Safran Aircraft Engines

Clement Cottet

Regis Eugene Henri Servant

Thierry Georges Paul Papin

Laurent Jablonski

Vincent Joudon

Christophe Marcel Lucien Perdrigeon

Vivien Mickael Courtier

Mathias Gautier

A propeller for an aircraft turbomachine, the propeller having; a hub extending around a first axis including openings distributed around the first axis, each of the openings having a substantially radial orientation relative to the first axis and extending through the hub, a system for controlling the angular setting of a blade which is mounted in each of the openings, and bearings for guiding the control system, which are mounted in each of the openings, the guide bearings including two guide bearings, one of which includes two annular rows of angular contact coaxial balls having different diameters.

Propeller for an aircraft turbomachine

A system for changing the pitch of the blades of a turbomachine propeller, each blade being mounted so as to pivot about a pitch axis, the system including a control means and a connection mechanism connecting the control means to each blade of the propeller, the connection mechanism including, for each blade of the propeller: —a connecting rod having a first end connected to the control means; and —an eccentric having a first end connected to the blade in order to rotate same about its pitch axis and a second end forming a yoke connected to a second end of the connecting rod by a pivot connection; the yoke of the eccentric being oriented towards the pitch axis of the blade.

System for changing the pitch of the blades of a turbomachine propeller

An assembly comprising a propeller blade and its system for angularly adjusting the pitch of the blade including a bowl which is radially delimited by an annular wall extending about an axis for adjusting the pitch of the blade, the bowl having a bottom wall, a free lower end of the root being fitted axially into a complementary housing of the bottom wall in order to rotatably connect the bowl and the blade about the pitch-adjustment axis. The root of the blade comprises a first limiting face that engages with a first abutment face of the bowl to limit the rotation of the blade in the event of breakage of the lower end of the root.

Aircraft turbine engine comprising variable-pitch propeller blades

The invention relates to a turbomachine module (), comprising: &#x2014;a rotating housing (-) supporting a propeller provided with a plurality of blades (), &#x2014;a system for varying the pitch of the propeller blades (), the system comprising a control means, and a mechanism for varying the pitch of the propeller blades, characterised in that the system is supported by the rotary housing (-), in that the control means comprise an annular row of rotary actuators (), and in that the mechanism for varying the pitch of the blades comprises a synchronisation ring () that is driven to rotate by rotary output shafts () of the actuators (), the synchronisation ring () being guided in rotation relative to the rotary housing (-) by guide means and meshed by a first toothing () with pinions () of the blades ().

Turbomachine module for a propeller having variable-pitch blades and turbomachine comprising same

The invention relates to a module of a turbomachine of longitudinal axis X, the module comprising: &#x22c5;&#x2014;a rotary casing () that rotates about the longitudinal axis and bears a propeller () which is provided with a plurality of blades (); &#x22c5;&#x2014;a fixed casing () comprising a cylindrical wall () extending between an inner wall () and an outer wall () of the rotary casing (); and, &#x22c5;&#x2014;a system () for changing the pitch of the blades of the propeller, mounted around the fixed casing and comprising: a control means () comprising a movable body () that is able to move axially on said fixed casing, at least one load transfer bearing () comprising an inner ring () that is connected to the movable body (), and an outer ring (); and a connection mechanism () for connecting the outer ring () to the blades of the propeller. According to the invention, the module further comprises a feathering device () for feathering the blades of the propeller, this device () comprising an annular row of springs () that are arranged around said fixed casing and extend axially, the springs () comprising first axial ends () that bear against a ferrule () of the fixed casing, and opposite second axial ends () that bear against said inner ring ().

Growing community of inventors

Moissy-Cramayel, France

Clement Cottet