Assembly for controlling variable pitch vanes in a turbine engine

Patent metadata

Field	Value
Publication number	US-10502087-B2
Application number	US-201715645504-A
Country	US
Kind code	B2
Filing date	Jul 10, 2017
Priority date	Jul 12, 2016
Publication date	Dec 10, 2019
Grant date	Dec 10, 2019

Abstract

An assembly for controlling variable pitch vanes in a turbine engine, the assembly comprising an actuating ring surrounding a casing of the turbine engine and connected by rods to variable pitch vanes. The actuating ring is configured to rotate around the casing. The assembly further includes a passive element including a first end sliding connected to a second end. The first end is connected by a sliding pivoting link on the actuating ring, and the second end is connected by a ball-joint link to the casing.

First claim

The invention claimed is:

1. An assembly for controlling variable pitch vanes in a turbine engine, the assembly comprising:
an actuating ring surrounding a casing of the turbine engine and connected by rods to variable pitch vanes;
driving means for rotating the actuating ring around the casing; and
a passive element including a first end slidingly connected to a second end, wherein the first end of the passive element is connected by a sliding pivoting link on the actuating ring, and wherein the second end of the passive element is connected by a ball-joint link to the casing.

2. The assembly of claim 1 , wherein the passive element is arranged circumferentially substantially opposite the driving means of the actuating ring.

3. The assembly of claim 1 , wherein the passive element comprises a body bearing the first end and in which a pin bearing the second end is mounted for translational movement.

4. The assembly of claim 1 , wherein the first end of the passive element is mounted for rotation and translational movement around and according to a radial axis in a yoke of a first support element integral with the actuating ring.

5. The assembly of claim 4 , wherein the second end of the passive element is connected via the ball-joint link to a second support element integral with the casing.

6. The assembly of claim 5 , wherein the first support element is arranged axially downstream, or upstream respectively, from the rods and the second support element is arranged upstream, or downstream respectively, from the rods.

7. The assembly of claim 1 , wherein the second end of the passive element is connected via a flange of the casing.

8. The assembly of claim 1 , wherein the passive element is a braking cylinder.

9. The assembly of claim 8 , wherein the braking cylinder is a gas cylinder or a spring loaded cylinder.

10. A turbine engine comprising the assembly of claim 1 .

11. The assembly of claim 1 , wherein the first end comprises a body of a cylinder, and wherein the second end comprises a pin mounted in the body of the cylinder.

Assignees

• Safran Aircraft Engines

Inventors

• Benderradji Kamel
• Bergon Blaise
• Bromann Alain Marc Lucien
• Coustillas Suzanne Madeleine
• Dumas Lilian Yann

Classifications

• F04D29/563

  specially adapted for elastic fluid pumps · CPC title

• F01D17/162 Primary

  for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line (F01D17/167 takes precedence) · CPC title

• F05D2220/323

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

• F01D17/26

  fluid, e.g. hydraulic · CPC title

• F05D2260/50

  Kinematic linkage, i.e. transmission of position · CPC title