Safran Aircraft Engines

Snecma

Sebastien Emile Philippe Tajan

Anthony Lafitte

Charles-Henri Michel Marie Derrez

Cyril Roger Yves Le Pecheur

Emmanuel Pierre Dimitri Patsouris

Michel Gilbert Roland Brault

Gilles Alain Charier

Adrien Jacques Philippe Fabre

Christophe Paul Jacquemard

Arnaud Nicolas Negri

Nathalie Nowakowski

Romain Guillaume Cuvillier

Guillaume Patrice Kubiak

Nils Edouard Romain Bordoni

Denis Louis Bocquet

Sarah Chartier

Caroline Adeline Herauville

A fan of a turbine engine includes a disc provided with blades at the periphery thereof, the blades being mounted so as to pivot on the disc about a pivot axis, and a mechanism for changing the pitch of the blades. The mechanism is configured to adjust an angular position of each blade around the pivot axis. The angular position is in an angular setting range no greater than 20&#xb0;.

Low-pitch variable-setting fan of a turbine engine

A device for locking the pitch and for feathering adjustable-pitch fan blades of a turbine engine propeller, the device including an actuator having at least one movable portion designed to be coupled to pivots of the fan blades of the propeller in order to modify their pitch angle when it slides, a movable part having first mechanical device suitable for co-operating with the actuator when in a fan blade pitch-unlocking position in order to enable the actuator movable portion to slide over an extended actuator stroke; and second mechanical device suitable for co-operating with the actuator when in a fan blade pitch-locking position in order to enable the actuator movable portion to slide over an actuator stroke that is shorter than the extended actuator stroke, and an actuator.

Device for locking the pitch and for feathering adjustable-pitch fan blades of a turbine engine propeller

The invention relates to a propeller ring () of a turbomachine (), with variable-pitch blades (P), the propeller ring () comprising a substantially coaxial annular body () with a main axis (A) and a plurality of radial housings () uniformly distributed around the main axis (A), each radial housing () being designed to receive a bearing () for a root () of a blade (P) so as to allow the variable pitch of the blade (P), the radial housings () having a substantially ovoid cross-section in a plane (T) tangential to the annular body ().

Propeller ring comprising radial housings with an ovoid cross-section

The invention relates to a hub for an unducted propeller () having variable-pitch blades () of a turbine engine, comprising two parallel annular side walls () between which are arranged rings () which are distributed angularly in a regular manner around a longitudinal axis (A) of the hub, which are connected to the annular side walls (), and which comprise compartments () receiving bearings () having radial axes (R) for guiding in rotation roots () of blades of said propeller, said rings () being connected in pairs by connection means () which are arranged between the annular side walls () and which comprise substantially radial reinforcing partitions (), characterised in that at least some of said reinforcing partitions () are connected to said annular side walls ().

Stiffened hub for unshrouded propeller

A propeller ring of a turbomachine including an annular body substantially coaxial to a principal axis and a plurality of radial housings uniformly distributed about the principal axis, each radial housing being configured to receive a root of a blade, the annular body being made of composite material including a fibrous reinforcement densified by a polymer matrix and further including a plurality of metallic inserts configured to each receive the root of a blade, said metallic inserts being anchored in the composite material of the annular body.

Propeller ring made of composite material for a turbomachine

The present invention relates to a propulsion unit comprising a pair of contra-rotating coaxial propellers, that are referred to as upstream () and downstream (), the downstream propeller, forming a rotating reference frame, being mounted for rotation about a central member forming a stationary reference frame, and being provided with a device for changing the pitch of the blades, characterized in that the downstream propeller is supported by bearings arranged externally on the cylindrical central support, an upstream bearing () of which is arranged downstream of a device for changing the pitch of the blades of the upstream propeller, and in that said device for changing the pitch of the downstream propeller comprises a linear actuator () in the stationary reference frame with an element () that is able to move axially along the axis of the downstream propeller, the upstream bearing comprising an inner ring that is rigidly connected to the linear actuator and an outer ring that is rigidly connected to a rotating casing () of the downstream propeller, and a movement-transmission mechanism () connecting said movable element of the linear actuator to the blades, comprising a load-transfer bearing arranged to transmit the axial forces from the linear actuator to the rotating reference frame of the downstream propeller.

Propulsion unit with a pair of propellers for an aircraft

A control device of the pitch of blades of a rotor of a propeller is provided. The control device includes: a radial shaft; a pivot connected to the blade, the rotation of the radial shaft driving the rotation of the pivot for the modification of the pitch of the blade; an insert fixed rigidly to the pivot so as to block their relative displacement, the radial shaft being configured to drive in rotation the insert; at least one peg passing through the insert and the pivot for transmission of the rotation of the insert to the pivot; and a heat insulation element arranged between the insert and the pivot, whereof the thermal conductivity is less than the thermal conductivity of the pivot and of the radial shaft.

Growing community of inventors

Moissy-Cramayel, France

Sebastien Emile Philippe Tajan