Abstract: In rocket engines power is usually obtained by burning fuel and oxidizer. The two are mixed, pressurized, and directed to a combustion chamber by means of turbopumps. Hydrostatic bearings have been proposed for use in these turbopumps because during flight, hydrostatic lubrication can reduce roller bearing wear. But during startup, acceleration and shutdown high pressure fluids are not available to provide fluid lubrication for hydrostatic bearings. During these periods a second bearing is required to carry the load, rendering hybrid bearings desirable for rocket engine turbopumps. Herein a hybrid hydrostatic-rolling element bearing has been provided. The rolling element bearing is locked on a stationary housing through which a rotating journal passes. A transient supporting ring is keyed to the journal. It is adapted to lock on the rolling element bearing so that the rolling element bearing supports radial loads during startup, initial acceleration, deceleration and shut down, and to release at high speeds.