Rocket propellant system

Claim 1

IN A PROPELLANT SYSTEM, FIRST AND SECOND SUPPLY DUCTS, ONE FOR EACH OF TWO PROPELLANTS, A PUMP IN THE FIRST OF SAID DUCTS FOR DELIVERING THE PROPELLANT IN SAID DUCT UNDER PRESSURE, A TURBINE FOR DRIVING SAID PUMP, AN EJECTOR HAVING A PRESSURE INLET, A SUCTION INLET AND AN OUTLET CHAMBER, SAID FIRST DUCT BEING CONNECTED TO SAID PRESSURE INLET FOR DELIVERING PROPELLANT UNDER THE DISCHARGE PRESSURE FROM SAID PUMP, A CONNECTION FROM SAID SECOND DUCT TO SAID SUCTION INLET, A COMBUSTION CHAMBER HAVING A GENERALLY SPHERICAL WALL AND PROPELLANT NOZZLES EXTENDING RADIALLY THROUGH THE WALL THEREOF, AN ARCUATE MANIFOLD EXTERNAL OF SAID COMBUSTION CHAMBER WALL HAVING FLUID CONNECTIONS TO SAID PROPELLANT NOZZLES, A FLUID CONNECTION FROM SAID EJECTOR OUTLET CHAMBER TO SAID MANIFOLD, A COMBUSTOR FOR DRIVING SAID TURBINE SUPPLIED WITH A COMBUSTIBLE MIXTURE FROM THE OUTLET CHAMBER OF THE EJECTOR, SAID COMBUSTOR HAVING TWO INLETS AND AN OUTLET, A CONDUIT CONNECTING THE COMBUSTOR OUTLET WITH THE TURBINE INLET, A SECOND CONDUIT CONNECTING ONE OF SAID INLETS WITH SAID EJECTOR OUTLET CHAMBER, AND A THIRD CONDUIT CONNECTING SAID COMBUSTOR WITH THE PROPELLANT DISCHARGE FROM SAID PUMP.