Patent ID: 8864441

Claim:
A turbopump for a rocket engine comprising: a main rotor shaft having a forward end and an aft end; a liquid oxygen impeller rotatably connected to the forward end of the main rotor shaft; a turbine rotatably connected to the aft end of the main rotor shaft; a multiple stage liquid hydrogen impeller rotatably connected to the main rotor shaft between the liquid oxygen impeller and the turbine; a forward side hydrostatic bearing located between the liquid oxygen impeller and the multiple stage liquid hydrogen impeller to rotatably support the forward side of the main rotor shaft; an aft side hydrostatic bearing located between the multiple stage liquid hydrogen impeller and the turbine to rotatably support the aft side of the main rotor shaft; and, both of the liquid oxygen impeller and the turbine are formed as an overhung rotor shaft.