Assembly for controlling variable pitch blades

Patent metadata

Field	Value
Publication number	US-11015477-B2
Application number	US-201916448680-A
Country	US
Kind code	B2
Filing date	Jun 21, 2019
Priority date	Jun 22, 2018
Publication date	May 25, 2021
Grant date	May 25, 2021

Abstract

An assembly for the control of variable pitch blades. The assembly includes a movable part movable parallel to an axis is in engagement with pivot connections which rotate about at least one radial axis fixed with respect to the casing, and which act on a radial shaft, which passes through a clevis fixed with a control ring to rotate with it about said axis. The radial shaft is mounted radially rotating with respect to the control ring and the casing.

First claim

The invention claimed is:

1. An assembly for controlling variable pitch blades in a turbo-engine of an aircraft, the assembly comprising:
a control ring:
surrounding a casing of the turbo-engine arranged about a longitudinal axis of the turbo-engine, and
connected by connecting rods to the variable pitch blades, which each pivot about a first radial axis which is radial to said longitudinal axis, and

a device for driving the control ring, rotating about said longitudinal axis and translating parallel to said longitudinal axis,

wherein the device for driving the control ring comprises an actuator having:
a fixed part fixed to the casing, and
a movable part movable parallel to said longitudinal axis, grooved, via a grooved rod, and in engagement with pivot connections:
which each rotates about a respective second radial axis fixed with respect to the casing and radial to said longitudinal axis,
and which each acts on a radial shaft, which radial shaft passes through a clevis fixed with the control ring to rotate with the control ring about said longitudinal axis, the second radial shaft being mounted radially rotatable with respect to the control ring and the casing,

so that a movement of the actuator parallel to said longitudinal axis acts on the pitch of the blades, by actuating the pivot connections, rotation of the radial shafts, rotation of the connecting rods, rotation of the control ring.

2. The assembly according to claim 1 , wherein the movable part of the actuator is movable exclusively in translation and has a succession of said grooves perpendicular to said longitudinal axis.

3. The assembly according to claim 1 , wherein the movable part is in gear engagement with the pivot connections.

4. The assembly according to claim 3 , wherein the pivot connections with which the movable part of the actuator is in gear engagement respectively comprise a secondary connection having a toothed sector head meshing with the grooves of the movable part.

5. The assembly according to claim 1 , wherein the pivot connections respectively comprise at least two secondary connecting rods articulated to each other about said respective second radial axis fixed with respect to the casing.

6. The assembly according to claim 1 , further including:
a first rigid casing surrounding the movable part of the actuator, and
a lubricant contained in said first rigid casing.

7. The assembly according to claim 6 , wherein:
the lubricant lubricates the engagement of the pivot connections with the moving part of the actuator, and
said assembly further comprises at least a second protective casing surrounding said engagement and interposed between said engagement and an external environment, the second protective casing containing a sealing bellows that insulates said engagement from the external environment.

8. A turbo-engine comprising the assembly according to claim 1 , wherein:
the casing surrounded by said at least one control ring is a high pressure casing which surrounds a high pressure compressor of the turbo-engine,
the turbo-engine further comprises an intermediate casing arranged adjacent to the high-pressure casing to which the intermediate casing is coaxially attached, and
the fixed part of the actuator is fixed to an outer surface of the intermediate casing.

9. The turbo-engine according to claim 8 , wherein:
the turbo-engine further comprises a first rigid casing surrounding the movable part of the actuator, and a lubricant contained in said first rigid casing, and
the fixed part of the actuator is fixed to said outer surface of the intermediate casing through said first rigid casing which has axial ends where the first rigid casing is fixed respectively to said fixed portion of the actuator and to said outer surface of the intermediate casing.

10. The assembly according to claim 1 , wherein the actuator is an active actuator, which includes a cylinder.

Assignees

• Safran Aircraft Engines

Inventors

• Lagarde Romain Nicolas
• Dumas Lilian Yann

Classifications

• F05D2250/241

  spherical · CPC title

• F04D29/563

  specially adapted for elastic fluid pumps · CPC title

• F04D29/56

  adjustable · CPC title

• F05D2220/323

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

• F05D2260/50

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