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

Francois M Marlin

Gerard E Jourdain

Georges Mazeaud

Francois J Mirville

Ollivier Carletti

Philippe Jean-Pierre Pabion

Gerard Francedillaois Inizan

Christine J Ruffier

Josiane M Labatut

Laurence Prato

Thierry G Pancou

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 propulsion system for a reusable spacecraft is disclosed having turbojet, amjet and rocket modes of operation. Hydrogen or exhaust gases from a gas generator drives a gas turbine which powers an air compressor in the turbojet mode. An injection device injects hydrogen and exhaust from the gas driven turbine in the combustion chamber in the turbojet mode. In the ramjet mode, only hydrogen is injected into the combustion chamber. In the ramjet mode, hydrogen and oxygen are supplied to the rocket motor. An adjustable nozzle is provided to form a variable throat convergent-divergent nozzle in the turbojet and ramjet modes and to form a divergent nozzle in the rocket mode.

Combination turbojet-ramjet-rocket propulsion system

A bladed disc of a turbomachine rotor comprising an array of blades evenly disposed around the rim of the disc and separate platforms secured to the disc between the blades, each platform comprising a plate and a mounting foot at each axial end of the plate by which the platform is secured to the rim of the disc, at least one of the feet being secured by a C-shaped clamp which rigidly connects the foot to a tooth-like element of the disc adjacent the rim and which is locked axially in position by a flange of an adjacent element of the rotor.

Bladed disc for a turbomachine rotor

Growing community of inventors

Melun, France

Francois M Marlin