Variable-pitch vane

Patent metadata

Field	Value
Publication number	US-10415404-B2
Application number	US-201414771787-A
Country	US
Kind code	B2
Filing date	Feb 27, 2014
Priority date	Mar 1, 2013
Publication date	Sep 17, 2019
Grant date	Sep 17, 2019

Abstract

A variable-pitch vane including a plurality of propeller blades ( 2 ). Each blade has a variable pitch according to a blade rotational axis (A 1 ) and a root ( 201 ). A plurality of rotor connecting shafts ( 6 ), each shaft having a foot ( 602 ) and a head ( 601 ). The root ( 201 ) of each blade is mounted on the head ( 601 ) of a rotor connecting shaft via a pivot ( 8 ) in such a way as to allow each blade ( 2 ) to rotate according to the blade rotational axis (A 1 ), in which each blade ( 2 ) has a blade pitch, such that the blade rotational axis (A 1 ) is inclined relative to a radial axis (A 2 ) passing through the foot ( 602 ) of the corresponding shaft.

First claim

The invention claimed is:

1. Variable-pitch blading including:
a plurality of propeller blades, each with variable pitch about a blade axis of rotation (A 1 ) and each having a root,
a plurality of rotor connecting shafts, each shaft having a root and a head, the root of each blade being assembled on the head of a rotor connecting shaft via a pivot so as to allow rotation of each blade about the blade axis of rotation (A 1 ),

wherein each blade has a blade inclination such that its blade axis of rotation (A 1 ) is inclined with respect to a radial axis (A 2 ) running through the root of the corresponding shaft, and in that the inclination of the blade includes a tangent inclination component (β) in a plane of a propeller.

2. The blading according to claim 1 , wherein a tangential inclination angle toward an extrados is comprised between 5 and 15°.

3. The blading according to claim 1 , wherein the blade inclination includes an upstream or downstream inclination component with respect to the plane of the propeller.

4. The blading according to claim 3 , wherein the upstream inclination component is between 0 and 2°.

5. The blading according to claim 1 , wherein each shaft is inclined with respect to the radial axis (A 2 ), inclining the corresponding blade by the blade inclination.

6. The blading according to claim 1 , wherein the head of each shaft has an articulation inclining the head of the shaft with respect to the rest of the shaft, and thus inclining the corresponding blade by the blade inclination.

7. The blading according to claim 6 , wherein the articulation includes a bellows.

8. The blading according to claim 6 , wherein the articulation includes a universal joint.

9. A turbomachine including a blading according to claim 1 .

10. A turbomachine including two counter-rotating variable-pitch bladings, each according to claim 1 .

Assignees

• Snecma
• Safran Aircraft Engines

Inventors

• Fabre Adrien
• Laurenceau Adrien
• Vlastuin Jonathan

Classifications

• F05D2260/74

  by turning around an axis perpendicular the rotor centre line · CPC title

• B64D2027/005

  Aircraft with an unducted turbofan comprising contra-rotating rotors, e.g. contra-rotating open rotors [CROR] · CPC title

• B64C11/36

  non-automatic · CPC title

• F01D5/12

  Blades ({specially adapted for radial flow machines or engines F01D5/04}; blade roots F01D5/30; rotors with blades adjustable in operation F01D7/00; stator blades F01D9/02) · CPC title

• F01D7/00 Primary

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