Stationary actuator device for controlling the pitch of fan blades of a turboprop

Patent metadata

Field	Value
Publication number	US-9284041-B2
Application number	US-201013375024-A
Country	US
Kind code	B2
Filing date	Apr 16, 2010
Priority date	May 29, 2009
Publication date	Mar 15, 2016
Grant date	Mar 15, 2016

Abstract

A device for controlling pitch of fan blades of a turboprop including at least one set of variable-pitch fan blades constrained to rotate with a rotary ring centered on a longitudinal axis and mechanically connected to a turbine rotor, each blade coupled for pitch adjustment to a synchronization ring. A turntable is mounted via a rotary connection to a rod of an actuator that is secured to a stationary structural element of the turboprop, the turntable being mechanically connected to the synchronization ring by a plurality of connection arms hinge-mounted on the turntable and connected to the synchronization ring such that a longitudinal movement of the turntable under drive from the actuator causes the synchronization ring to turn about the longitudinal axis.

First claim

The invention claimed is:

1. A device for controlling pitch of fan blades of a turboprop including at least one set of variable-pitch fan blades, the set being constrained to rotate with a rotary ring centered on a longitudinal axis and mechanically connected to a rotor of a turbine, each blade of the set being coupled for pitch adjustment to a synchronization ring centered on the longitudinal axis, the device comprising:
an actuator centered on the longitudinal axis and secured to a stationary structural element of the turboprop, the actuator including a rod movable along the longitudinal axis;
a turntable which is mounted at a center thereof on the rod of the actuator via a rotary connection such that the turntable is rotatable about the longitudinal axis while the rod of the actuator remains stationary in rotation;
a plurality of connection arms which mechanically connect the turntable to the synchronization ring, each of the connection arms includes an axial link and a radial link, a first end of the axial link is fastened to the turntable via a first connection which pivots about a first tangential axis, a second end of the axial link is fastened to a first end of the radial link via a second connection which pivots about a second tangential axis, and a second end of the radial link is connected to the synchronization ring, the radial link is stationary in a longitudinal direction;
means for converting the movement of the radial link of each connection arm into turning of the synchronization ring about the longitudinal axis; and
a tangential link having a first end fastened to the second end of the radial link of a connection arm by a connection that pivots about a longitudinal axis, a second end of the tangential link being fastened on a blade root support that is swivel-mounted on the rotary ring and that is connected to the synchronization ring via a drive link,
wherein longitudinal movement of the turntable under drive from the actuator causes the radial link to move in a direction that is substantially radial so as to cause the synchronization ring to turn about the longitudinal axis.

2. A device according to claim 1 , wherein the turntable is mounted on the rod of the actuator by a rolling bearing of ball thrust bearing type.

3. A device according to claim 1 , wherein the connection arms are regularly distributed around the longitudinal axis.

4. A device according to claim 1 , wherein the set of fan blades comprises N blades and the turntable is mechanically connected to the synchronization ring by N/2 connection arms, and N is an even number.

5. A two-propeller turboprop comprising:
a turbine including two contrarotating rotors and two sets of variable-pitch fan blades constrained to rotate with two rotary rings that are connected to respective ones of the rotors, the pitch of the blades of at least one of the sets being controlled by a device according to claim 1 .

6. A device according to claim 1 , wherein the actuator is a hydraulic, electric, or pneumatic actuator which is controlled by a digital engine controller.

7. A device according to claim 1 , wherein the actuator and the turntable are disposed downstream of a combustion chamber of the turboprop.

Assignees

• Belmonte Olivier
• Bosco Franck Emmanuel
• Snecma

Inventors

• Belmonte Olivier
• Bosco Franck Emmanuel

Classifications

• B64D2027/026

  Operations & Transport · mapped topic

• B64C11/32 Primary

  mechanical · CPC title

• F01D7/00

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

• B64C11/48

  Units of two or more coaxial propellers · CPC title

• F05D2260/79

  Bearing, support or actuation arrangements therefor · CPC title