摘要
为解决机载大过载、大偏心下动压轴承微间隙变尺度流动的分析问题,在推演局部剪应力计算滑移速度方程基础上,建立了剪应力方程、滑移修正雷诺方程、弹流润滑气膜厚度方程耦合迭代的界面非一致滑移流动分析方法。对比研究了非一致滑移模型与传统模型滑移流场的差异,以及周向非一致滑移速度演化规律,结果表明:非一致滑移模型可以获得与局部克努森数更相符的滑移速度分布,局部滑移对气膜压力的最大影响为10.6%,气膜压力分布数值与实验结果符合度好;随轴承数和偏心率增大,箔片侧与轴面侧依次出现滑移,滑移区域沿周向从最小气膜厚度处周向扩张且滑移速度不断增大,轴面侧滑移区域面积比箔片侧大,最高约为箔片侧的2倍。
To solve the problem of the analysis method for the variable scale flow in the micro clearance of the air⁃borne gas foil bearing under large overload and large eccentricity,a coupled iterative interface non-uniform slip flow analysis method of the shear stress equation,the slip correction Reynolds equation and the gas film thickness equa⁃tion based on elastohydrodynamic lubrication are established by deducing the local shear stress to calculate the slip ve⁃locity equation.The differences of the slip flow field between the non-uniform slip model and the traditional model and the evolution law of the circumferential non-uniform slip velocity are compared.The results show that the slip velocity distribution obtained by the non-uniform slip model is more consistent with the local Knudsen number.The maximum effect of the local slip on the gas film pressure is 10.6%,and the gas film pressure distribution is in good agreement with the experimental results.With the increase of the bearing number and eccentricity,slip sequentially occurs on the foil side and the shaft side.The slip regions expand from the minimum gas film thickness to both sides along the cir⁃cumferential direction with continuously increasing slip velocity.The area of the slip region on the shaft side is up to twice as large as that on the foil side.
作者
张镜洋
陈哲
吕元伟
孙义建
张靖周
陈卫东
罗欣洋
ZHANG Jingyang;CHEN Zhe;LYU Yuanwei;SUN Yijian;ZHANG Jingzhou;CHEN Weidong;LUO Xinyang(College of Astronautics,Nanjing University of Aeronautics and Astronautics,Nanjing 211106,China;College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;State Key Laboratory of Mechanics and Control of Mechanical Structures,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration,Nanjing Engineering Institute of Aircraft Systems,Nanjing 211106,China)
出处
《航空学报》
EI
CAS
CSCD
北大核心
2023年第11期88-102,共15页
Acta Aeronautica et Astronautica Sinica
基金
航空科学基金(201928052008)
南京航空航天大学科研与实践创新基金(xcxjh20211505)。
关键词
动压轴承
非一致滑移
极限剪应力
滑移速度
气膜压力
gas foil bearing
non-uniform slip flow
ultimate shear stress
slip velocity
gas film pressure
