Rocket engine

Claim 1

A ROCKET ENGINE COMPRISING A HOLLOW CASING, A STATIONARY PRE-COMBUSTION CHAMBER INTEGRAL WITH SAID CASING, A NOZZLE DEFINING A FINAL COMBUSTION CHAMBER BEING IN COMMUNICATION WITH SAID PRE-COMBUSTION CHAMBER AND HAVING A DISCHARGE OPENING FOR EXHAUST GASES, SAID NOZZLE BEING CONNECTED TO SAID CASING, COOLING DUCTS ADJACENT TO SAID NOZZLE AND EXTENDING SUBSTANTIALLY ALONG SAID NOZZLE, A COOLANT MANIFOLD IN SAID CASING ADJACENT TO SAID DISCHARGE OPENING OF SAID NOZZLE FOR ESTABLISHING COMMUNICATION BETWEEN SAID COOLING DUTS, A SHAFT ROTATABLY MOUNTED IN SAID CASING, A HOLLOW TURBINE ROTOR ON SAID SHAFT, SAID TURBINE ROTOR BEING ARRANGED BETWEEN SAID PRE-COMBUSTION CHAMBER, AND SAID FINAL COMBUSTION CHAMBER AND HAVING ROTOR BLADES, WHEREBY SAID TURBINE ROTOR IS DRIVEN BY THE COMBUSTION GASES FLOWING FROM THE PRE-COMBUSTION CHAMBER INTO THE FINAL COMBUSTION CHAMBER, SAID TURBINE ROTOR COMPRISING AT LEAST TWO CENTRIFUGAL PUMP SYSTEMS FOR PUMPING AT LEAST TWO FLUIDS INTO SAID PRE-COMBUSTION CHAMBER FOR BURNING SAID FLUIDS, MEANS FOR SUPPLYING SAID FLUIDS TO THE INLET OPENINGS OF THE PUMP SYSTEMS, CERTAIN OF SAID COOLING DUCTS BEING CONNECTED TO THE OUTLET OPENINGS OF AT LEAST ONE PUMP SYSTEM AT THE END OF SAID DUCTS OPPOSITE SAID MANIFOLD, THE REMAINING COOLING DUCTS BEING IN COMMUNICATION WITH THE PRE-COMBUSTION CHAMBER, WHEREBY THE FLUID PUMPED BY SAID SYSTEM IS FIRST FORCED THROUGH CERTAIN OF SAID COOLING DUCTS IN THE DIRECTION OF SAID DISCHARGE OPENING AND THEN BACK THROUGH CERTAIN OTHER OF SAID COOLING DUCTS TO SAID PRE-COMBUSTION CHAMBER FOR COOLING SAID NOZZLE.