Abstract: The complete gas field including supply hole and clearance is built up, and a two-dimensional laminar flow model and local turbulent flow model are used to calculate the parameters of gas thrust bearing in different clearances. The calculation results basically agree with the experimental results. The numerical results illustrate the shock/boundary layer interaction and the shock train phenomenon. The analysis of velocity and pressure show that, with increase of both gas supply pressure and clearance thickness, the gas flows more quickly at the entrance of supply hole, which produces local back-flow, there is supersonic flow behind the throat, and pressure rise slowly with the dissipation effect at wall and oblique shock wave, the gas lowers down to subsonic velocity, gradually shows non-viscosity.

Key words: Boundary layer, Gas bearing, Inertia force, Shock wave