Assembly of aircraft turbine engine comprising improved lubrication system of fan-driven reduction gear

The invention relates to an assembly (22) of an aircraft turbine engine, comprising a fan-driven reduction gear (20) and a lubrication system (24), said lubrication system (24) comprising:-a reduction gear housing (31a); a lubricating oil tank (26); a lubricating oil supply circuit (28) comprising a supply pump (38); -a lubricating oil recovery circuit (30) comprising a pump (46a) for recovering lubricating oil from the reduction gear housing (31a). According to the invention, the recovery circuit comprises a lubricating oil distributor (52) comprising:-a lubricating oil inlet (54) communicating with a lubricating oil outlet (55) of the housing (31a); an air inlet (56); -a dispenser outlet (58) capable of employing a lubricating oil recovery structure and a structure for holding the lubricating oil in the housing. 本发明涉及飞行器涡轮发动机的组件(22)，其包括风扇驱动减速齿轮(20)和润滑系统(24)，所述润滑系统(24)包括：-减速齿轮壳体(31a)；-润滑油箱(26)；-包括供给泵(38)的润滑油供给回路(28)；-润滑油回收回路(30)，其包括用于从减速齿轮壳体(31a)回收润滑油的泵(46a)。根据本发明，该回收回路包括润滑油分配器(52)，其包括：-与壳体(31a)的润滑油出口(55)连通的