Combustion chamber for ram-jets or rocket power units employing a cooling film of liquid fuel

Claim 1

COMBUSTION CHAMBER WITH NOZZLE FOR LIQUID-FUEL RAM-JETS AND ROCKETS, WHICH COMPRISES A UNITARY METAL CASING COMPRISING IN SUCCESSION IN THE DIRECTION OF FLOW OF THE COMBUSTION GASES A FRUSTOCONICAL CONVERGENT WALL HAVING A MAJOR BASE AND A MINOR BASE AND DEFINING THE COMBUSTION CHAMBER PROPER, AND A DIVERGENT WALL, AN ANNULAR GRAPHITE MEMBER HAVING AN INNER SURFACE AND A FRUSTOCONICAL EXTERNAL SURFACE COMPRISING A MAJOR BASE AND A MINOR BASE, SAID GRAPHITE MEMBER BEING FITTED ENTIRELY WITHIN SAID CONVERGENT WALL BETWEEN THE MINOR BASE OF SAID CONVERGENT WALL AND AN INTERMEDIATE SECTION BETWEEN ITS MINOR BASE AND ITS MAJOR BASE, THE INNER SURFACE OF SAID GRAPHITE MEMBER FORMING A CONVERGENTDIVERGENT ELEMENT OF WHICH THE DIVERGENT SECTION MERGES INTO THE DIVERGENT WALL OF SAID METAL CASING, A REFRACTORY BINDER INTERPOSED BETWEEN THE EXTERNAL FRUSTOCONICAL SURFACE OF SAID ANNULAR GRAPHITE MEMBER AND SAID CONVERGENT WALL, AN ANNULAR SHOULDER PROVIDED IN THE ZONE WHERE THE INNER SURFACES OF SAID CONVERGENT AND DIVERGENT WALLS OF SAID CASING MERGE INTO EACH OTHER, AND ENGAGED BY THE MINOR BASE OF SAID ANNULAR GRAPHITE MEMBER, AND A RING MEMBER SECURED TO THE INNER SURFACE OF SAID CONVERGENT WALL AND ENGAGING THE MAJOR BASE OF SAID ANNULAR GRAPHITE MEMBER TO HOLD SAID GRAPHITE MEMBER AGAINST SAID ANNULAR SHOULDER.