Design and test of an oxygen turbopump for a dual expander cycle rocket engine

A liquid oxygen (LOX) turbopump with an 860 degree R gaseous oxygen (GOX) turbine drive was designed for a 3750-lb thrust dual expander cycle rocket engine. This turbopump, which requires no interpropellant seals or system purges, features 156-hp, single-stage, full admission, impulse turbine; an axial flow inducer; a two-stage centrifugal pump with unshrouded impellers; long-life, LOX-lubricated, self-aligning, hydrostatic bearings; and a subcritical rotor design. It is constructed of Monel, a nickel-copper alloy, which has low ignition potential in oxygen.