Propeller blade pivot

• US 9,896,189 B2
• Filed: 05/16/2014
• Issued: 02/20/2018
• Est. Priority Date: 05/17/2013
• Status: Active Grant

• Current Assignee: Safran Aircraft Engine Company
• Original Assignee: Snecma (Safran SA)
• Inventors: Tajan, Sebastien, Fabre, Adrien Jacques Philippe, Jacquemard, Christophe, Laurenceau, Adrien, Boudier, Romain
• Primary Examiner(s): Murphy, Kevin
• Assistant Examiner(s): Cary, Kelsey
• Application Number:
  US14/279,727
• Publication Number:
  US 20140341739A1
• Time in Patent Office: 1,376 Days
• Field of Search: 416147, 416204 R, 416219 R, 416134 R, 416134 A, 416209, 416205
• CPC Class Codes: B64C 11/06 for variable-pitch blades
• CPC Class Codes: B64C 11/325 comprising feathering, braking or stopping systems
• CPC Class Codes: B64C 11/346 actuated by the centrifugal force or the aerodynamic drag acting on auxiliary masses or surfaces
• CPC Class Codes: B64D 2027/005 Aircraft with an unducted turbofan comprising contra-rotating rotors, e.g. contra-rotating open rotors [CROR]
• CPC Class Codes: F01D 7/02 having adjustment responsive to speed
• CPC Class Codes: F04D 29/366 Adjustment by interaction of inertion and lift
• CPC Class Codes: F05D 2220/323 for aircraft propulsion, e.g. jet engines
• CPC Class Codes: F05D 2260/70 Adjusting of angle of incidence or attack of rotating blades
• CPC Class Codes: F05D 2260/77 the adjusting mechanism driven or triggered by centrifugal forces
• CPC Class Codes: F05D 2260/78 the adjusting mechanism driven or triggered by aerodynamic forces
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

The invention relates to the field of aerial propellers, in particular the field of variable-pitch propellers, specifically for unducted fans. More specifically, the invention relates to a pivot (15) for a blade (14) of a propeller (3a, 3b), the pivot including at least a proximal portion (15a) made of metal and suitable for being retained in a radial orifice of a propeller hub, while being capable of turning in said orifice about a longitudinal axis (Z) of the pivot (15), and a distal portion (15b) including a receptacle (20) suitable for retaining a blade root, and at least one arm (17) of organic matrix composite material extending laterally relative to said longitudinal axis (Z) and supporting a flyweight (16).

Claims

1. A pivot for a blade of a propeller, the pivot comprising:

a proximal portion suitable for being retained in a radial orifice in a propeller hub while being capable of turning in the orifice about a longitudinal axis of the pivot; and

a distal portion including at least one arm extending laterally relative to said longitudinal axis and supporting a flyweight at an end of said at least one arm furthest from said longitudinal axis;

wherein at least said proximal portion is made of metal, at least said at least one arm is made of organic matrix composite material, and a receptacle for retaining a blade root is formed in a metal extension of the proximal portion of the pivot that passes through the distal portion of the pivot and presents a longitudinal section that diverges towards a distal end of the pivot to retain along the longitudinal axis, by interlocking shapes, the distal portion of the pivot.

2. The pivot according to claim 1, wherein said proximal and distal portions are bonded together by adhesive.

3. The pivot according to claim 1, wherein said proximal and distal portions are bonded together by a bolted connection.

4. The pivot according to claim 1, wherein said receptacle is in the form of a dovetail slot extending in a direction that is substantially perpendicular to said at least one arm.

5. The pivot according to claim 1, wherein said distal portion comprises two opposite arms extending laterally relative to said longitudinal axis and each supporting a respective flyweight.