Gearbox of aircraft turbine engine

Patent metadata

Field	Value
Publication number	US-9790804-B2
Application number	US-201515313036-A
Country	US
Kind code	B2
Filing date	May 22, 2015
Priority date	May 23, 2014
Publication date	Oct 17, 2017
Grant date	Oct 17, 2017

Abstract

A gearbox for an aircraft turbine engine has a casing defining an enclosure for housing rotating elements lubricated by oil. At least one tubular sleeve is coupled to the rotating elements and configured to rotate a shaft. The sleeve includes splines configured to cooperate with complementary splines of said shaft. The gearbox further includes means for recovering lubricating oil from the rotating elements and conveying the recovered oil by streaming to the splines to lubricate the splines.

First claim

The invention claimed is:

1. A gearbox for an aircraft turbine engine, comprising a casing defining an enclosure for housing rotating elements lubricated by oil, and at least one tubular sleeve coupled to the rotating elements and configured to rotate a shaft, the sleeve including splines configured to cooperate with complementary splines of said shaft, the gearbox further comprising means for recovering lubricating oil from the rotating elements and conveying recovered oil by streaming to the splines to lubricate the splines, said recovery and conveying means comprising at least one inner wall collecting oil from said casing, the gearbox being configured to cause the oil to stream over said at least one collecting inner wall during the operation of the turbine engine, wherein said recovery and conveying means comprise a channeling member that extends at least partially inside said sleeve, and at least one gutter configured to convey the oil that streams over said at least one collecting inner wall to the channeling member, in which said channeling member and said at least one gutter are supported by or formed with a flange of the casing, the flange defining said at least one collecting inner wall and supporting a rolling bearing of the sleeve, the flange including at least one radial opening allowing oil flowing on said collecting inner wall to reach said channeling member.

2. The gearbox according to claim 1 , wherein the flange has a planar part and a hollow cylindrical part that extends substantially perpendicular to the planar part and that supports the rolling bearing, said channeling member extending inside the cylindrical part from the planar part, and said at least one radial opening being arranged in the cylindrical part at a junction with the planar part such that the streaming oil passes through said at least one radial opening to be collected in said at least one gutter.

3. The gearbox according to claim 1 , wherein said splines extend in a longitudinal annular cavity of the sleeve that is defined at one longitudinal end by an annular seal configured to cooperate with said shaft, and an opposite longitudinal end by an annular dam preferably formed by a leveling seal whereof the outer periphery defines a maximum oil level in said annular cavity.

4. The gearbox according to claim 3 , wherein the annular dam extends in a transverse plane that is traversed by the recovery and conveying means.

5. The gearbox according claim 1 , wherein said flange comprises two gutters together forming a V with an angle of about 120°-160°.

6. The gearbox according claim 1 , wherein at least one of the at least one gutters has a substantially U-shaped section.

7. The gearbox according claim 1 , wherein at least one of the at least one gutters extends substantially radially relative to the axis of said cylindrical part of the flange.

8. The gearbox according claim 1 , wherein at least one of the at least one gutters is situated in an axial space extending between said planar part of the flange and an end of the sleeve guided by said bearing.

9. The gearbox according claim 1 , wherein the channeling member has a substantially U-shaped section.

10. An aircraft turbine engine, such as an airplane or helicopter turbojet engine or turboprop, comprising at least one gearbox according to claim 1 .

Assignees

• Safran Aircraft Engines

Inventors

• Lepretre Jean-Baptiste Etienne Bernard

Classifications

• F01D15/08

  Adaptations for driving, or combinations with, pumps · CPC title

• F01D15/10

  Adaptations for driving, or combinations with, electric generators · CPC title

• F05D2260/98

  Lubrication · CPC title

• F05D2220/323

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

• F01D15/12 Primary

  Combinations with mechanical gearing (driven by multiple engines F01D13/00) · CPC title