Snecma

Christophe Jacq

Jean-Pierre Lombard

Mathieu Caucheteux

Stephane Rene Julien Giusti

Arnaud Rene Suffis

Charles Douguet

The invention relates to a nozzle stage for a turbomachine compressor, the stage comprising two coaxial shrouds, a radially inner shroud and a radially outer shroud, and radial vanes extending between the shrouds and being connected via their ends to the shrouds, together with a support for abradable material that is mounted by crimping onto the upstream and downstream edges of the inner shroud, the inner shroud presenting openings in which the radially inner ends of the vanes are inserted and fastened. The radially inner ends of the vanes are plane and do not have any projecting tenons.

Nozzle stage for a turbomachine compressor

The invention relates to a turbomachine blade comprising an aerodynamic surface made of a composite material and extending in a first direction between a leading edge and a trailing edge, and in a second direction between a root and a tip of the blade. The blade includes solid metal reinforcement that is adhesively bonded to the leading edge of its aerodynamic surface, which reinforcement extends along the first direction beyond the leading edge of the aerodynamic surface and along the second direction between the root and the tip, and includes at least one recess for absorbing at least a portion of the energy that results from an impact of a foreign body against the leading edge of the blade.

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Courpalay, France

Christophe Jacq