipe is the worst at the same speed.At all speeds,there is a highest point in the distribution of pressure loss with the outlet angle.With the increase of speed,the overall pressure loss is reduced.
作者
郝媛慧
王锁芳
夏子龙
HAO Yuan-hui;WANG Suo-fang;XIA Zi-long(Aero-engine Thermal Environment and Structure Key Laboratory of Ministry of Industry and Information Technology,Ncanjing University of Aeronautics and Astronautics,Nanjing 210016,China)
出处
《航空发动机》
北大核心
2019年第4期38-41,共4页
Aeroengine
关键词
减涡管
出口角度
去旋系统
数值模拟
压力损失
航空发动机
tubed vortex reducer
outlet angel
de-swirl system
numerical simulation
pressure loss
aeroengine
