Assembly for controlling variable pitch blades

Patent metadata

Field	Value
Publication number	US-2019390563-A1
Application number	US-201916448680-A
Country	US
Kind code	A1
Filing date	Jun 21, 2019
Priority date	Jun 22, 2018
Publication date	Dec 26, 2019
Grant date	—

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

1 . An assembly for controlling variable pitch blades in an aircraft gas turbo-engine, the assembly comprising:
at least one control ring:
surrounding a casing of the turbo-engine arranged about an axis of the turbo-engine, and
connected by rods to the variable pitch blades, which each pivot about a radial axis to said axis of the turbo-engine, and
a device for driving the control ring, rotating about said axis and translating parallel to said axis,
characterized in that the device for driving the control ring comprises an active actuator, which is a cylinder, having:
a fixed part fixed to the casing, and
a movable part movable parallel to said axis, grooved, via a grooved rod, and in engagement with pivot connections:
which rotate between them 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 the control ring to rotate with it about said axis, the 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 axis acts on the pitch of the blades, by actuating the pivot connections, rotation of said radial shaft, 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 axis of the turbo-engine.

3 . The assembly according to claim 1 , in which 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 comprise a secondary connection having a toothed sector head meshing with the grooves of the movable part.

5 . The assembly according to claim 1 , in which the pivot connections comprise at least two secondary connecting rods articulated to each other about a said 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 lubricant ( 57 ) contained in said first 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 lubricated assembly, the second casing containing a sealing bellows that insulates said lubricated assembly from the outside.

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 it 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 fixed part of the actuator is fixed to said outer surface of the intermediate casing through said first rigid casing which is fixed at its axial ends on one side to said fixed portion of the actuator and on the opposite side to said outer surface of the intermediate casing.

Assignees

• Safran Aircraft Engines

Inventors

• Lagarde Romain Nicolas
• Dumas Lilian Yann

Classifications

• F01D5/30

  Fixing blades to rotors; Blade roots {; Blade spacers} · CPC title

• F04D29/56

  adjustable · CPC title

• F04D29/362

  during rotation · CPC title

• F01D7/00

  Rotors with blades adjustable in operation; Control thereof (for reversing F01D1/30) · CPC title

• F01D5/02

  Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28}) · CPC title