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

Snecma Moteurs

Monique A Thore

Bruno Albert Beutin

Jean-Louis Charbonnel

Andre C Collot

Daniel J Martin

Claude Dejaune

Philippe Fessou

Michel Gilbert Brault

Pascal C Vasseur

Elisabeth Guigli

Jean-Francois Ranvier

Herve Paitre

Pascal Gervais

Jean-Claude Gregoire

Alain Espenel

A spacer ( ) made to be installed between two permanently connected discs ( and ), without a bolted flange, and comprising axial thrust ( ) as well as outer radial thrust ( ) alignment surfaces ( ). It comprises moreover an outer cover ( ) to provide sealing and a cooling passageway, and stiffening tongues ( ) which accommodate thrust loads.

Turbomachine rotor assembly with two bladed-discs separated by a spacer

The arrangement of a gas turbine engine suitable for high bypass ratio aircraft engines in which gases circulate in a primary air channel (7) and a secondary channel (8) concentric to said primary air channel, is characterized in that structural vanes (22) connecting the channel delimitation casings (2, 10, 14, 5) with each other, alternate with aerodynamic vanes (20) for guiding the gases on a common circumference of the engine bypass air channel (8), and in that the structural channels branch out between the two channels. The resulting advantages are simplicity of construction associated with a reduction in the space required for housing the channels and good resistance without notable increase of the total mass.

Arrangement of gas turbine engine comprising aerodynamic vanes and

A turbine engine blade made from a composite material and having at a free end thereof an integrated brush joint. A process for producing such a blade includes the steps of: introducing a fibrous fabric into a mold, introducing specific fibres into the mold, in the vicinity of the free end of the blade, injecting a resin into the mold, performing polymerization by use of a heating press of the resin-impregnated fibrous fabric.

Composite material turbine engine blade equipped with a seal and its

The present invention relates to a monobloc rotor having a disk and hollow blades which are secured to the disk. The disk includes a protuberance and a projection on a periphery of the disk such that the projection forms a block having a shape which approximately corresponds to a shape of an inside of a radially internal extremity of the blade. The present invention further relates to a monobloc rotor in which a block is welded to the protuberance with the block forming a projection having a shape which approximately corresponds to a shape of an inside of a radially internal extremity of the blade.

Method for producing a monobloc rotor with hollow blades and monobloc

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Crosne, France

Monique A Thore