Oil pipe cover and mechanical reduction gear for an aircraft turbomachine comprising such a cover

An oil pipe cover for a reduction gear of an aircraft turbomachine, the oil pipe cover being configured to be fixed to a planet carrier of the reduction gear and to be mounted on an axial end of a tubular support for a hydrodynamic bearing of a planet gear of the reduction gear, the oil pipe cover comprising an annular body extending around an axis (Y) and comprising a mounting central orifice on the axial end, wherein the annular body comprises:

• a first circumferential deflector having a first circumferential extent (α1) around the axis (Y), the first circumferential deflector comprising a circumferential oil guiding surface (38a) located radially outwards with respect to an axis (Y);
• a second circumferential deflector having a second circumferential extent around the axis (Y), the second circumferential deflector comprising a circumferential oil guiding surface located radially inwards with respect to an axis (Y), the first and second circumferential deflectors being diametrically opposed with respect to an axis (Y);
• and
• oil discharge pipes which pass substantially axially through the annular body and which are diametrically opposed with respect to the first circumferential deflector, the oil discharge pipes opening axially on a side of the second circumferential deflector, radially inside the second circumferential deflector with respect to an axis (Y).