Mechanical reduction device for aircraft turbomachine

Abstract

This application relates to a mechanical reduction gear (160) for a turbine (1), particularly a turbine for an aircraft, the reduction gear comprising: a sun gear (70) having a rotation axis; a ring gear (90) extending around the sun gear (70); planetary gears (80) meshing with the sun gear (70) and the ring gear (90), and each planetary gear comprising a first toothed portion (84) and a second toothed portion (84), each toothed portion comprising two series of teeth located on both sides of a median plane (H), each planetary gear (80) being centered and rotatably guided by bearings (94a, 94b) including an upstream bearing (94a) and a downstream bearing (94b), the upstream bearing being axially positioned between a series of upstream teeth (84d1) of the second toothed portion (84) and the plane (H), and the downstream bearing being axially positioned between a series of downstream teeth (84d2) of the second toothed portion (84) and the plane (H).

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