Cooling techniques for high temperature engines and other components

Claim 1

AN INTEGRALLY COOLED ROCKET ENGINE NOZZLE CAPABLE OF OPERATION IN THE PRESENCE OF A ROCKET EXHAUST STREAM HAVING TEMPERATURES SUBSTANTIALLY EXCEEDING THE MELTING POINTS OF REFRACTORY METALS COMPRISING A FUSIBLE COOLANT CONFIGURED TO PERMIT EXPANSION AND HAVING A VAPOR PRESSURE CHARACTERISTIC FOR FACILITATING LIQUID FILM FORMATION AT ROCKET OPERATING TEMPERATURES, A NOZZLE LINER BOUNDING SAID EXHAUST STREAM AND DIMENSIONED TO FUNCTION AS A HEAT EXCHANGER FOR FORMING A FUSED FILM OF COOLANT ON THE EXHAUST STREAM SIDE OF SAID LINER, SAID LINER INCLUDING A STACK OF ANNULAR RINGS, A CASING ENCLOSING SAID LINER WITH A STORAGE SPACE THEREBETWEEN FOR STORING SAID FUZIBLE COOLANT, SAID STORAGE SPACE THEREBETWEEN FOR STORING SAID FUZIBLE LINER IN SUCH A MANNER AS TO CONVEY HEAT OF FUSION TO SAID COOLANT VIA SAID LINER, AND PASSAGEWAYS IN SAID STACK INTERCONNECTING SAID STORAGE SPACE AND THE EXHAUST STREAM SIDE OF SAID LINER AND DIMENSIONED AND LOCATED FOR CONTINUOUSLY TRANSPORTING SAID FUSED COOLANT TO SAID EXHAUST STREAM SIDE OF SAID LINER TO PROVIDE EVAPORATIVE FILM COOLING THEREOF.