摘要
静压气体轴承供气孔出口后的压力陡降一直限制着静压气体轴承的使用;且随着气膜间隙的增大,气膜内甚至会出现负压,而传统的雷诺方程无法计算出流场内的压力陡降。运用FLUENT软件对单孔环面节流静压气体圆盘止推轴承的流场进行了仿真计算;基于计算结果,分析了不同气膜间隙下气膜入口区和压力回升区的流场特性;运用边界层知识解释了不同气膜间隙下的压力回升;以流场中马赫数的连续变化为依据说明气膜内正激波是不存在的;研究了流场中气体粘度的变化情况;通过仿真压力分布与实验压力分布的对比,验证了仿真模型和仿真方法的正确性。
The pressure depression after the outlet of the gas supply hole of aerostatic bearing limits its use, and the negative pressure will even occur with the increase of gas film clearance, which can not be calculated effectively with the traditional Reynolds equation. The Fluent software was used to calculate the flow of externally pressurized circular thrust gas bearings with one supply hole. The characteristics of the flow at the film entrance and the pressure recovery regions under different gas film clearances were analyzed based on the calculation results. The pressure recovery was explained with the help of the boundary layer knowledge. That the change of the Mach number is continuous shows there is no shock wave in the flow. The change of viscosity was studied. The calculation pressure distributions show good agreement with the experimental ones, which proves that the calculation method and model are correct.
出处
《机床与液压》
北大核心
2008年第10期109-112,共4页
Machine Tool & Hydraulics
基金
国家自然基金资助项目(50335010)
关键词
FLUENT
压力
马赫数
边界层
正激波
FLUENT
Pressure
Mach number
Boundary layer
Normal shock wave
