Patent ID: 8613189
Filing Date: 2013-12-24
Classification: F02K

Abstract:
1. A rocket engine comprising: a main combustion chamber and a throat and an expansion nozzle for the rocket engine connected together to produce thrust from burning of a fuel with an oxidizer; a turbine rotatably connected to a fuel impeller and an oxidizer impeller; the fuel impeller and the oxidizer impeller each having a high pressure outlet and a low pressure outlet; a fuel low pressure pump having an outlet connected to an inlet of the fuel impeller; an oxidizer low pressure pump having an outlet connected to an inlet of the oxidizer impeller; the high pressure outlets for the fuel impeller and the oxidizer impeller being connected to the main combustion chamber; an inlet of the fuel low pressure pump connected to the low pressure outlet of the fuel impeller; and, an inlet of the oxidizer low pressure pump connected to the low pressure outlet of the oxidizer impeller.