Lubricating oil piping gutter of an aircraft turbomachine

Patent metadata

Field	Value
Publication number	US-11008942-B2
Application number	US-201916522535-A
Country	US
Kind code	B2
Filing date	Jul 25, 2019
Priority date	Jul 26, 2018
Publication date	May 18, 2021
Grant date	May 18, 2021

Abstract

The present disclosure describes a lubrication oil piping gutter of an aircraft turbomachine. The lubrication oil piping gutter can be used for a sun gear train reducer of the turbomachine. The gutter may include two lateral annular walls connected at their outer periphery by an annular bottom wall. In some embodiments, the annular bottom wall may include at least one oil evacuation opening in which is located a deflector configured to facilitate the flow of oil radially from the inside to the outside of the gutter.

First claim

We claim:

1. A lubrication oil piping gutter of an aircraft turbomachine, for a sun gear train reducer of the aircraft turbomachine, comprising:
two lateral annular walls connected at their outer periphery by an annular bottom wall,
the annular bottom wall includes at least one oil evacuation opening,
a deflector located in the at least one oil evacuation opening, the deflector configured to facilitate a flow of oil radially from inside to outside of the lubrication oil piping gutter, wherein the deflector has a L-shape and comprises a first wall extending into the lubrication oil piping gutter and a second wall extending from the first wall to outside of the lubrication oil piping gutter.

2. The lubrication oil piping gutter according to claim 1 , wherein the first wall extends parallel to the annular bottom wall of the lubrication oil piping gutter, and the second wall extends in a plane passing through an axis of revolution of the lubrication oil piping gutter.

3. The lubrication oil piping gutter according to claim 1 , wherein the deflector is a part attached into the lubrication oil piping gutter.

4. The lubrication oil piping gutter according to claim 1 , wherein the second wall passes through the at least one oil evacuation opening.

5. The lubrication oil piping gutter according to claim 1 , wherein the second wall delimits a first oil passage with a first edge of the at least one oil evacuation opening and a second oil passage with an opposite second edge of the at least one oil evacuation opening.

6. The lubrication oil piping gutter according to claim 5 , wherein the first wall covers the first edge of the at least one oil evacuation opening.

7. The lubrication oil piping gutter according to claim 1 , wherein the deflector comprises lateral edges extending from a side of each of the lateral annular walls of the lubrication oil piping gutter, at least along the second wall.

8. The lubrication oil piping gutter according to claim 1 , wherein the deflector extends over an entire axial dimension of the annular bottom wall.

9. The lubrication oil piping gutter according to claim 1 , further including: radially outer lugs for fixing to an engine casing.

10. An aircraft turbomachine, comprising a sun gear train reducer including an outer cowl for recovering rotating mobile oil and surrounded by at least one lubrication oil piping gutter according to claim 1 .

Assignees

• Safran Aircraft Engines

Inventors

• Jacquemard Christophe Paul
• Desombre Didier Gabriel Bertrand
• Morreale Serge René

Classifications

• F16H57/04

  Features relating to lubrication or cooling {or heating} (control of lubrication or cooling in hydrostatic gearing F16H61/4165) · CPC title

• F01D25/18 Primary

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

• F16H57/042

  Guidance of lubricant · CPC title

• F05D2260/609

  Deoiling or demisting · CPC title

• F05D2260/40311

  of the epicyclical, planetary or differential type · CPC title