CENTRIFUGAL FUEL PUMP WITH STARTING STAGE

摘要

A novel centrifugal pumping system is disclosed for supplying fuel to aircraft gas turbines. The system has a common rotor (12) with two different sets of impeller blades on opposite sides. A regenerative liquid-ring starting pump (18) is located on one side of the rotor (12), and a centrifugal impeller (14) is located on the other. During engine start-up, the regenerative/liquid-ring pump (18) is capable of priming itself and supplies engine fluid and pressure. The starting pump (18) delivers fuel until the main pump (14) reaches a speed sufficient to provide adequate pressure for fuel delivery. At that time, the starting pump (18) is switched off, via a valving means.