波箔型动压气体轴承间隙非一致滑移流场  

Flow field in clearance of dynamic pressure gas foil bearing with partical slip

作　　者：张镜洋[1] 孙义建 吕元伟 张靖周[2] 陈卫东[3] 刘晨晨 ZHANG Jingyang;SUN Yijian;LYU Yuanwei;ZHANG Jingzhou;CHEN Weidong;LIU Chenchen(College of Astronautics,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,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;Jincheng Nanjing Engineering Institute of Aircraft System,Aviation Industry Corporation of China,Limited,Nanjing 210016,China)

机构地区：[1]南京航空航天大学航天学院,南京210016 [2]南京航空航天大学能源与动力学院,南京210016 [3]南京航空航天大学机械结构力学及控制国家重点实验室,南京210016 [4]中国航空工业集团有限公司金城南京机电液压工程研究中心,南京210016

出　　处：《航空动力学报》2024年第8期470-482,共13页Journal of Aerospace Power

基　　金：航空基金(201928052008);江苏省自然科学基金(BK20210303)。

摘　　要：为揭示界面滑移对动压气体轴承间隙流场的影响机理,以波箔型动压气体径向轴承为研究对象,建立周向非一致滑移修正雷诺方程并采用超松弛迭代法进行求解,分析了转速、偏心率、间隙高度和箔片变形等因素变化下滑移对轴承间隙内流场的影响。结果表明:随着转速的增大或间隙高度的减小,流固界面由无滑移状态转变为静子侧滑移状态,并最终达到两侧均滑移状态,转子侧从压力上升区、静子侧从压力下降区向两侧滑移区域面积和速度逐渐增大;而偏心率的增大仅会导致滑移速度增大,而滑移区域面积几乎不变;箔片变形使滑移速度场呈现阶梯状分布。非一致滑移对最高气膜压力最大影响可达17%。速度梯度和压力场显著变化诱导界面剪应力和极限剪应力复杂演化而产生上述规律。In order to reveal the effects of the slip state on the flow field evolution under different working conditions of the dynamic pressure gas foil bearing,taking the dynamic pressure gas foil bearing as the research object,the modified Reynolds equation for circumferential partial slip was established and solved by the over-relaxation iteration method.The influence of slip on the flow field in the bearing clearance was analyzed under the change of rotating speed,eccentricity,clearance height and foil deformation.The results showed that with the increase of rotating speed or the decrease of clearance height,the fluid-solid interface changed from no slip state to the stator side slip state,and finally reached the slip state at both sides.The area and velocity of the slip region on the rotor side from the pressure rise region and the stator side from the pressure drop region to both sides gradually increased.However,as the eccentricity increased,the slip velocity on both sides increased gradually,and the slip area was almost unchanged.The deformation of the foil caused the slip velocity field to exhibit a stepped distribution.Partial slip had a maximum effect of 17% on the highest film pressure.The reason for the above law is that the changes of velocity gradient and pressure field make the interface shear stress and ultimate shear stress change complexly.

关 键 词：动压气体轴承 微尺度 箔片 界面滑移 流场 

分 类 号：V232[航空宇航科学与技术—航空宇航推进理论与工程] TH123[机械工程—机械设计及理论]