Collector for a drained liquid for an aircraft turbine engine and associated turbine engine

Collector (10) for a drained liquid for an aircraft turbine engine, the collector comprising:

• an internal cavity (54) comprising a first space (54A) for collecting the drained liquid and a second space (54B) for transferring the collected liquid to a recovery outlet (30), the internal cavity extending longitudinally in a first direction (Z) between a first end closed off by a bottom wall (16) of the collector and a second end closed off by a cover (14) of the collector;
• at least one inlet (44) for the drained liquid, in fluid communication with the first space (54A);
• and
• at least one recovery outlet (30), in fluid communication with the second space (54B);
• wherein the first space (54A) and the second space (54B) are separated from each other by a liquid-tight partition (56) in which is arranged a drained liquid passage restriction means (58) which restricts the passage of the drained liquid from the first space to the second space, the passage restriction means comprising at least one orifice (58A), and
• wherein the drained liquid passage restriction means is mounted so that it may be removed from the collector (10) by moving the drained liquid passage restriction means along the first direction (Z), in the directional sense that extends from the bottom wall (16) of the collector towards the cover (14) of the collector.