| 摘要 |
The invention relates to an arrangement (200) for an aircraft turbine engine combustion chamber, comprising an injection system and a fuel injector, the injection system comprising a spray nozzle guide (26), the inner surface (40) of which delimits an opening (40') for centring the nozzle (82), which comprises an outer casing (85). According to the invention, the arrangement comprises a sealing device (100) between the inner surface (40) of the guide (26) and the outer casing (85), the device (100) comprising: - a first part (102) accommodated in a groove (108) of the outer casing (85), the groove being delimited, in part, by a downstream delimiting surface (108a), the first part (102) having a first sealing surface (114) and bearing axially against the downstream delimiting surface (108a); and - a second part (104) having a second sealing surface (116) bearing radially against the inner surface (40) of the guide (26). |
