Patent ID: 11959418
Assignee: SAFRAN TRANSMISSION SYSTEMS
Field: Mechanical elements (Mechanical engineering)
Classification: CPC F | IPC F

Claim 0:
1. An assembly for an aircraft turbomachine, comprising:
an epicyclic gear speed reducer; and
at least one oil sprinkler configured to spray an oil jet oriented in a direction comprising at least one component parallel to a longitudinal axis of the turbomachine,
wherein the epicyclic gear speed reducer comprises a planet carrier equipped with an impeller configured to be secured in rotation with the planet carrier and to be rotated about said longitudinal axis, the impeller having an annular shape about the longitudinal axis and comprising lubrication means for lubricating planet gears bearings of the epicyclic gear speed reducer, the lubrication means comprising an annular cavity located at an internal periphery of the impeller, the impeller comprising an internal peripheral wall for closing off the annular cavity in a radial direction, the impeller comprising an annular port which extends around the longitudinal axis and which opens out in an axial direction into the annular cavity for the purpose of being supplied with lubricating oil by the oil jet which is configured to pass through the annular port,
wherein the annular cavity is axially delimited by two annular side walls, a first of the two annular side walls being connected at an internal periphery thereof to the internal peripheral wall of the impeller and the second of the two annular side walls comprising the annular port or having an internal periphery thereof radially spaced from the internal peripheral wall in order to define the annular port, wherein the annular cavity comprises oil guiding fins configured to guide the lubricating oil and limit disturbance of the lubricating oil depending on a direction of rotation of the impeller.