MECHANICAL REDUCER FOR AN AIRCRAFT TURBOMACHINE

Abstract

Mechanical gearbox (110) for a turbomachine (1), in particular for aircraft, the gearbox (110) comprising: - a sun gear (111), - a ring gear (114), - planet gears (112) interposed between the sun gear (111) and the ring gear (114), - a planet carrier (113) having two annular flanges (128, 130), and - at least one oil distributor (116) fixed to the first flange (128), each of the flanges (128, 130) comprising two rings, respectively internal (132) and external (134), and radial partitions (136) perpendicular to the first axis (X) which connect the rings (132, 134) to each other, each of the flanges (128, 130) being hollowed out and having circular arc-shaped recesses (138) which extend around the first axis (X), the distributor (116) includes mounting lugs (140) that are axially applied and fixed to at least one of the rings (132, 134) and / or to the partitions (136) of the first flange (128). Abbreviated figure: Figure 3

Claims

- between the external diameter (Dann_int) of the inner ring and the diameter (De) of a circumference (C) centered on the first axis (X) and passing through the second axes (Y), or - between the diameter (De) of a circumference (C) centered on the first axis (X) and passing through the second axes (Y) and the internal diameter (Dann-ext) of the outer ring (134).

11. Reducer (110) according to the preceding claim, wherein the distributor (116) or its component (142) comprises conduits (148) extending radially with respect to the first axis (X).

12. Reducer (110) according to any one of the preceding claims, wherein the planet carrier (113) comprises a web (150) perpendicular to the first axis (X) and which passes through the middle of the planet carrier (113), the web (150) connecting the inner and outer rings (132, 134) and axially separating the recesses (138) of the first flange (128) opposite the recesses (138) of the second flange (130).

13. Reducer (110) according to any one of the preceding claims, wherein it comprises another oil distributor (116) which is centered on the first axis (X) and fixed on the second flange (130), this distributor (116) comprising fixing lugs (140) which are applied axially and fixed on at least one of the rings (132, 134) and / or on the partitions (136) of the second flange (130).

14. Reducer (110) according to the preceding claim, in which the distributors (116) are fluidly connected to each other, for example by pipes (156) which axially pass through the supports (120) of the satellites (112).

15. Turbomachine (1), in particular aircraft turbomachine, comprising a reducer (110) according to any one of the preceding claims. [Fig. 3] 131 ' X Dann-int Dextl Fig. 7]

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