INJECTOR COMBUSTION CHAMBER GAS TURBINE WITH DOUBLE fuel system and combustion chamber provided with at least one SO INJECTOR

摘要

1. An injector (1, 1 ') of the combustion chamber (3) of a gas turbine comprising a dual fuel injection circuit (C1, C2) and an air path (C3), characterized in that the fuel injection circuit (C1, C2) are composed of the fuel system starting (C1) capable of causing ignition in the chamber (3) continue to work in all flight modes, and the main circuit fuel supply (C2) intended to operate in all modes of flight, after ignition, and fuel system (C1, C2) are parallel line (12a, 12b), formed in the common pipe (11, 11 ') along the longitudinal axis (X'X), start-up circuit (12a) is opened INDICATES one end (12e) substantially in the center of the spherical injector housing (11s), which continues to the common pipe (11, 11 ') at the end (12e) a conduit comprising an injection ramp (7) for driving the fuel into rotation before injecting it into chamber (3) through the central channel (41) passing through the central wall (14) of the swirler (4), a channel (12b) of the main circuit (C2) opens into the annular channel (16) formed in the housing (11s) opposite the jets channels ( 42) disposed radially in the main wall (14) around the central channel (41) and brakes the chain (C3) is directed between dy two parts concentric spheres formed, which opens a swirler (4) .2 injector housing (11s) and the shell (5, 5 ') surrounding the injector body (11s) and having an opening (15). Injector according to claim 1, wherein a swirler (4) is in the tilted position (Y'Y) of the injector relative to the longitudinal axis (X'X) to accommodate the end (12e) a triggering circuit (12a) at its center and the orientation of the air jet (Ca ) and fuel (Cs) at the injector exit in the direction of the spark plug (101) located in the bottom of the chamber (3f) .3. Injector according to claim 1, wherein the conduit (12a) starting