# US 2019/0170240 A1 · Planetary reduction gear ring gear for a turbine engine > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2019/0170240 A1 - Document ID: US20190170240A1 - Status: Published application - Kind: A1 - Application number: 16/211,133 - Filed: 2018-12-05 - Published: 2019-06-06 - Earliest claimed: 2017-12-06 - Assignees: Safran Transmission Systems - Applicants: Safran Transmission Systems - Inventors: Mathieu Jean CHARRIER; Boris Pierre Marcel MORELLI; Adrien Louis SIMON - Web page: https://patentgrep.com/patent/US20190170240A1 ## CPC - F16H 57/0427: {on rotary parts, e.g. using baffles for collecting lubricant by centrifugal force} - 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 1/28: with gears having orbital motion - F16H 55/17: Toothed wheels (worm wheels F16H55/22; chain wheels F16H55/30) - F16H 57/0428: {Grooves with pumping effect for supplying lubricants} - F16H 57/0482: {Gearings with gears having orbital motion} - F16H 57/0486: {with fixed gear ratio (axle or inter-axle differentials F16H57/0483)} - F16H 57/08: of gearings with members having orbital motion - F05D 2260/40311: of the epicyclical, planetary or differential type - F05D 2260/98: Lubrication - F16H 2055/176: {Ring gears with inner teeth} - 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) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS ## Abstract A planetary reduction gear ring gear for a turbine engine, in particular of an aircraft, the ring gear extending about an axis (X) and including first and second coaxial annular elements and respectively two inner annular teeth oriented differently. The first and second annular elements include respectively first and second radially external annular flanges to secure the first and second elements to one another, the teeth of the first and second annular elements being axially spaced from one another and from a joint plane (P) of the first and second flanges, and defining between them an annular space externally delimited by two annular rims supporting respectively the flanges. At least one of the flanges includes joint plane notches that are substantially radial for the oil to pass through by centrifugation. The ring gear further includes an annular row of oil-retention walls protruding from the rims in the space. ## Claims ### Claim 1 Ring gear of a planetary reduction gear for a turbine engine, in particular of an aircraft, said ring gear extending about an axis (X) and comprising first and second coaxial annular elements and comprising respectively two inner annular teeth oriented differently, said first and second annular elements further comprising respectively first and second radially external annular flanges to secure said first and second elements to one another, the teeth of said first and second annular elements being axially spaced from one another and from a joint plane (P) of said first and second flanges, and defining between them an annular space externally delimited by two annular rims supporting respectively said flanges, at least one of the flanges comprising at the level of said joint plane notches that are substantially radial for the oil to pass through by centrifugation, wherein it further comprises an annular row of oil-retention walls protruding from said rims in said space. ### Claim 2 (depends on 1) Ring gear according to claim 1, wherein each one of the rims comprises an annular row of oil retention walls, the walls of one of said rims being axially aligned with the walls of the other of the rims. ### Claim 3 (depends on 1) Ring gear according to claim 1, wherein the walls extend substantially in planes that are parallel to said axis (X). ### Claim 4 (depends on 1) Ring gear according to claim 1, wherein the walls of one of the rims are spaced by an axial clearance (E) from the walls the other of the rims. ### Claim 5 (depends on 1) Ring gear according to claim 1, wherein the walls are provided and secured to the first and second annular elements. ### Claim 6 (depends on 1) Ring gear according to claim 1, wherein the walls are formed in one piece with the first and second annular elements. ### Claim 7 (depends on 1) Ring gear according to claim 1, wherein said rims are substantially cylindrical. ### Claim 8 (depends on 1) Planetary reductions gear of a turbine engine, comprising a ring gear according to claim 1. ### Claim 9 (depends on 8) Turbine engine, in particular of an aircraft, comprising a reduction gear according to claim 8.