# US 11,079,008 B2 · Lubrication of a planet-carrier for a mechanical reduction gear of a turbine engine, in particular of an aircraft > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,079,008 B2 - Document ID: US11079008B2 - Status: Granted - Kind: B2 - Application number: 16/790,476 - Filed: 2020-02-13 - Published: 2020-08-20 - Granted: 2021-08-03 - Earliest claimed: 2019-02-14 - Assignees: Safran Transmission Systems - Applicants: Safran Transmission Systems - Inventors: Adrien Louis Simon; Mathieu Jean Charrier; Jean-Charles Michel Pierre Di Giovanni; Simon Loïc Clément Lefebvre; Guillaume Jean Pierre Robinet - Web page: https://patentgrep.com/patent/US11079008B2 ## CPC - F16H 57/0486: {with fixed gear ratio (axle or inter-axle differentials F16H57/0483)} - F01D 25/18: Lubricating arrangements (of machines or engines in general F01M) - F02C 7/36: Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user ({F02C3/107 - F02C3/13 and} F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H) - F16H 1/36: with two central gears coupled by intermeshing orbital gears - F16H 57/042: {Guidance of lubricant} - F16H 57/0482: {Gearings with gears having orbital motion} - F16H 57/082: {Planet carriers} - F16H: GEARING - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00) ## Abstract The present disclosure relates to the lubrication of a planet-carrier for a mechanical reduction gear of a turbine engine, for example of an aircraft. The planet-carrier includes a cage defining an internal housing configured to receive a central sun gear with an axis of rotation X, and an annular row of planet gears arranged around the sun gear. The cage includes two annular walls that are radial with respect to the axis X, and connected to one another at their outer periphery by a cylindrical wall. At least one of the radial walls has orifices for mounting the planet gears, and the cylindrical wall has through-holes for the passage of the gearings of the planet gears so that they may engage with a gearing of the ring gear, which is configured to extend around the planet gears and the cage. ## Claims ### Claim 1 A planet-carrier for a mechanical reduction gear of a turbine engine, comprising: a cage defining an internal housing configured to receive a central sun gear with an axis of rotation (X), and an annular row of planet gears arranged around the central sun gear, the cage comprising: two annular radial walls that are radial with respect to the axis of rotation (X), and connected to one another at their outer periphery by a cylindrical wall of the axis of rotation (X), at least one of these two annular radial walls comprising a plurality of planet gear mounting orifices, and the cylindrical wall comprising a plurality of through-holes configured to receive the annular row of planet gears so that they engage with a ring gear, which is configured to extend around the annular row of planet gears and the cage; and an annular distributor of lubricating oil formed of a single part and secured to an inner periphery of one of the two annular radial walls of the cage, so as to define, together with the one of the two annular radial walls, two annular chambers which are independent and sealed to oil circulation. ### Claim 2 (depends on 1) The planet-carrier according to claim 1, wherein the annular distributor comprises a second cylindrical wall internally delimiting the two annular chambers and an annular partition closing axially one of the two annular chambers. ### Claim 3 (depends on 2) The planet-carrier according to claim 2, wherein the annular distributor comprises two annular partitions that extend radially outwards from the second cylindrical wall and together delimit one of the two annular chambers, the other of the two annular chambers being delimited by one of the two annular partitions and an annular surface facing the annular radial wall on which the annular distributor is provided. ### Claim 4 (depends on 2) The planet-carrier according to claim 2, wherein each annular partition comprises at an outer periphery thereof an external cylindrical centering surface on which is formed an annular groove for receiving an annular seal configured to cooperate with the inner periphery of the annular radial wall on which the annular distributor is attached. ### Claim 5 (depends on 2) The planet-carrier according to claim 2, wherein the second cylindrical wall comprises a cylindrical centering surface on which is formed an annular groove configured to receive an annular seal configured to cooperate with the inner periphery of the annular radial wall on which the distributor is attached. ### Claim 6 (depends on 1) The planet-carrier according to claim 1, wherein the two annular chambers are arranged adjacently, one behind the other, along the axis of rotation (X). ### Claim 7 (depends on 1) The planet-carrier according to claim 1, wherein each of the two annular chambers has a parallelepiped cross sectional shape. ### Claim 8 (depends on 1) The planet-carrier according to claim 1, wherein the annular distributor comprises a flange or fixation lugs onto the cage. ### Claim 9 (depends on 5) The planet-carrier according to claim 5, wherein an internal cylindrical surface of the inner periphery of the annular radial wall on which the annular distributor is provided comprises a protruding annular rib configured to cooperate with the annular seal. ### Claim 10 (depends on 1) The planet-carrier according to claim 1, wherein an oil nozzle is connected to one of the two annular chambers. ### Claim 11 (depends on 10) The planet-carrier according to claim 10, wherein the oil nozzle is integrated into the annular distributor, and wherein the annular distributor comprises a second cylindrical wall internally delimiting the two annular chambers and an annular partition closing axially one of the two annular chambers. ### Claim 12 (depends on 1) A reduction gear for a turbine engine, comprising: a sun gear mounted rotationally on a drive shaft around an axis (X) of rotation; a plurality of planet gears arranged around the axis (X) of rotation; and a ring gear that extends around the plurality of planet gears and is coaxial with the axis (X) of rotation, wherein the plurality of planet gears is engaged with the sun gear and the ring gear, wherein the plurality of planet gears is movably mounted on the planet-carrier according to claim 1. ### Claim 13 (depends on 1) A turbine engine of an aircraft having a mechanical reduction gear, the mechanical reduction gear comprising the planet-carrier according to claim 1.