摘要
在常压、双涵进气条件下 ,通过对几种波瓣混合器与圆形收敛喷管组合的出口流场测试 ,研究不同外、内涵速度比情况下 ,波瓣混合器的混合气动性能 (压力和温度均匀度、压力损失系数等 )变化规律 ,为对比起见 ,还对环形混合器组合进行了试验。试验表明 :在本试验范围内 ,随着速度比的增加 ,压力均匀度曲线呈“凸”形 ,冷态试验时 ,峰值在速度比 1 .0处 ,热态试验时 ,峰值在 0 .68附近 (冷、热态峰值的速度都与温度比的平方根成正比 )。压力损失系数曲线呈“凹”形 ,冷态试验时 ,谷值速度比小于 1 .0 ,热态试验时 ,谷值在速度比更小处 ,温度均匀度曲线则随着速度比的增加呈下降趋势 ,在速度比 0 .2～ 0 .7之间 ,温度均匀度随速度比的变化基本呈线性关系 ,而在速度比大于 0 .7以后 ,则下降趋势变平缓。
The exit flow fields of a circular convergent nozzle with three lobed mixers were measured at atmospheric pressure and two flow conditions,to study the impact of velocity ratio on the mixing performance.An annular mixer was also tested for comparison.The results show that the curves of pressure uniformity with the velocity ratio have 'convex' shapes.Their peak values appear at velocity ratio 1 under cold conditions,and at velocity ratio 0 68 under hot conditions.The two velocity ratio values are directly proportional to the square root of temperature ratio under cold and hot conditions.Contrary,the curves of pressure loss coefficient with the velocity ratio have 'concave' shapes.The velocity ratio values at the valley points of the curves are dependent on the configuration of the mixers,and are both less than those at the peak points of the pressure uniformity curves under cold and hot conditions.The temperature uniformity decreases with the increase of velocity ratio in the test range.The correlation is linear when the velocity ratioslie 0 2～0 7,and then it changes smoothly as the velocity ratio is greater than 0 7.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2002年第1期53-57,共5页
Journal of Aerospace Power
