Burner for hot fuel

Claim 1

IN AN AIRCRAFT, THE COMBINATION OF A WING TRIANGULAR IN CROSS-SECTION, WITH A LOWER SURFACE SLOPING REARWARDLY AND UPWARDLY TO THE AIRCRAFT AND HAVING AN EDGE PROJECTING DOWNWARDS TO DEFINE A COMBUSTION SPACE BELOW THE LOWER SURFACE TO THE REAR OF THE EDGE, AT LEAST ONE BURNER COMPRISING A NOZZLE AND ONE PIPE CONNECTED TO SAID NOZZLE AND SUPPLIED WITH HOT LIQUID FUEL UNDER PRESSURE, SAID NOZZLE HAVING A DIVERGENT PART OF SUBSTANTIAL LENGTH WITH A DIVERGENCE OF A PREDETERMINED VALUE OPENING BELOW THE WING IN SAID COMBUSTION SPACE, THE SAID HOT LIQUID FUEL HAVING A PRESSURE ABOVE A LEVEL WHICH PERMITS THE FUEL TO BE VAPORIZED IN THE SAID PIPE AND BELOW A LEVEL WHICH PERMITS AT LEAST A PART OF THE SAME TO BE VAPORIZED BY EXPANSION IN THE SAID DIVERGENT PART OF PREDETERMINED DIVERGENCE WHILE FLOWING THERETHROUGH, WHEREBY THE HOT LIQUID FUEL IS VAPORIZED IN SAID DIVERGENT PART AT LEAST PARTIALLY BY EXPANSION WITH FORMATION OF A JET WHICH MIXES WITH A FLOW OF INCIDENT AIR TO PENETRATE INTO THE COMBUSTION SPACE, AND IGNITION MEANS IN THE COMBUSTION SPACE, WHEREBY COMBUSTION TAKES PLACE IN THE COMBUSTION SPACE TO INCREASE THE PRESSURE ON SAID LOWER SURFACE OF THE WING, THEREBY INCREASING THE LIFT AND THRUST OF THE AIRCRAFT.