摘要
目前收缩扩张型混合管结构参数对于圆排波瓣引射器影响的相关研究少,为此首先进行了带有不同结构参数收缩扩张型混合管的圆排波瓣喷管和圆形喷管引射器缩比模型引射性能的实验研究。结果表明,当混合管喉道直径和长度较小且主流质量流量较低时,圆形喷管的引射性能高于波瓣喷管,但随着质量流量增加情况发生逆转;当喉道直径和长度较大时,在实验质量流量范围内和满足主流附壁条件下,波瓣喷管引射性能均高于圆形喷管;随着主流质量流量增大,引射质量流量比存在一个极大值,并且随着喉道直径和长度增大,该极大值也逐渐增大,在所研究模型中极大值的最大增长率为58.5%。接着,本文建立了经过实验数据验证的数值计算模型,误差不大于4.5%。仿真结果表明:随着喉道直径和长度增大,总压恢复系数逐渐增大,喉道尺寸的增大对于流动损失具有改善作用。
At present,few studies are devoted to the effect of structural parameters of converging diverging mixing ducts on circularly lobed nozzle ejector.Therefore,several converging diverging mixing ducts with different geometric parameters were designed firstly,and an experimental study on the pumping performance of circularly lobed nozzle and circular nozzle exhaust-ejector scaled-down models was developed.The results showed that when the throat diameter and length of the mixing duct were smaller,the pumping ratio of the circular nozzle was higher than that of the lobed nozzle within lower main flow range,but the situation was reversed as the mass flow increased.When the throat diameter and length of the mixing duct were larger,under the condition of wall-attached main flow,the pumping ratio of the lobed nozzle was higher than that of the circular nozzle within the experimental mass flow range.With the increase of the mass flow,a maximum value of the pumping ratios appeared.Furthermore,as the throat diameter and length increased,the maximum value also gradually increased,and the maximum growth rate was 58.5%.Secondly,a numerical calculation model was established and verified by experimental data,with the error not more than 4.5%.The simulation results showed that the total pressure recovery coefficient increased as the throat diameter and length of the mixing duct increased.Therefore,larger mixing ducts throat diameter and length had an improved effect on flow loss.
作者
肖长庚
刘友宏
张寒
淳杰
黄宇
XIAO Changgeng;LIU Youhong;ZHANG Han;CHUN Jie;HUANG Yu(School of Energy and Power Engineering,Beihang University,Beijing 102206,China)
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2024年第6期178-185,共8页
Journal of Aerospace Power
基金
国家重大科技专项(J2019-Ⅲ-0009-0053,2017-Ⅲ-0003-0027)。
关键词
收缩扩张型混合管
圆排波瓣喷管
圆形喷管
引射器实验与仿真
引射性能
converging diverging mixing ducts
circularly lobed nozzle
circular nozzle
experiment and simulation of ejector
pumping performance
