Planetary reduction gear for an aircraft turbine engine

Patent metadata

Field	Value
Publication number	US-12044305-B2
Application number	US-202017596045-A
Country	US
Kind code	B2
Filing date	May 29, 2020
Priority date	Jun 6, 2019
Publication date	Jul 23, 2024
Grant date	Jul 23, 2024

Abstract

A planetary reduction gear (10) for an aircraft turbine engine, said reduction gear comprising a rotatable sun gear, a rotatable ring gear (9) and satellite gears meshed with the sun gear and the ring gear and carried by a planet carrier intended to be fixed to a stator, the reduction gear further comprising an annular trough for recovering and channelling lubrication oil that is mounted around the ring gear, characterised in that the reduction gear further comprises an annular deflector (22) fixed to the ring gear and configured to route the oil exiting radially towards the outside of the ring gear up to the trough by virtue of centrifugal forces, the trough comprising an annular chamber (18) which is axially remote relative to a median plane (P) substantially passing through the centre of the ring gear, and an annular duct (20) located on a side of said chamber and emerging in said chamber.

First claim

The invention claimed is:

1. A planetary reduction gear for an aircraft turbine engine, said reduction gear comprising a rotatable sun gear, a rotatable ring gear, and planet gears meshed with the sun gear and ring gear and carried by a planet carrier intended to be fixed to a stator, said reduction gear further comprising an annular gutter for recovering and channelling lubrication oil that is mounted around the ring gear, said ring gear comprising fastening flanges and oil outlet orifices formed in facing faces of said fastening flanges, said facing faces being separated by a median plane substantially passing through a center of the ring gear, wherein the reduction gear further comprises an annular deflector fixed to said fastening flanges and configured to route the oil exiting radially towards said oil outlet orifices up to the gutter by virtue of centrifugal forces, said annular deflector protruding radially outwards the fastening flanges and having a free annular edge located radially outside from the fastening flanges, the gutter comprising:
a) an annular chamber which is axially remote relative to said median plane (P), and
b) an annular duct located on one side of said chamber and emerging into said chamber, this annular duct being configured to receive the oil routed by said deflector and to ensure its flow to the chamber,
wherein said annular duct extends about said free annular edge.

2. The reduction gear according to claim 1 , wherein the annular chamber defines a first upper semi-circular trough with a U-shaped axial cross-section, which extends substantially from 9 o'clock to 12 o'clock and from 12 o'clock to 3 o'clock by analogy with a dial of a clock, and a second lower semi-circular trough with a U-shaped axial cross-section, which extends substantially from 9 o'clock to 6 o'clock and from 6 o'clock to 3 o'clock by analogy with a dial of a clock.

3. The reduction gear according to claim 2 , wherein said first trough comprises a bottom defined by an inner cylindrical wall of the chamber, and said second trough comprises a bottom defined by an outer cylindrical wall of the chamber.

4. The reduction gear according to claim 3 , wherein the outer cylindrical wall comprises a radial opening for discharging oil.

5. The reduction gear according to claim 3 , wherein the inner and outer cylindrical walls have axes which are not aligned with each other and/or are not aligned with a longitudinal axis of the reduction gear.

6. The reduction gear according to claim 2 , wherein the first trough is connected to a radially inner annular wall forming part of said duct, and the second trough is connected to a radially outer annular wall forming part of said duct.

7. The reduction gear according to claim 1 , wherein a perforated annular partition is housed in said chamber and is configured to deaerate the oil.

8. The reduction gear according to claim 7 , wherein the first trough is connected to a radially inner annular wall forming part of said duct, and the second trough is connected to a radially outer annular wall forming part of said duct and wherein the partition comprises a first sector extending into the first trough, substantially at said radially inner annular wall ( 20 a ), and a second sector extending into the second trough, substantially at said radially outer annular wall.

9. An aircraft turbine engine, comprising a reduction gear according to claim 1 .

10. A planetary reduction gear for an aircraft turbine engine, said reduction gear comprising a rotatable sun gear, a rotatable ring gear, and planet gears meshed with the sun gear and ring gear and carried by a planet carrier intended to be fixed to a stator, said reduction gear further comprising an annular gutter for recovering and channelling lubrication oil that is mounted around the ring gear, characterised in that the reduction gear further comprises an annular deflector fixed to the ring gear and configured to route the oil exiting radially towards the outside of the ring gear up to the gutter by virtue of centrifugal forces, the gutter comprising:
c) an annular chamber which is axially remote relative to a median plane (P) substantially passing through a center of the ring gear, and
d) an annular duct located on one side of said chamber and emerging into said chamber, this annular duct being configured to receive the oil routed by said deflector and to ensure its flow to the chamber,
wherein the annular chamber defines a first upper semi-circular trough with a U-shaped axial cross-section, which extends substantially from 9 o'clock to 12 o'clock and from 12 o'clock to 3 o'clock by analogy with a dial of a clock, and a second lower semi-circular trough with a U-shaped axial cross-section, which extends substantially from 9 o'clock to 6 o'clock and from 6 o'clock to 3 o'clock by analogy with a dial of a clock, and wherein said first trough comprises a bottom defined by an inner cylindrical wall of the chamber, and said second trough comprises a bottom defined by an outer cylindrical wall of the chamber.

11. A planetary reduction gear for an aircraft turbine engine, said reduction gear comprising a rotatable sun gear, a rotatable ring gear, and planet gears meshed with the sun gear and ring gear and carried by a planet carrier intended to be fixed to a stator, said reduction gear further comprising an annular gutter for recovering and channelling lubrication oil that is mounted around the ring gear, characterised in that the reduction gear further comprises an annular deflector fixed to the ring gear and configured to route the oil exiting radially towards the outside of the ring gear up to the gutter by virtue of centrifugal forces, the gutter comprising:
e) an annular chamber which is axially remote relative to a median plane (P) substantially passing through a center of the ring gear, and
f) an annular duct located on one side of said chamber and emerging into said chamber, this annular duct being configured to receive the oil routed by said deflector and to ensure its flow to the chamber,

wherein a perforated annular partition is housed in said chamber and is configured to deaerate the oil.

12. The reduction gear according to claim 1 , wherein said annular chamber is located upstream of said median plane.

13. The reduction gear according to claim 10 , wherein the outer cylindrical wall comprises a radial opening for discharging oil.

14. The reduction gear according to claim 10 , wherein the inner and outer cylindrical walls have axes which are not aligned with each other and/or are not aligned with a longitudinal axis of the reduction gear.

15. The reduction gear according to claim 10 , wherein the first trough is connected to a radially inner annular wall forming part of said duct, and the second trough is connected to a radially outer annular wall forming part of said duct.

16. The reduction gear according to claim 10 , wherein a perforated annular partition is housed in said chamber and is configured to deaerate the oil.

17. The reduction gear according to claim 16 , wherein the first trough is connected to a radially inner annular wall forming part of said duct, and the second trough is connected to a radially outer annular wall forming part of said duct and wherein the partition comprises a first sector extending into the first trough, substantially at said radially inner annular wall ( 20 a ), and a second sector extending into the second trough, substantially at said radially outer annular wall.

18. The reduction gear according to claim 10 , wherein said annular chamber is loca

Assignees

• Safran Aircraft Engines

Inventors

• Jacquemard Christophe Paul
• Desombre Didier Gabriel Bertrand

Classifications

• F16N39/002

  by deaeration (degasification of liquids B01D19/00) · CPC title

• F16H57/0427 Primary

  on rotary parts, e.g. using baffles for collecting lubricant by centrifugal force · CPC title

• F05D2260/98

  Lubrication · CPC title

• F05D2260/40311

  of the epicyclical, planetary or differential type · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title