Snecma

Snecma Moteurs

Olivier Michael Molinari

Dominique Coupe

Bruno Dambrine

Regis Eugene Henri Servant

Bruno Jacques Gerard Dambrine

Georges Jean Xavier Riou

Son Le Hong

Francois Marie Paul Marlin

Antoine Phelippeau

Philippe Verseux

Patrick Charles Georges Morel

Jacques Michel Albert Julliard

Patrick Morel

Jacques Michel Julliard

Regis Eugene Servant

Jacques Julliard

A composite material casing of varying thickness, in particular for a gas turbine fan, is made by forming fiber reinforcement and densifying the reinforcement with a matrix. The fiber reinforcement is made by winding superposed layers of a fiber texture onto a mandrel, the texture being made by three-dimensional weaving with varying thickness.

Method of manufacturing a gas turbine casing out of composite material, and a casing as obtained thereby

A twin fan turbomachine with two contrarotating fans, one upstream and one downstream, driven by two contrarotating coaxial shafts each of which connects one fan impeller to at least one low-pressure turbine impeller located downstream, the downstream fan impeller being connected by its downstream part to its drive shaft.

Twin fan turbomachine

The present invention relates to a structural or non-structural turbojet engine fan casing connecting arm that also acts as a flow straightener downstream of the fan rotor. Its distinctive feature is that it is constructed to form an acoustic attenuator. In particular, it comprises a closed cavity and perforations on one of the faces so as to form a Helmholtz resonator. The arm forms part of the intermediate casing.

Acoustic flow straightener for turbojet engine fan casing

The composite turbomachine blade of the present invention comprises a preform made of yarns or fibers woven in three dimensions and a binder maintaining the relative disposition between the yarns of the preform. Said preform is made up of warp yarns and of weft yarns, the direction of the warp yarns forming the longitudinal direction of the preform. In characteristic manner, said preform comprises at least a first portion made using a first weave forming the airfoil of the blade, and a second portion made using a second weave forming the root of the blade, and the first and second portions are united by a transition zone in which the first weave is progressively modified to end up with the second weave, thereby obtaining a reduction at least in the thickness of the blade between the second portion and the first portion. The invention is applicable to making a fan blade for a turbojet.

Turbomachine blade, in particular a fan blade, and its method of manufacture

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Avon, France

Olivier Michael Molinari