Jet engine cooling system

Claim 1

A FUEL AND COOLING SYSTEM FOR A TURBOMACHINE OF THE AXIAL FLOW TYPE HAVING AN OUTER ANNULAR LONGITUDINALLY EXTENDING ENGINE CASING AND INNER LONGITUDINALLY EXTENDING ANNULAR WALL MEANS COOPERATING THEREWITH TO TOGETHER DEFINE AXIALLY ALIGNED COMPRESSOR, MAIN COMBUSTION, TURBINE, AND AFTERBURNER COMBUSTION SECTIONS THEREBETWEEN FOR THE FLOW OF GAS THERETHROUGH, A PLURALITY OF FUEL INJECTORS ADAPTED TO CONTAIN FUEL SECURED TO SAID CASING AND WALL MEANS AND EXTENDING INTO EACH OF THE MAIN AND AFTERBURNER COMBUSTION SECTIONS FOR THE INJECTION OF FUEL THEREIN, SEPARATE SOURCES OF CRYOGENIC FUEL EACH HAVING A HIGH SPECIFIC HEAT CAPACITY FOR SAID MAIN AND AFTERBURNER SECTIONS, MEANS CONNECTING SAID SOURCES AND SAID MAIN AND AFTERBURNER COMBUSTION SECTION FUEL INJECTORS, PORTIONS OF SAID ENGINE CASING AND SAID WALL MEANS HAVING HOLLOW INTERIORS ADAPTED TO CONTAIN FUEL UNDER PRESSURE, AND MEANS CONNECTING SAID SOURCES OF FUEL AND THE HOLLOW INTERIORS OF SAID CASING AND WALL MEANS FOR THE FLOW OF CRYOGENIC FUEL UNDER PRESSURE THERETHROUGH TO COOL THE ENCLOSURE DEFINING SURFACES OF SAID MAIN AND AFTERBURNER COMBUSTION SECTIONS, ANNULAR MEANS ENCLOSING THE INTERIOR OF SAID COMPRESSOR SECTION, AND MEANS CONNECTING SAID AFTERBURNER SECTION SOURCE OF FUEL TO SAID LAST MENTIONED MEANS FOR THE FLOW OF CRYOGENIC FUEL THERETHROUGH TO COOL SAID INTERIOR OF SAID COMPRESSOR SECTION BY THE ABSORPTION OF HEAT BY SAID FUEL.