Combustion chamber for liquid fuels

Claim 1

A ROCKET ENGINE FOR LIQUID FUELS COMPRISING A RELATIVELY AXIALLY ELONGATED COMBUSTION CHAMBER HAVING A CIRCULAR CROSS SECTION AND INCLUDING A SUBSTANTIALLY CYLINDRICAL MAIN SECTION; AN AXIALLY RELATIVELY SHORT SWIRL CHAMBER HAVING A CIRCULAR CROSS SECTION AND COAXIAL WITH SAID COMBUSTION CHAMBER AT THE ENTRANCE OF THE LATTER; SAID SWIRL CHAMBER INCLUDING CYLINDRICAL WALL MEANS AND AXIALLY SPACED END WALL MEANS HAVING PORTIONS EXTENDING SUBSTANTIALLY PERPENDICULAR TO SAID CYLINDRICAL ALL MEANS, ONE OF SAID END WALL MEANS HAVING A RELATIVELY SMALL DIAMETER CIRCULAR OPENING COMMUNICATION WITH SAID COMBUSTION CHAMBER; SAID COMBUSTION CHAMBER HAVING AN ENTRANCE TRANSITION SECTION BETWEEN SAID CIRCULAR OPENING AND SAID SUBSTANTIALLY CYLINDRICAL MAIN SECTION AND PROGRESSIVELY INCREASING IN DIAMETER FROM SAID CIRCULAR OPENING; FIRST AND SECOND NOZZLE MEANS OPENING THROUGH CYLINDRICAL WALL MEANS OF SAID WHIRL CHAMBER AND ARRANGED TO DIRECT A FLUID INTO THE LATTER TANGENTIALLY THEREOF AND WITH AN AXIAL VELOCITY COMPONENT; MEANS FOR DELIVERING A RELATIVELY HEAVY LIQUID COOLLANT AT A HIGH VELOCITY TO SAID FIRST NOZZLE MEANS TO FORM A SWIRLING LAYER OF LIQUID COOLANT ON THE INNER SURFACE OF SAID SWIRL CHAMBER AND SAID COMBUSTION CHAMBER AND MOVING AXIALLY OF SAID COMBUSTION CHAMBER; MEANS FOR DELIVERING A RELATIVELY LIGHTER LIQUID FUEL AT HIGH VELOCITY TO SAID SECOND NOZZLE MEANS TO FORM A SWIRLING LAYER OF LIQUID FUEL ON THE INNER SURFACE OF SAID LAYER OF COOLANT AND MOVING AXIALLY OF SAID COMBUSTION CHAMBER; AND MEANS FOR INTRODUCING A COMBUSTION SUPPORTING GAS INTO SAID COMBUSTION CHAMBER FOR ADMIXTURE WITH SAID LIQUID FUEL; SAID TRANSITION SECTION MAINTAINING CONTINUITY OF SAID LAYER OF LIQUID COOLANT THROUGHOUT THE LENGTH OF SAID INNER SURFACE OF SAID COMBUSTION CHAMBER TO MAINTAIN SAID LAYER OF LIQUID FUEL SEPARATED FROM THE SURFACE OF SAID COMBUSTION CHAMBER DURING COMBUSTION OF SAID LIQUID FUEL BY THE COMBUSTION SUPPORTING GAS.