Rocket engine injector

Claim 1

IN A ROCKET ENGINE HAVING A COMBUSTION CHAMBER, AN IGNITEER, AND AN INJECTOR MANIFOLD HAVING A GENERALLY PLANAR ORIFICE PLATE FORMING AN END WALL OF SAID COMBUSTION CHAMBER, FUEL AND OXIDANT SUPPLYING MEANS COMPRISING: A FIRST CONDUIT FOR SUPPLYING PRESSURIZIED FUEL; A PASSAGE EXTENDING THROUGH SAID ORIFICE PLATE AND COMMUNICATING WITH SAID FIRST CONDUIT; SAID PASSAGE HAVING A GENERALLY CYLINDRICAL INNER SURFACE EXTENDING BETWEEN OPPOSED FACES OF SAID ORIFICE PLATE; A SECOND CONDUIT FOR SUPPLYING PRESSURIZED OXIDANT; A TUBE IN SAID PASSAGE EXTENDING THROUGH SAID ORIFICE PLATE AND COMMUNICATING WITH SAID SECOND CONDUIT; SAID TUBE HAVING A GENERALLY CYLINDRICAL OUTER SURFACE SPACED FROM SAID CYLINDRICAL INNER SURFACE THE DIAMETER OF SAID INNER SURFACE TO DEFINE A FUEL CONDUCTING PATH IN THE FORM OF A THIN WALLED ANNULUS, AND SAID TUBE TERMINATING SUBSTANTIALLY FLUSH WITH THE COMBUSTION CHAMBER FACE OF SAID ORIFICE PLATE WHEREBY SAID TUBE AND SAID PASSAGE COOPERATE TO CONDUCT THE OXIDANT AND FUEL SEPARATELY INTO SAID COMBUSTION CHAMBER AND TO INJECT THE FUEL THEREINTO IN THE FORM OF A THIN WALLED ANNULUS AND THE OXIDANT SUBSTANTIALLY COAXIALLY WITHIN SAID ANNULUS IN THE FORM OF AN EXPANDING STREAM CONTACTING AND MIXING WITH SAID FUEL.