Safran Aircraft Engines

Blaise Bergon

Laurent Jablonski

Caroline Marie Frantz

Vincent François Georges Millier

Huguette De Wergifosse

Lilian Yann Dumas

Alain Marc Lucien Bromann

Kamel Benderradji

Suzanne Madeleine Coustillas

Guillaume Sevi

Jean Charles Olivier Roda

Thomas Nolwenn Emmanuel Delahaye

Noël Joseph Camille Robin

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

Variable-pitch blade control ring () for a turbine engine, including an annular body () configured to be mounted so as to be rotatable about an annular casing () of the turbine engine. The body links to levers () for connecting to the vanes. The ring has a mechanism for guiding in an axial and/or helical direction, supported by the body. The mechanism includes at least one substantially radial finger () for axial abutment on at least one first surface () of the casing and for sliding on the surface.

Variable-pitch blade control ring for a turbomachine

An assembly for controlling variable pitch vanes in a turbine engine, the assembly comprising an actuating ring surrounding a casing of the turbine engine and connected by rods to variable pitch vanes. The actuating ring is configured to rotate around the casing. The assembly further includes a passive element including a first end sliding connected to a second end. The first end is connected by a sliding pivoting link on the actuating ring, and the second end is connected by a ball-joint link to the casing.

Assembly for controlling variable pitch vanes in a turbine engine

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Moissy-Cramayel, France

Blaise Bergon