Oil restrictor for emergency lubrication of a component for an aircraft turbine engine

Patent metadata

Field	Value
Publication number	US-11976786-B2
Application number	US-202017642169-A
Country	US
Kind code	B2
Filing date	Sep 16, 2020
Priority date	Sep 24, 2019
Publication date	May 7, 2024
Grant date	May 7, 2024

Abstract

An oil restrictor for emergency lubrication of a component for an aircraft turbine engine includes a metal cylindrical body having a longitudinal axis and configured to be housed in and shrink-fitted into a cylindrical bore of a part of the turbine engine. The restrictor further includes an integrated oil circuit enabling oil to pass through the restrictor along the axial extent thereof. The body is a one-piece body, and the circuit has at least two oil channels recessed on an outer cylindrical surface of the body and extending around and/or along the axis.

First claim

The invention claimed is:

1. An oil restrictor for the emergency lubrication of a component for an aircraft turbine engine, the restrictor comprising a cylindrical body extending along a longitudinal axis and configured to be housed and shrink-fitted in a cylindrical bore of a part of the turbine engine, the restrictor further comprising an integrated oil circuit configured to provide passage of oil through the restrictor along an axial extent of the restrictor, wherein the body is a one-piece body, and the integrated oil circuit comprises at least two oil channels recessed on a single outer cylindrical surface of the body and extending around and/or along said axis, and wherein said at least two oil channels are independent from each other and remote from each other so as not to communicate directly with one another.

2. The restrictor according to claim 1 , further comprising at least two oil channels extending helically on the single outer surface of the body.

3. The restrictor according to claim 2 , wherein the body comprises first and second opposite longitudinal ends each provided with a longitudinal end face radial to the longitudinal axis, each of the helical channels comprising a first channel end opening at the first longitudinal end of the body and an opposite second channel end in fluid communication with a duct of the body, the duct having a radial orientation with respect to said longitudinal axis and extending between said second channel end and a blind hole formed in a center of the radial face of the second longitudinal end of the body.

4. The restrictor according to claim 3 , further comprising a plurality of ducts each connected to a respective helical channel, the ducts being evenly distributed around said axis.

5. The restrictor according to claim 4 , wherein the ducts open into the blind hole in a first plane which is perpendicular to said longitudinal axis, the first plane being located at a first distance from said radial face of the second longitudinal end of the body, the first distance being less than a second distance between the radial face of the second longitudinal end of the body and a second plane perpendicular to said longitudinal axis and passing through a bottom of the blind hole, and which represents between 30 and 80% of this second distance.

6. The restrictor according to claim 1 , further comprising a first annular row of at least two rectilinear channels parallel to each other and to said longitudinal axis and being regularly distributed around this longitudinal axis.

7. The restrictor according to claim 6 , further comprising at least a second annular row of at least two, rectilinear channels parallel to each other and to said longitudinal axis and being regularly distributed around this axis, the channels of the first row being circumferentially offset around the longitudinal axis with respect to the channels of the second or further row, and the channels of the first row being separated from the channels of the second or further row by an annular groove formed on the single outer surface of the body and extending around said longitudinal axis.

8. The restrictor of claim 7 , wherein said or each annular groove has a depth greater than a depth of said channels of each row.

9. The restrictor according to claim 1 , further comprising straight longitudinal channels parallel to each other, which extend along only part of the length of said body, and circumferential channels connecting the longitudinal channels to each other, with a first and second longitudinal channel opening at an opposite axial end of the body and configured to provide passage of oil through the restrictor along its axial extent.

10. A mechanical reduction gear for a turbine engine, comprising a sun gear, a ring gear extending around the sun gear, and planet gears meshed with the sun gear and the ring gear, said planet gears being guided by plain bearings of a planet carrier, each of the plain bearings comprising an internal cavity supplied with oil and an outer guiding cylindrical surface, each of the plain bearings further comprising oil passage orifices extending from said cavity to said outer guiding cylindrical surface, as well as at least one bore extending from said cavity to said outer guiding cylindrical surface and in which is housed and shrink-fitted a restrictor according to claim 1 .

11. A turbine engine, comprising at least one restrictor according to claim 1 .

12. A turbine engine, comprising a mechanical reduction gear according to claim 10 .

13. An oil restrictor for the emergency lubrication of a component for an aircraft turbine engine, the restrictor comprising a cylindrical body extending along a longitudinal axis and configured to be housed and shrink-fitted in a cylindrical bore of a part of the turbine engine, the restrictor further comprising an integrated oil circuit configured to provide passage of oil through the restrictor along an axial extent of the restrictor, wherein the body is a one-piece body, and the integrated oil circuit comprises at least two oil channels recessed on an outer cylindrical surface of the body and extending around and/or along said axis,
wherein the body comprises first and second opposite longitudinal ends each provided with a longitudinal end face radial to the longitudinal axis, each of the oil channels comprising a first channel end opening at the first longitudinal end of the body and an opposite second channel end in fluid communication with a duct of the body, the duct having a radial orientation with respect to said longitudinal axis and extending between said second channel end and a blind hole formed in a center of the radial face of the second longitudinal end of the body.

Assignees

• Safran Trans Systems

Inventors

• Dombek Alexis Claude Michel
• Gedin Patrice Jocelyn Francis

Classifications

• F16C2360/23

  Gas turbine engines · CPC title

• F16C2326/43

  Aeroplanes; Helicopters · CPC title

• F16C17/24

  with devices affected by abnormal or undesired positions, e.g. for preventing overheating, for safety · CPC title

• F16C33/105

  Conditioning, e.g. metering, cooling, filtering · CPC title

• F16C17/02

  for radial load only · CPC title