Planetary reduction gear ring gear for a turbine engine

Patent metadata

Field	Value
Publication number	US-10704669-B2
Application number	US-201816211133-A
Country	US
Kind code	B2
Filing date	Dec 5, 2018
Priority date	Dec 6, 2017
Publication date	Jul 7, 2020
Grant date	Jul 7, 2020

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.

First claim

The invention claimed is:

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.

2. Ring gear according to claim 1 , wherein each one of the rims comprises an annular row of oil retention walls, walls of one of said rims being axially aligned with the walls of the other of the rims.

3. Ring gear according to claim 1 , wherein the walls extend substantially in planes that are parallel to said axis (X).

4. 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.

5. Ring gear according to claim 1 , wherein the walls are provided and secured to the first and second annular elements.

6. Ring gear according to claim 1 , wherein the walls are formed in one piece with the first and second annular elements.

7. Ring gear according to claim 1 , wherein said rims are substantially cylindrical.

8. Planetary reductions gear of a turbine engine, comprising a ring gear according to claim 1 .

9. Turbine engine, in particular of an aircraft, comprising a reduction gear according to claim 8 .

Assignees

• Safran Trans Systems

Inventors

• Charrier Mathieu Jean
• Morelli Boris Pierre Marcel
• Simon Adrien Louis

Classifications

• F16H57/0428

  Grooves with pumping effect for supplying lubricants · CPC title

• F16H57/0482

  Gearings with gears having orbital motion · CPC title

• F16H2055/176

  Ring gears with inner teeth · CPC title

• F02C7/36

  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) · CPC title

• F16H1/28

  with gears having orbital motion · CPC title