FIELD: machine building.
SUBSTANCE: invention relates to device (200) for a combustion chamber of an aircraft gas turbine engine, which includes an injection system and a fuel injector, wherein the injection system comprises nozzle injector guide (26), inner surface (40) limiting nozzle alignment hole (82) comprising outer housing (85). Device comprises sealing device (100) between inner surface (40) of guide (26) and outer housing (85); said device (100) comprises: first part (102) located in groove (108) in outer housing (85), partially limited by downstream limiting surface (108a), wherein first part (102) has first sealing surface (114), and second part (104) having second sealing surface (116), wherein system (18) for injection of fuel-air mixture includes divergent bowl (28).
EFFECT: result is an increase in performance and life of the combustion chamber.
10 cl, 10 dwg
