Societe Nationale D'etude Et De Construction De Moteurs D'aviation

Jean-Michel Payen

Gerard E Jourdain

Jean G Bouiller

Marc G Loubet

Philippe Jean-Pierre Pabion

Gerard Francedillaois Inizan

Christine J Ruffier

Jean Pierre Ruis

A separate inter-blade platform for a bladed rotor disk of a turbo-machine comprises a first part in the form of a four-sided frame of generally trapezoidal shape and made of a laminated material, the frame having smaller and larger ends for location on the upstream and downstream sides respectively of the rotor disk, and two lateral sides interconnecting said ends for location between successive blades of the rotor, and a second part made of a relatively flexible and self-adhesive material of the polyurethane type attached to the first part, the second part defining a plate capping the frame over the greater part of its two lateral sides and leaving the smaller and larger end portions free, a portion enclosing the two lateral sides of the frame in line with the plate, and a plurality of evenly spaced, transverse reinforcing ribs which are integral with said enclosing portion and the underside of the plate.

Separate inter-blade platform for a bladed rotor disk

An adjustable two-dimensional nozzle is disclosed in which simplified control means are located away from the flow of gasses through the nozzle. The nozzle includes a movable frame located outside of fixed sidewalls and has pivotally attached thereto a pair of upstream or converging nozzle flaps. Upstream edges of the upstream flaps are attached to the movable frame such that the flaps pivot about axes extending substantially perpendicular to the longitudinal axis of the nozzle. Downstream or diverging flaps are attached to the downstream edges of the upstream flaps such that these flaps also pivot about axes extending substantially perpendicular to the longitudinal axis of the nozzle. A cam member extends between each of the movable frames and each downstream flap to control the angular variations of the flaps during movement of the frame. The flap arrangements are symmetrically arranged with respect to a plane passing through the longitudinal axis of the nozzle, such that translational movement of the frames will alter the cross-section of the nozzle in a symmetrical manner with respect to the plane. If the frame is rotated about its pivot attachment, the nozzle flaps will be asymmetrically adjusted and may be utilized to vector the thrust of the gasses emanating from the nozzle.

Adjustable two dimensional nozzle for aircraft jet engines

A carrier ring for a large diameter propeller system fabricated from a composite material having metallic blade mounting insert members in which are fastened roots of the propeller blades. The carrier ring has an annular ring member formed of a composite material which defines a plurality of radially extending openings, in which openings metallic blade mounting insert members are attached. The blade mounting insert members are retained in assembled relationship with the composite annular ring member by one or more fastening belts which extend around the circumference of the annular ring member in one or more grooves defined by the blade mounting inserts. The fastening belts may be formed by a plurality of turns of a fibrous filament, such as carbon filaments, so as to provide the necessary strength to retain the metallic blade mounting inserts in the composite annular ring member.

Carrier ring for a propeller blade system

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Le Mee sur Seine, France

Jean-Michel Payen