摘要
为降低航空发动机径向预旋系统的流阻,增加温降,研究供气孔内的流动特性,建立径向预旋系统三维模型,在不同预旋角和旋转雷诺数条件下,采用数值方法研究不同供气孔角度下预旋系统的特性。结果表明:随着供气孔角度的增加,孔内的旋涡逐渐减小,孔内流通性得到改善;系统温降系数增加,在高旋转雷诺数下增幅较大,最大可提高19.3%;供气孔的流量系数有显著提高,最大可提高64.9%,降低了系统的流阻,从而预旋喷嘴出口流量系数及系统无量纲质量流量均有所提高。
In order to reduce the flow resistance and increase the temperature drop of the aero-engine radial pre-swirl system,the flow characteristics inside the supply hole was studied and a three-dimensional model of the radial pre-swirl system was established.The numerical simulation was conducted to study the features of different pre-swirl systems at different pre-swirl nozzle angles and in rotational Reynolds numbers.The results show that as the angle of the supply hole increases,the vortex inside the hole gradually decreases,which improves the flowability of the supply hole.Temperature drop coefficient increases with the supply hole increases,and the increase of temperature drop coefficient is larger in high rotational Reynolds number,up to 19.3%.After the angle of supply hole is increased,the discharge coefficient is significantly improved,up to 64.9%,which reduces the flow resistance of the system,thus the discharge coefficient of the pre-swirl nozzle outlet and the system dimensionless mass flow rate being improved.
作者
柴金孟
王锁芳
沈文杰
CHAI Jinmeng;WANG Suofang;SHEN Wenjie(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)
出处
《机械制造与自动化》
2024年第2期96-100,共5页
Machine Building & Automation
基金
国家科技重大专项资助项目(2017-Ⅲ-0011-0037)。
关键词
航空发动机
径向预旋
供气孔角度
温降
流阻
流量系数
aero-engine
radial pre-swirl
supply hole angle
temperature drop
flow resistance
discharge coefficient
