Safran Helicopter Engines

Mathieu Cladiere

Olivier Pierre Descubes

Stephane Vergez

Bertrand Guillaume Robin Pellaton

Jean-Luc Breining

Cedric Roger Zordan

Armand Bueno

Christophe Nicolas Henri Viguier

Stéphane Vergez

Stéphane Raphaël Yves Richard

Gabriel Gorka Exilard

Nicolas Christophe Perra

Jerome Dinquel

Cédric Roger Zordan

An assembly for a turbomachine includes at least one turbine having a turbine disc with an internal bore and an annular cavity which is arranged upstream of the disc. The assembly further includes a fire safety system with a cooling device that supplies the cavity with cooling air via injection means. The fire safety system includes means that divide the annular cavity into first and second cavities. A cooling air speed is maintained at the outlet of the injection means and the cooling air in the first cavity is guided to the internal bore of the turbine disc. A diffuser co-operates with the injection means and an annular cover co-operates with the diffuser and covers first attachment members arranged in the cavity. A radially outer surface of the cover at least partially guides the cooling air at the outlet of the diffuser.

Fire safety system for a turbomachine comprising means for maintaining a cooling air speed and corresponding turbomachine

An assembly for a turbine engine. The assembly includes a mount, a nut clamping around the male portion of the mount, a member projecting from the mount and a device for limiting loosening of the nut. The loosening limitation device includes a member for locking the nut against rotation relative to the mount. The rotation locking member includes an inner surface designed to limit rotation of the nut with shape engagement with an outer surface of the nut. The rotation locking member includes a first anti-rotation abutment designed to rotatably abut against the projecting member. The loosening limitation device includes a translation locking member designed to limit translation of the rotation locking member relative to the nut.

Device for limiting the loosening of a nut in a turbine engine

Adjustable-length connecting rod for an aircraft turbomachine, connecting rod having a generally elongate shape and having first and second longitudinal opposite ends for attachment to elements to be connected. The first longitudinal end is connected to a first threaded shaft screwed into a first tubular portion of an adjustment sleeve. The second longitudinal end is connected to a second threaded shaft screwed into a second tubular portion of the adjustment sleeve. The connecting rod further includes a housing in which at least a portion of the first shaft is configured to slide.

Adjustable-length connecting rod for turbomachine

The invention relates to a mechanical fuse intended to be rigidly mounted between a drive unit (), and a receiver unit (), each rotating about the same axis () of rotation, said fuse comprising a body () extending in a longitudinal direction parallel to said axis () of rotation, once the fuse is mounted between said drive unit () and receiver unit (). The invention is characterized in that said body () comprises a plurality of longitudinal bars (), each bar () being deformable by bending, such as to form a twist-breakable mechanical fuse.

Twist-breakable mechanical fuse and cooling unit of a turbine engine fitted with such a fuse

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Pau, France

Mathieu Cladiere