Sealing device between an injection system and a fuel injection nozzle of an aircraft turbine engine

An arrangement for a combustion chamber for an aircraft turbine engine, the arrangement comprising:

• a system for injection of an air-fuel mix into the combustion chamber;
• and
• a fuel injector comprising an injector nozzle,
• the injection system comprising an injector nozzle guide, an inner surface of the injector nozzle guide delimits a centering opening in which there is the injector nozzle that is composed of an outer casing centered on a longitudinal axis of the injector nozzle,
• wherein the arrangement further comprises a sealing device between the inner surface of the injector nozzle guide and the outer casing of the injector nozzle, the sealing device comprising:
• a first part accommodated in a groove in the outer casing, said groove extending around said longitudinal axis and being delimited partly by a downstream delimiting surface, the first part having a first sealing surface and bearing axially against said downstream delimiting surface of the groove;
• and
• a second part having a second sealing surface bearing radially against said inner surface of the injector nozzle guide.