Safran Aircraft Engines

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

Snecma

Claude Dejaune

Bruno Albert Beutin

Jean-Louis Charbonnel

Valerie Annie Gros

Andre C Collot

Alexandre Tan-Kim

Monique A Thore

Benjamin Petard

Philippe Fessou

Julien Foll

Daniel J Martin

Cyril Douady

Stephane Bois

Herve Paitre

Jean-Claude Gregoire

Alain Espenel

Arnaud Accary

Benjamin Kiener-Calvet

Jean-Francois Ranvier

Stéphane Bois

An anti-vibration device for the machining of a shaft includes a first fixed ring intended to be kept inside a shaft by a shoulder, the anti-vibration device including: at least one first external groove and at least one first external seal for forming at least one contact with the internal surface of the shaft; at least one first internal circumferential groove and at least one first internal seal for forming at least one contact with the external surface of the bar; an internal circumferential cavity that is able to cause the circulation of a fluid arriving through a first duct and leaving through a second duct, the first duct and second duct passing through the radial thickness of the anti-vibration device, the internal circumferential cavity making it possible to realize a vibration-damping function when a fluid passes through it.

Shaft machining anti-vibration device

A fan disk is for a jet engine in which there flows a gas stream in a flow direction. A pin-shaped radial section of the fan disk includes a first branch, designed to be fixed to a drive shaft of the jet engine, a second branch, extending opposite the first branch and designed to support a plurality of fan blades, and a curved junction wall that extends between the first branch and the second branch.

Fan disk for a jet engine and jet engine

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

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Boissise la Bertrand, France

Claude Dejaune