Lubrication system for aircraft engine reduction gearbox

A gas turbine engine, comprising:

• a power input and a power output;
• and
• an epicyclic gear train engaged with the power input and with the power output, the epicyclic gear train comprising:
• a sun gear defining a center axis and engaged with the power input;
• a plurality of planet gears mounted to a carrier and engaged to the sun gear, the plurality of planet gears rotatable about respective planet gear axes, the plurality of planet gears and the carrier rotatable about the center axis, the carrier engaged with the power output at a carrier-output engagement location;
• one or more ring gears in meshed engagement with the plurality of planet gears;
• a plurality of planet gear bearings, each planet gear bearing disposed between one of the plurality of planet gears and the carrier, a lubrication interface defined between each planet gear bearing and the one of the plurality of planet gears;
• and
• a bearing lubrication system including a lubricant supply conduit extending between a conduit inlet at the carrier-output engagement location and conduit outlets at the lubrication interfaces of the plurality of planet gear bearings, the bearing lubrication system including a lubricant strainer mounted about the conduit inlet at the carrier-output engagement location.