GB716456A - - Google Patents

Abstract

716,456. Jet propulsion plant; gas turbine plant. SOC. NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. May 26, 1952 [June 20, 1951], No. 13327/52. Class 110(2) [Also in Group XII] A ducted-fan turbo-jet engine comprises at least one pulse jet unit which is disposed in the duct by passing the gas turbine unit and is supplied with at least part of the flowing through said duct. The ducted-fan turbo-jet 'engine, Fig. 1, comprises a single- or multi-stage turbine 8 driving high- and low-pressure compressors 1, 2 respectively and a series of airjacketed. pulsatory combustion chambers 10 which are interconnected by a tube 30 for ignition purposes and terminate in nozzles 13. The air circulating between the combustion chambers is discharged through an annular nozzle 16. The combustion chambers are disposed parallel to the longitudinal axis of the engine or are arranged obliquely thereto along the generatrices of a hyperboloid if they are rectilinear or helically arranged if their axes are curved. The combustion gases entering the turbine are mixed with compressed air taken from the delivery side of the high-pressure compressor. The whole of the air fed to the bypass duct 6 may be passed through the combustion chambers ]0. In a modification, (Fig. not shown), a series of convergent-divergent nozzles 17 are disposed in alignment with and are axially spaced from the members 13 whereby the orifice 16 is dispensed with. In a further modification, Fig. 5, the nozzles 17 are mounted on an annular member 20 for axial adjustment along bearing surfaces 21, 22. When the combustion chambers 10 are operating the nozzles 17 engage the members 13 whereby the compressed air circulating between the combustion chambers 10 is discharged through annular orifices 26, 27 instead of the nozzles 17. The lowpressure compressor may incorporate a device for regulating its intake section.