EPICYCLIC REDUCTION GEAR, NOTABLY FOR A TURBOMACHINE

• US 20150252889A1
• Filed: 08/29/2013
• Published: 09/10/2015
• Est. Priority Date: 09/04/2012
• Status: Active Grant

• Current Assignee: Safran Transmission Systems
• Original Assignee: Hispano-Suiza (Safran SA)
• Inventors: Feraud, Benjamin
• Granted Patent: US 9,404,568 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: 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
• CPC Class Codes: F05D 2260/40311 of the epicyclical, planetary or differential type
• CPC Class Codes: F16H 2057/085 Bearings for orbital gears
• CPC Class Codes: F16H 57/0442 for supply in case of failure, i.e. auxiliary supply
• CPC Class Codes: F16H 57/045 Lubricant storage reservoirs, e.g. reservoirs in addition to a gear sump for collecting lubricant in the upper part of a gear case
• CPC Class Codes: F16H 57/0479 Gears or bearings on planet carriers
• CPC Class Codes: F16H 57/0486 with fixed gear ratio differentials F16H57/0483
• CPC Class Codes: F16H 57/082 Planet carriers

Abstract

An epicyclic reduction gear, for example for a turbomachine, including an internal sun gear and an external sun gear, which are coaxial, with the internal sun gear being movable in rotation about its axis, with the external sun gear being stationary. At least one planet gear is mounted to be movable in rotation on a planet carrier and meshing with both the internal sun gear and the external sun gear. The planet carrier is configured to pivot about the axis of the internal sun gear and the external sun gear, the planet gear having a cylindrical inner surface mounted to be movable in rotation around a cylindrical surface of the planet carrier. The reduction gear further includes a mechanism supplying oil at an interface between the cylindrical surfaces.

Claims

1-10. -10. (canceled)

11. An epicyclic reduction gear, or for a turbomachine, comprising:

an internal sun gear and an external sun gear, which are coaxial, with the internal sun gear being movable in rotation about its axis, with the external sun gear being stationary;

at least one planet gear mounted to be movable in rotation on a planet carrier and meshing with both the internal sun gear and the external sun gear, the planet carrier configured to pivot about the axis of the internal sun gear and the external sun gear, the planet gear having a cylindrical inner surface mounted to be movable in rotation around a cylindrical surface of the planet carrier;

means for supplying oil at an interface between the cylindrical surfaces, wherein the oil supplying means comprises a chamber provided in the planet carrier, configured to form a buffer volume of oil, and including a lower zone spaced from the axis of rotation of the planet carrier, an upper zone close to the axis of rotation of the planet carrier, at least one main passage opening at the interface and at the upper zone, and at least one secondary passage opening at the interface and at the lower zone.

12. A reduction gear according to claim 11, wherein the chamber is substantially cylindrical.

13. A reduction gear according to claim 11, wherein the section of the secondary passage is smaller than the section of the main passage.

14. A reduction gear according to claim 11, wherein the chamber comprises at least two parts which are axially shifted relative to each other and connected together by at least one communication hole opening at the lower zone of each part of the chamber.

15. A reduction gear according to claim 14, wherein the two parts of the chamber are separated by a partition wall which comprises a hole connecting both parts and opens at the upper zone of each part, with the main passage opening in the hole.

16. A reduction gear according to claim 11, wherein the secondary passage opens in the chamber at a point radially away from a lowest point of the chamber.

17. A reduction gear according to claim 16, wherein the secondary passage opens in the chamber at a zone protruding relative to an inner wall of the chamber.

18. A reduction gear according to claim 11, comprising at least two secondary passages, opening on either side of a radial plane going through the axis of rotation of the planet carrier, at points radially away from a lowest point of the chamber.

19. A reduction gear according to claim 18, wherein each secondary passage opens in a part of the chamber.

20. A reduction gear according to claim 11, wherein the chamber comprises a groove provided in the lower zone of the chamber, with the groove comprising at least an upper zone and at least a lower zone axially spaced from each other, with the lower zone of the groove being radially further away from the axis of rotation of the planet carrier than the upper zone of the groove, with the lower zone of the groove being axially away from the opening of the secondary passage in the chamber.