Patent ID: 6655127
Filing Date: 2003-12-02
Classification: F02K

Abstract:
A propellant supply system for a turbopump fed rocket engine, comprising:a rocket fuel source; a source of monopropellant oxidizer that decomposes at high temperatures to the engine; a first gas generator adapted to receive rocket fuel from the rocket fuel source and monopropellant oxidizer from the source of monopropellant oxidizer, the first gas generator operable to convert the rocket fuel and the monopropellant oxidizer into a fuel rich gas and supply the fuel rich gas to the engine; a turbine interposed between the first gas generator and the engine, such that the fuel rich gas passes through the turbine; a second gas generator adapted to receive a substantial portion of the oxidizer from the source of monopropellant oxidizer and operable to decompose the oxidizer into an oxidizing gas; and an injector adapted to receive the oxidizing gas from the second gas generator and the fuel rich gas from the first gas generator and operable to inject the gases into a main combustion chamber associated with the rocket engine.