Pre-burner for low temperature turbine applications

#1. Field of the Invention

#This invention relates generally to turbopump fed rocket engines, and, more particularly, to a fuel rich pre-burner that operates at a very low mixture ratio to drive a turbine in a hydrogen peroxide based rocket engine.

#2. Discussion of the Related Art

#FIG. 1 is a block diagram of a prior art propellant supply system for a turbopump fed rocket engine; and

#FIG. 2 is a block diagram of a propellant supply system for a turbopump fed rocket engine in accordance with the present invention.

#FIG. 1 illustrates a propellant supply system 10 for a conventional turbopump fed rocket engine 12. The propellant supply system 10 generally includes a fuel pump 14, an oxidizer pump 16, a gas generator 18 and a turbine 20. The engine 12 is further defined to include an injector 22, and a main combustion chamber 26.

#Liquid rocket fuel is typically stored at low pressures in a fuel tank (not shown). The fuel pump 14 provides pressurized fuel from the fuel tank to the injector 22 of the engine 12. Prior to reaching the engine, the pressurized fuel may pass through at least one orifice 32 and a main fuel throttle valve 34.

#Likewise, liquid oxidizer is stored at low pressures in an oxidizer tank (not shown). The oxidizer pump 16 provides pressurized liquid oxidizer to gas generator 18. Prior to reaching the gas generator 18, the liquid oxidizer may pass through at least one orifice 42, a main oxidizer throttle valve 44 and through a cooling jacket 46 that is formed along the outer surface of the combustion chamber. In this way, the liquid oxidizer may be used to cool the high temperatures associated with the main combustion chamber 26 of the engine 12.