Jet engine noise suppressor and booster

Claim 1

THE COMBINATION WITH AN AIRCRAFT-SUPPORTED JET ENGINE HAVING AN EXHAUST NOZZLE THROUGH WHICH A CONTINUOUS STREAM OF HEATED GASES IS DISCHARGED AT A FIRST SUB-SONIC VELOCITY, FIRST PRESSURE AND FIRST TEMPERATURE, A GENERALLY CYLINDRICAL SHEATH THAT ENVELOPES SAID NOZZLE, AND A TRANSVERSELY POSITIONED FIRST RING THAT RIGIDLY CONNECTS THE REAR END PORTIONS OF SAID SHEATH AND NOZZLE OF A COMBINATION NOISE SUPPRESSOR AND BOOSTER, INCLUDING: (A) A SECOND RIGID RING DISPOSED IN ABUTTING CONTACT WITH A REAR SURFACE OF SAID FIRST RING; (B) FIRST MEANS FOR REMOVABLY SUPPORTING SAID SECOND RING FROM SAID FIRST RING; (C) A PLURALITY OF CIRCUMFERENTIALLY SPACED BRACKETS EXTENDING REARWARDLY FROM SAID SECOND RING; (D) A FIRST TUBULAR SHELL DEFINING A FORWARDLY DISPOSED CONVERGENT SECTION, A THROAT, AND A REARWARDLY DISPOSED DIVERGENT SECTION, WITH THE ENTRANCE TO SAID CONVERGENT SECTION AND THE EXIT FROM SAID DIVERGENT SECTION BEING OF GREATER CROSS-SECTIONAL AREA THAN THAT OF THE REAR END OF SAID NOZZLE; (E) A PLURALITY OF RIGID RIBS WHICH EXTEND REARWARDLY FROM SAID BRACKETS THAT HOLD SAID FIRST SHELL IN COAXIAL ALIGNMENT WITH SAID NOZZLE, WITH THE REAR PORTION OF SAID NOZZLE PROJECTING INTO THE FORWARD PORTION OF SAID CONVERGENT SECTION, AND THE INTERIOR SURFACE OF SAID CONVERGENT SECTION AND THE EXTERIOR SURFACE OF SAID NOZZLE COOPERATIVELY DEFINING AN ANNULUS-SHAPED SPACE; (F) A SECOND GENERALLY CYLINDRICAL SHELL SUPPORTED FROM THE OUTER PORTIONS OF SAID RIBS WHICH ENVELOPES SAID RIBS AND SAID FIRST SHELL, WITH THE MAXIMUM TRANSVERSE CROSS SECTION OF SAID SECOND SHELL BEING NO GREATER THAN THE MAXIMUM TRANSVERSE CROSS SECTION OF SAID SHEATH TO MINIMIZE THE AIR RESISTANCE AS SAID ENGINE MOVES THROUGH THE AMBIENT ATMOSPHERE; AND