Apparatus for generating combustion gases under pressure

摘要

960,297. Gas turbine plant; jet propulsion plant; generating combustion products under pressure. W. MANS. Aug. 27, 1962, No. 32860/62. Headings FIG, F1J and F1L. An apparatus for generating combustion gases under pressure comprises an air suction device fed by part of the gases produced by the apparatus and constructed to accelerate the air to sonic or supersonic velocity and at least one combustion chamber arranged around a compression device comprising consecutive stagnation chambers, each of which is connected via Venturi nozzles with the next stagnation chamber and in which the first stagnation chamber in the direction of air flow is connected to the outlet of the air suction device and the last stagnation chamber terminates in the combustion chamber such that under the influence of heat transfer from the combustion chamber the air in the stagnation chamber is compressed. A combustion apparatus, Fig. 1, for an aircraft comprises a jet pump 1 fed by gas from a combustion chamber 2 which escapes with supersonic velocity through a pipe 4 and induces atmospheric air through pipe 3 into a mixing tube 6, the gas-air ratio being controlled by a movable cone 5. The pressure of the mixture is increased in stagnation chambers 7 connected by staggered Venturi nozzles 71, 711 &c of successively decreasing cross-section, each nozzle accelerating the gas flow to supersonic velocity. Compression is increased by heat transfer from the combustion chamber 2, or additional combustion gas may be supplied to the nozzles 71 to reduce boundary layer losses, or fuel may be injected directly into the stagnation chambers 7. The gas-air mixture flows from the chambers 7 into the combustion chamber 2 containing a fuel burner 10 and after combustion part of the gas produced flows to a chamber 17, in which additional fuel is supplied, and to a jet propulsion nozzle 11, controlled by a movable cone 16. At high flight speeds surplus air is discharged from an annular chamber 12 through a propulsion nozzle controlled by a cone 13. Combustion of additional fuel may occur in this nozzle. Starting is effected by closing annular valve 15 and supplying air or gas through valve 14. In a modification for a stationary engine, Fig. 2, the jet pump 1 is replaced by a compressor (not shown) driven by a turbine 18, and a separate power turbine 19 and a second combustion chamber 17 are included.