US 12,480,451 B2
Mechanical reducer for an aircraft turbomachine
Adrien Louis Simon, Moissy-Cramayel (FR); Luc Henri Chatenet, Moissy-Cramayel (FR); Boris Pierre Marcel Morelli, Moissy-Cramayel (FR); and Jonathan Jean-Pierre Rouffet, Moissy-Cramayel (FR)
Assigned to SAFRAN TRANSMISSION SYSTEMS, Colombes (FR); and SAFRAN AIRCRAFT ENGINES, Paris (FR)
Filed by SAFRAN TRANSMISSION SYSTEMS, Colomes (FR); and SAFRAN AIRCRAFT ENGINES, Paris (FR)
Filed on Apr. 21, 2023, as Appl. No. 18/305,208.
Claims priority of application No. 2203777 (FR), filed on Apr. 22, 2022.
Prior Publication US 2023/0340912 A1, Oct. 26, 2023
Int. Cl. F02C 7/36 (2006.01); F02C 7/06 (2006.01)
CPC F02C 7/36 (2013.01) [F02C 7/06 (2013.01); F05D 2220/323 (2013.01); F05D 2240/50 (2013.01); F05D 2260/40311 (2013.01)] 16 Claims
OG exemplary drawing
 
1. A mechanical reducer for a turbomachine, the reducer comprising:
a sun gear having a first axis of rotation, the sun gear having internal splines and an external toothing;
a ring gear which extends around the sun gear and which has an internal toothing;
planet gears arranged between the sun gear and the ring gear, each of the planet gears comprising at least one external toothing meshing with the external toothing of the sun gear and the internal toothing of the ring gear, the planet gears being crossed by a plane which is perpendicular to the first axis, the plane passing in the middle of the planet gears and being a plane of symmetry for each of the planet gears, the plane further passing in the middle of the external toothing and in the middle of the internal toothing;
a planet carrier which carries first bearings for guiding the planet gears in rotation about second axes parallel to the first axis; and
at least one second bearing for guiding the sun gear in rotation,
wherein the at least one second bearing is mounted between the sun gear and the planet carrier, and wherein the at least one second bearing is axially remote from the plane,
wherein the at least one second bearing comprises two second bearings, and wherein the two second bearings are at an axial distance from each other, which is smaller than an axial dimension of the first bearings or of the planet gears,
wherein the sun gear comprises a first axial tubular extension which extends to one side of the sun gear and on which one of the two second bearings is mounted, and
wherein the sun gear comprises a second axial tubular extension which extends on an opposite side of the sun gear and on which is mounted the other of the two second bearings.