Abstract
In this study, numerical investigation of coolant flow across the angular contact ball bearing in a rocket turbopump was
performed to evaluate pressure loss of the bearing. The results show that the pressure loss tendencies against the bearing
revolution speed were significantly different between the flow directions. It was mainly caused by the flow separation
behind the ball and centrifugal force effect of swirl flow made by bearing revolution. Furthermore, we get a simplified pressure
loss model of the bearing and it can approximately estimate the difference of the pressure losses between the flow
directions.
