Oil transfer system on rotating shaft

Patent metadata

Field	Value
Publication number	US-9726039-B2
Application number	US-201414208485-A
Country	US
Kind code	B2
Filing date	Mar 13, 2014
Priority date	Mar 14, 2013
Publication date	Aug 8, 2017
Grant date	Aug 8, 2017

Abstract

A lubrication system for a device located between an internal shaft and an external shaft of an aircraft turbine, that are free to rotate, concentric and arranged at least partially one around the other, is provided. The lubrication system includes an annular element provided with an external groove and being mounted integral with the external shaft, the external groove being supplied with lubricant from a fixed part of the turbine; and a grooved element mounted integral with the internal shaft, the grooved element having a relief which directs a lubricant in contact with its external surface along a longitudinal direction when the internal shaft is rotating. The external groove is in fluid communication with an external surface of the grooved element through at least two conduits arranged through the external shaft.

First claim

The invention claimed is:

1. A lubrication system for a bearing located between and connecting an internal shaft and an external shaft of an aircraft turbine, said internal shaft and external shaft being free to rotate, concentric and arranged with the external shaft at least partially around the internal shaft, the lubrication system comprising: an annular element provided with an external groove, said annular element being configured so that said annular element can be mounted integral with said external shaft, said external groove being designed to be supplied with lubricant from a fixed part of the turbine; and a grooved element configured to be mounted integral with said internal shaft, said grooved element having a helical groove around an external surface of said grooved element designed to direct a lubricant in contact with the external surface of said grooved element along a given longitudinal direction toward the bearing due to an orientation of the helical groove when said internal shaft is rotating, wherein said external groove of said annular element is in fluid communication with said external surface of said grooved element through at least two conduits arranged through said external shaft, wherein said annular element comprises an opening in fluid communication with said external groove, said opening including a recess extending around a portion of an inner periphery of said annular element, a first end of said recess passing through said annular element so as to open up in said external groove, wherein a second end of said recess opens up in a duct housing formed on said annular element.

2. The lubrication system according to claim 1 , further comprising an accumulation ring forming a lubricant reservoir, configured to be mounted in said external shaft.

3. The lubrication system according to claim 2 , wherein a surface of said accumulation ring extends radially from an upstream side of said grooved element and is arranged to limit any projection of lubricant on said upstream side of said grooved element.

4. The lubrication system according to claim 2 , further comprising a retaining ring, each duct having an outer collar designed to be sandwiched between said retaining ring and said accumulation ring.

5. The lubrication system according to claim 1 , further comprising at least two ducts, placed inside a corresponding conduit, each duct being configured to extend from said external groove of said annular element to said external surface of said grooved element.

6. The lubrication system according to claim 1 , wherein the bearing is a roller bearing or a ball bearing.

7. An aircraft turbine comprising:
an internal shaft and an external shaft that are free to rotate, concentric and arranged with the external shaft at least partially around the internal shaft; and
a lubrication system according to claim 1 .

8. The aircraft turbine according to claim 7 , wherein said internal shaft and said external shaft rotate in opposite directions when the aircraft turbine is in operation.

9. The lubrication system according to claim 1 , wherein said opening includes a blade arranged through said annular element, a first end of said blade being arranged to project in said external groove and a second end of said blade being directed towards an inside of said recess.

Assignees

• Snecma

Inventors

• Belmonte Olivier
• Antunes Serge Louis
• Perrier Mathieu

Classifications

• F01D25/18 Primary

  Lubricating arrangements (of machines or engines in general F01M) · CPC title

• F02C7/06

  Arrangements of bearings (bearings F16C); Lubricating ({of turbo machines F01D25/18; of machines or} engines in general F01M) · CPC title

• F02K3/072

  with counter-rotating {, e.g. fan} rotors · CPC title

• F02C6/206

  the vehicles being airscrew driven · CPC title

• F05B2250/25

  helical · CPC title