Oil transfer for a control system regulating the propeller pitch of a turbine engine

Patent metadata

Field	Value
Publication number	US-11021235-B2
Application number	US-201816168675-A
Country	US
Kind code	B2
Filing date	Oct 23, 2018
Priority date	Oct 24, 2017
Publication date	Jun 1, 2021
Grant date	Jun 1, 2021

Abstract

Oil transfer tube for a system to control the regulation of a turbine engine propeller pitch, in particular of an aircraft, the tube being intended to be mounted coaxially inside a tubular shaft of the propeller, the tube having an elongated shape and including a first male longitudinal end part intended to be inserted in a female housing of a stator casing equipped with an oil supply circuit of the tube, and a second male longitudinal end part around which is intended to be mounted a hydrodynamic bearing to guide the tube in the shaft, wherein the first end part includes a free annular end with a convex rounded cross-section intended to bear axially against an annular bottom of said housing, and in that said second end part comprises an outer axial annular bearing surface of an inner ring of the bearing, the annular bearing surface presenting in cross-section a convex curved shape.

First claim

The invention claimed is:

1. An oil transfer tube for a system to control regulation of a turbine engine propeller pitch of an aircraft, said turbine engine propeller having a rotational axis A, the tube being intended to be mounted coaxially inside a tubular shaft of the turbine engine propeller, the tube having an elongated shape and comprising a first male longitudinal end part intended to be inserted in a female housing of a stator casing equipped with an oil supply circuit of the tube, and a second male longitudinal end part around which is intended to be mounted a hydrodynamic bearing to guide the tube in the shaft,
wherein said first male longitudinal part comprises a free annular end comprising an outer peripheral surface shaped as a spherical portion and having a convex rounded cross-section in a plane passing through said rotational axis A, said free annular end being intended to bear axially against an annular bottom of said housing to form a ball-joint connection between the first male longitudinal part and the casing, and in that said second male longitudinal end part comprises an outer axial annular bearing surface of an inner ring of said bearing shaped as a spherical portion, and comprising an annular surface having a cross-section with a convex curved shape in a plane passing through said rotational axis A and intended to bear against an annular surface of an upstream end of aa-said inner ring of the bearing to form another ball-joint connection between said second male longitudinal end part and the bearing.

2. The oil transfer tube according to claim 1 , wherein the first male longitudinal end part comprises an outer annular groove housing an O-ring seal, this seal being intended to cooperate with a wall of said housing.

3. The oil transfer tube according to claim 1 , wherein the second male longitudinal end part comprises an outer annular groove housing an O-ring seal, this seal being intended to cooperate with said inner ring of said bearing.

4. The oil transfer tube according to claim 1 , wherein said annular bearing surface is formed by an outer annular edge of the tube.

5. A control system for regulating the pitch of a turbine engine propeller of an aircraft, comprising the oil transfer tube according to claim 1 .

6. A turbine engine of an aircraft, comprising the turbine engine propeller rotationally driven by the tubular shaft and the control system to regulate the pitch of said turbine engine, said system comprising the oil transfer tube according to claim 1 , which is mounted coaxially with respect to the inside of the shaft, a first end part of the oil transfer tube being inserted in the female housing of the stator casing equipped with the oil supply circuit of the oil transfer tube, and a second end part of the oil transfer tube being inserted in the hydrodynamic bearing guiding the oil transfer tube in the shaft.

7. The turbine engine according to claim 6 , wherein said housing comprises a frustoconical annular bottom bearing the free end of said first part.

8. The turbine engine according to claim 6 , wherein said bearing comprises an inner ring mounted on said second part and comprising a free end comprising an annular surface with a concave curved cross-section against which said annular bearing surface comes to bear.

9. The turbine engine according to claim 8 , wherein said annular surface presents a cross-section with a radius of curvature (R 2 ) that is greater than the radius of curvature (R 1 ) of the cross-section of said annular bearing surface.

Assignees

• Safran Trans Systems

Inventors

• Hert Xavier Paul Lucien
• Moreau De Lizoreux Aldric Renaud Gabriel Marie
• Morelli Boris Pierre Marcel

Classifications

• F05D2240/63

  Glands for admission or removal of fluids from shafts · CPC title

• F01D25/183

  Sealing means · CPC title

• F05D2260/406

  through hydraulic systems · CPC title

• F05D2260/79

  Bearing, support or actuation arrangements therefor · CPC title

• F05D2270/64

  Hydraulic actuators · CPC title