Method and apparatus for providing improved combustion in jet engines

Claim 1

A JET ENGINE WHICH COMPRISES, IN COMBINATION, A COMBUSTION CHAMBER HAVING AN AIR INLET IN ONE END THEREOF AND AN EXHAUST GAS OUTLET IN THE OTHER END THEREOF, A FLOW SHIELD AXIALLY POSITIONED WITHIN SAID COMBUSTION CHAMBER, SAID FLOW SHIELD HAVING A GENERALLY FRUSTO-CONICAL SHAPE AND BEING OPEN AT THE LARGE END THEREOF TO FORM A FLOW SHIELD EXHAUST GAS OUTLET AND BEING OPEN AT THE SMALL END TO FORM A FLOW SHIELD AIR INLET, SAID FLOW SHIELD HAVING A PLURALITY OF PERFORATIONS DISPOSED AROUND THE SURFACE OF SAID SHIELD, SAID FLOW SHIELD EXHAUST GAS OUTLET BEING ATTACHED TO THE INNER WALL OF SAID COMBUSTION CHAMBER AT A POINT GENERALLY INTERMEDIATE THE AIR INLET AND EXHAUST GAS OUTLET OF SAID COMBUSTION CHAMBER, A FIRST FUEL NOZZLE AXIALLY-POSITIONED WITHIN SAID COMBUSTION CHAMBER ADJACENT TO SAID COMBUSTION CHAMBER AIR INLET AND OSITIONED SO AS TO DIRECT FUEL TOWARDS SAID EXHAUST GAS OUTLET AND SO AS TO BE WITHIN SAID AIR INLET TO THE COMBUSTION CHAMBER AND TO EXTEND PARTIALLY THROUG THE FLOW SHIELD AIR INLET, A SECOIND FUEL NOZZLE AXIALLY-POSITIONED WITHIN SAID FLOW SHIELD, SAID SECOND FUEL NOZZLE BEING POSITIONED SO AS TO DIRECT FUEL TOWARDS SAID FLOW SHIELD AIR INLET AND POSITIONED GENERALLY INTERMEDIATE THE AIR INLET AND EXHAUST GAS OUTLET OF SAID FLOW SHIELD, AN ELONGATED, TUBULAR FUEL CRACKING MEANS HAVING AN INLET AND AN OUTLET POSITIONED WITHIN SAID COM-