The oil film thickness between slider and shoe is a significant parameter and has a strong influence on the bearings performance. A CFD analysis has been carried out to find the effect of oil film thickness at the entrance of the slider using ANSYS workbench. Laminar viscous model with SIMPLE pressure-velocity coupling are used for the analysis. 2-D steady state, Navier-Stoke equations are discretized with finite volume approximations using structured grids. First the analysis has been carried out for the maximum load carrying capacity (i.e. m = 1.1889). For validation, CFD values are compared with the available analytical solution of Reynolds equation. CFD results showed good concord with the analytical values with a maximum error of 1%. After validation, the analysis has extended to four more m values such as 0.5, 1, 1.5 and 2. If bearing operate at below maximum load carrying capacity, the result shows that low load carrying capacity and high frictional losses. But for above, frictional forces reduces and blunt of the pressure profile at peak also decreases which will influence the action of extremely high load on a very small area of the shoe.

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This paper comprises the Computational Fluid Dynamic (CFD) analysis to investigate the flow behaviour of a high speed single stage transonic axial flow compressor. Steady state analyses were carried out at design and part speed conditions to obtain the overall performance map using commercial CFD software ANSYS FLUENT. Radial distribution of flow parameters were obtained at 90% of design speed for the choked flow and near stall flow conditions. The predicted data were validated against available experimental results. The end wall flow fields were studied with the help of velocity vector plots and Mach number contours at peak efficiency and near stall flow conditions at 60% and 100% design speeds. This study exhibited the nature of a transonic compressor, having strong interaction between the rotor passage shock and the tip leakage vortex at design speed, which generates a region of high blockage in the rotor blade passage. The influence of this interaction extends around 15% of the blade outer span at design speed and in the absence of blade passage shock at 60% design speed, the influence of tip leakage flow observed was around 8%. Revolutions per minute RPM