Air propeller blade pivot in the shape of a spherical cap

Patent metadata

Field	Value
Publication number	US-9938000-B2
Application number	US-201414899010-A
Country	US
Kind code	B2
Filing date	Jun 12, 2014
Priority date	Jun 17, 2013
Publication date	Apr 10, 2018
Grant date	Apr 10, 2018

Abstract

A pivot for an air propeller blade, the pivot including a rotary support for mounting radially on a propeller hub while being suitable for pivoting about a pivot axis; and a blade support including a housing for receiving a blade root and at least one arm extending laterally relative to the pivot axis and carrying a flyweight forming a counterweight; the arm and its flyweight presenting the general geometrical shape of a spherical cap.

First claim

The invention claimed is:

1. A pivot for an air propeller blade, the pivot comprising:
a rotary support for mounting radially on a propeller hub while being suitable for pivoting about a pivot axis; and
a blade support including a housing for receiving a blade root and an arm extending laterally relative to the pivot axis and carrying a flyweight forming a counterweight,
wherein the arm and the flyweight present the general geometrical shape of a spherical cap facing the rotary support with a double curvature, the arm and the flyweight having a first section that is curved in a longitudinal plane defined by the pivot axis and a direction in which the arm extends, and having a second section that is curved in a transverse plane defined by the pivot axis and a direction in which the housing extends.

2. The pivot according to claim 1 , wherein the arm and its flyweight have a section that is curved in a longitudinal plane and a section that is curved in a transverse plane.

3. The pivot according to claim 1 , wherein each of the first and second sections presents a respective radius of curvature lying in the range 200 mm to 400 mm for a propeller blade of a turboprop having a single propeller, and lying in the range 700 mm to 900 mm for a propeller blade of a turboprop having two contrarotating propellers.

4. The pivot according to claim 1 , wherein at least the blade support is made of organic matrix composite material.

5. The pivot according to claim 1 , wherein the blade support comprises two opposite arms extending laterally relative to the pivot axis and each carrying a flyweight forming a counterweight.

6. The pivot according to claim 1 , wherein the blade support arm is connected to the housing via a portion of curved profile.

7. The pivot according to claim 1 , wherein the blade support arm is connected to the housing via a portion of rectilinear profile.

8. The pivot according to claim 1 , wherein the blade support housing is a socket oriented in a direction that is substantially perpendicular to the arm.

9. An air propeller comprising a plurality of blades, each mounted in a pivot according to claim 1 .

10. An aircraft turboprop including at least one propeller according to claim 9 .

Assignees

• Snecma

Inventors

• Tajan Sebastien
• Fabre Adrien Jacques Philippe
• Jacquemard Christophe
• Laurenceau Adrien

Classifications

• B64C11/06

  for variable-pitch blades · CPC title

• F04D29/323

  adjustable · CPC title

• F04D29/366

  Adjustment by interaction of inertion and lift · CPC title

• B64C11/346 Primary

  actuated by the centrifugal force or the aerodynamic drag acting on auxiliary masses or surfaces · CPC title

• B64D2027/005

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