Patent ID: 8177489
Filing Date: 2012-05-15
Classification: F04D

Abstract:
1. A process for operating a turbopump of a rocket engine, the turbopump pressurizing a cryogenic liquid for burning in the rocket engine, the turbopump including and a low pressure inducer mechanically uncoupled from a high pressure centrifugal pump, the process comprising the steps of: driving the high pressure centrifugal pump to produce a high pressure cryogenic liquid; bleeding off a portion of the high pressure cryogenic liquid to drive the inducer and produce a low pressure cryogenic liquid; passing the low pressure cryogenic liquid into an inlet of the high pressure centrifugal pump; discharging the portion of the high pressure cryogenic liquid used to drive the inducer into the inlet of the high pressure centrifugal pump downstream of the inducer; and the step of driving the inducer includes passing the portion of the high pressure cryogenic liquid through a row of turbine blades integral to the inducer blades such that rotation of the turbine blades causes rotation of the inducer blades.