Abstract: A fuel injector system for injecting fuel into a turbomachine combustion chamber, the system comprising first and second fuel injectors wherein the first injector (22) is positioned in the center of the injector system (20) so as to inject a first fuel spray (42), and wherein the second injector (28) surrounds the first injector in such a manner as to inject a second fuel spray (48) of generally annular shape around the first fuel spray. The injector system further comprises an air admission duct (22) with outlet orifices (62) opening out between the first and second injectors so as to create a separator air film (f1) between the respective combustion zones of the first and second fuel sprays.

Abstract: A fuel injector system for injecting fuel into a turbomachine combustion chamber, the system comprising first and second fuel injectors wherein the first injector (22) is positioned in the center of the injector system (20) so as to inject a first fuel spray (42), and wherein the second injector (28) surrounds the first injector in such a manner as to inject a second fuel spray (48) of generally annular shape around the first fuel spray. The injector system further comprises an air admission duct (22) with outlet orifices (62) opening out between the first and second injectors so as to create a separator air film (f1) between the respective combustion zones of the first and second fuel sprays.

Abstract: An injection system for a turbomachine combustion chamber, the system comprising a fuel injection nozzle for vaporizing fuel in the combustion chamber and a mixer/deflector assembly coaxial with the injection nozzle and serving to mix fuel and oxidizer and to diffuse the mixture in the combustion chamber, said mixer/deflector assembly comprising a primary swirler and a secondary swirler disposed at a determined distance apart from each other in the axial direction and separated by a Venturi device disposed coaxially with the injection nozzle, the primary swirler being fixed securely to the injection nozzle and being spaced apart therefrom by a constant radial distance which is determined in such a manner that the fuel vaporized by the injection nozzle can under no circumstances impact on the primary swirler. The Venturi device preferably has an inside surface that presents an upstream portion with a slope discontinuity P.

Abstract: An offset annular combustion chamber for an airplane engine gas turbine, the chamber comprising a pilot head having a plurality of nozzle systems distributed on a pilot head chamber end wall interconnecting an inner longitudinally-extending side wall of the chamber to a pilot head outer longitudinally-extending side wall, and a take-off head that is radially and axially offset from the pilot head and comprising a plurality of nozzle systems distributed on a take-off head chamber end wall interconnecting the pilot head outer longitudinally-extending side wall and a take-off head outer longitudinally-extending side wall, the pilot head having at least N substantially identical nozzle systems with overall permeability PA adapted to lighting and to speeds close to idling, and the take-off head having at least 2N substantially identical nozzle systems of overall permeability PB, where PB is greater than or equal to PA, the permeability PA lying in the range 10% to 40% of the total air flow rate penetrating into th

Abstract: An injection system for a turbomachine combustion chamber, the system comprising a fuel injection nozzle for vaporizing fuel in the combustion chamber and a mixer/deflector assembly coaxial with the injection nozzle and serving to mix fuel and oxidizer and to diffuse the mixture in the combustion chamber, said mixer/deflector assembly comprising a primary swirler and a secondary swirler disposed at a determined distance apart from each other in the axial direction and separated by a Venturi device disposed coaxially with the injection nozzle, the primary swirler being fixed securely to the injection nozzle and being spaced apart therefrom by a constant radial distance which is determined in such a manner that the fuel vaporized by the injection nozzle can under no circumstances impact on the primary swirler. The Venturi device preferably has an inside surface that presents an upstream portion with a slope discontinuity P.