Safran Aircraft Engines

Aircelle Limited

Cyril Roger Yves Le Pecheur

Charles-Henri Michel Marie Derrez

Sebastien Emile Philippe Tajan

Anthony Lafitte

Adrien Jacques Philippe Fabre

Michel Rognant

Caroline Adeline Herauville

Sebastien Marcelino Juste

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

An unducted fan for an aircraft turbine engine, including a propeller having a hub and an annular array of blades extending substantially radially outwards from the hub, is provided. The hub includes an annular array of cowls, each of which is mounted between the radially inner ends of the blades and suitable for being fixed to an upstream collar and to a downstream collar of the hub. At least one cowl includes, at a circumferential end, a joint edge which is contiguous with a complementary joint edge of an adjacent cowl. The at least one cowl and at least one of the upstream and downstream collars are configured so that the cowl can be mounted and dismounted by a movement including a pivoting about an initial pivot axis circumferentially separated from the at least one joint edge.

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Grandvillars, France

Cyril Roger Yves Le Pecheur