Fuel injecting system for e.g. axial/bent combustion chamber of turbojet engine, has fuel injector positioned at center of system to inject fuel cloud, and another fuel injector surrounding former injector to inject annular fuel cloud

摘要

#CMT# #/CMT# The system (20) has a fuel injector (22) positioned at the center of the injecting system in order to inject a fuel cloud (42). Another fuel injector (28) surrounds the fuel injector (22) in order to inject an annular fuel cloud (48) around the fuel cloud (42). Air inlet passages (24, 30) e.g. air spins, respectively associated to the two injectors for forming two air/fuel mixtures, respectively. #CMT#USE : #/CMT# System for injecting fuel in a combustion chamber e.g. axial or bent combustion chamber, of a turbomachine (all claimed) e.g. turbojet engine, of an aircraft. Can also be used for a terrestrial turbomachine. #CMT#ADVANTAGE : #/CMT# The two fuel injectors permits to adapt the richness of the air/fuel mixtures at an operating mode of a turbojet engine and to limit the emission of gas pollutants e.g. nitrogen oxides. The arrangement of the fuel injectors enables the system to be adapted on the existing combusting chamber design with a single orifice arranged in the base of the chamber. #CMT#DESCRIPTION OF DRAWINGS : #/CMT# The drawing shows an axial sectional view of a fuel injecting system along an injection axle of a fuel injector. 20 : Fuel injecting system 22, 28 : Fuel injectors 24, 30 : Air inlet passages 32, 38 : Supply conduits 42, 48 : Fuel clouds.