Safran Aircraft Engines

Noël Joseph Camille Robin

Laurent Jablonski

Guillaume Sevi

Lilian Yann Dumas

Florian Benjamin Kévin Lacroix

Thomas Nolwenn Emmanuel Delahaye

Julien Vitra

Frédéric Jacques Eugène Goupil

Blaise Bergon

Thomas Etienne Camille Marie Van De Kerckhove

Disclosed is a compressor of a dual-flow aircraft turboshaft engine extending longitudinally along an axis X, the compressor comprising a low-pressure compressor, a high-pressure compressor and an intermediate casing axially connecting the low-pressure compressor and the high-pressure compressor, the high-pressure compressor comprising an inlet guide stator comprising a retaining ring, an outer high-pressure compressor casing and a plurality of vanes, the compressor comprising an immobilising device comprising at least one first member secured to the intermediate casing and at least one second member secured to the retaining ring and configured to cooperate with the first member in order to prevent tangential movement while allowing axial movement and radial movement of the retaining ring relative to the intermediate casing according to the axis X.

Aircraft turboshaft engine compressor comprising a device for immobilising a retaining annulus

A discharge conduit suitable for use with a turbine engine. The discharge conduit includes an air intake end, an air outlet end and a tubular duct for guiding air between the air intake and air outlet ends. The air intake end is equipped with attachment elements for attachment to an intermediate casing of the turbine engine. The attachment element can be of the resilient snap-in type.

Attachment of a discharge conduit of a turbine engine

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Villejust, France

Noël Joseph Camille Robin