Rocket engine having fuel driven propellant pumps

Claim 1

A ROCKET POWER PLANT INCLUDING A COMBUSTION CHAMBER, SAID COMBUSTION CHAMBER COMPRISING AN IMPERFORATE OUTER CASING AND AN INNER COAXIALLY DISPOSED PERFORATED MEMBER HAVING WALLS SPACED INWARDLY FROM SAID OUTER CASING AND FORMING AN ANNULAR CHAMBER THEREBETWEEN, A CONVERGENT-DIVERGENT EXHAUST NOZZLE RECEIVING GASES FROM SAID COMBUSTION CHAMBER, A SOURCE OF LIQUID OXIDIZER, A HEAT EXCHANGER ADJACENT SAID NOZZLE, A SOURCE OF LIQUID CRYOGENIC FUEL, MEANS FOR CONDUCTING FUEL FROM SAID SOURCE TO SAID HEAT EXCHANGER INCLUDING A FUEL PUMP, SAID FUEL BEING INCREASED IN TEMPERATURE IN SAID HEAT EXCHANGER, A TURBINE DRIVEN BY SAID FUEL AND LOCATED DOWNSTREAM OF SAID HEAT EXCHANGER, SAID FUEL PUMP INCLUDING A DRIVING MEMBER BEING DRIVEN BY SAID TURBINE, A CONDUIT INCLUDING A BYPASS VALVE FOR CONTROLLING THE AMOUNT OF FUEL BYPASSING SAID TURBINE, MEANS FOR CONDUCTING THE EXHAUST FLOW FROM SAID TURBINE AND THE FLOW BYPASSED BY SAID BYPASS VALVE TO SAID ANNULAR CHAMBER IN SAID COMBUSTION CHAMBER, AN OXIDIZER PUMP FOR DRAWING OXIDIZER FROM SAID OXIDIZER SOURCE, SAID OXIDIZER PUMP BEING DRIVEN BY SAID TURBINE, AND MEANS FOR CONDUCTING OXIDIZER IN ITS LIQUID STATE FROM SAID OXIDIZER PUMP TO THE INSIDE OF PERFORATED MEMBER OF SAID COMBUSTION CHAMBER TO MIX WITH SAID FUEL.