Gas turbine engine burner

Claim 1

IN A GAS TURBINE ENGINE, FUEL BURNING APPARATUS COMPRISING, IN COMBINATION, A GAS-OPERATED PRESSURE WAVE GENERATOR COMPRISING A HOUSING FORMING A GAS FLOW PASSAGEWAY HAVING INLET AND OUTLET OPENINGS, FIRST AND SECOND SPACED POSITIONS IN SAID PASSAGEWAY, RESTRICTOR MEANS AT SAID FIRST POSITION FOR REDUCING THE CROSS-SECTIONAL AREA OF SAID PASSAGEWAY, EXPANSION MEANS FOR INCREASING THE CROSS-SECTIONAL AREA OF SAID PASSAGEWAY BETWEEN SAID FIRST AND SECOND POSITIONS IN THE DIRECTION OF GAS FLOW THROUGH SAID PASSAGEWAY AND EXPANDING AND ACCELERATING A GAS TO SUPERSONIC VELOCITIES, RESONATOR MEANS POSITIONED ADJACENT SAID OUTLET OPENING, MEANS FOR SUBJECTING FLUID FUELS TO THE PRESSURE WAVES PRODUCED BY SAID GENERATOR AND ATOMIZING SAID FUELS, AIR COMPRESSION MEANS, AT LEAST ONE COMBUSTION CHAMBER PROVIDING A COMBUSTION AREA IN SAID ENGINE, MEANS FOR CONDUCTING COMPRESSED AIR FROM SAID AIR COMPRESSION MEANS TO SAID COMBUSTION CHAMBER AND TO THE INLET OF SAID GAS FLOW PASSAGEWAY TO OPERATE SAID PRESSURE WAVE GENERATOR, SAID PRESSURE WAVE GENERATOR BEING MOUNTED IN A WALL OF SAID COMBUSTION CHAMBER WITH ITS INLET COMMUNICATING WITH SAID CONDUCTING MEANS AND ITS OUTLET OPENING EXITING INTO SAID CHAMBER, SAID COMBUSTION CHAMBER HAVING AT LEAST OINE INLET OPENING COMMUNICATING WITH SAID CONDUCTING MEANS.