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

Philippe Jean-Pierre Pabion

Gerard E Jourdain

Gerard Francedillaois Inizan

Christine J Ruffier

Pascal Noel Brossier

Ollivier Carletti

Francois M Marlin

Jean-Michel Payen

Laurence Prato

Thierry G Pancou

A thrust reverser is disclosed for a high bypass ratio turbofan jet engine having a fan cowling forming an outer boundary of an airflow duct and a jet engine structure including a jet engine cowling. The thrust reverser has a casing affixed to the jet engine structure, the casing having a plurality of attaching yokes. A first thrust reverser flap is pivotally connected to a corresponding one of the attaching yokes and is located rearwardly of an exit of the airflow duct, each first thrust reverser flap having a distal end and being movable between a forward thrust position, and a reverse thrust position. A second thrust reverser flap is pivotally connected to the distal end of a corresponding one of the first thrust reverser flaps and is also movable between a forward thrust position, and a reverse thrust position, wherein the second thrust reverser flaps also redirect air flow emanating from the air flow duct. A linkrod connected to a corresponding one of the second thrust reverser flaps and the corresponding attaching yoke moves the second thrust reverser flap between its forward and reverse thrust positions as the corresponding first thrust reverser flap is moved between its forward and reverse thrust positions.

Thrust reverser for a high bypass turbofan engine

A separate inter-blade platform for a turbomachine rotor comprises a structural rectilinear longitudinal member formed by a foam core, plies of a carbon/epoxy type material in bidirectional layers of crossed fibres oriented at 45.degree. laid around the core and around an insert at each end of the longitudinal member, each insert being made of juxtaposed radial plies of a carbon/epoxy type material in bidirectional layers of fibres crossed at .+-.45 degrees, and further plies of a carbon/epoxy type material in unidirectional layers oriented in the direction of the major axis of the longitudinal member covering the upper and lower faces of the member, the platform further comprising lateral packing cores made of a foam material, plies of a glass/epoxy type material covering the lateral faces of the longitudinal member and connecting it to the lateral foam cores, and peripheral plies of a glass/epoxy type material covering the assembly formed by the longitudinal member and the lateral cores connected thereto.

Inter-blade platform for a bladed disc of a turbomachine rotor

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

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Le Mee S/Seine, France

Philippe Jean-Pierre Pabion