Snecma

Snecma Moteurs

Societe Nationale D'etude Et De Construction De Moteurs D'aviation

Claude R Lejars

Bruce Pontoizeau

Nicolas Christian Triconnet

Patrick Reghezza

Christophe Follonier

Jerome Mace

Jacky S Naudet

Jacques M Stenneler

Jean-Max M Silhouette

Richard Staessen

Patrice Suet

Sylvain Poitout

Jérôme Mace

François Buffenoir

Pierre-Yves Maillard

Silvain Lormier

Guy jean-Louis Lapergue

Nicolas Triconnet

Sebastien Bourgoin

Alexandre Roy

Marica Mesic

Thierry Niclot

Patrick Adenis

Christophe Tourne

Sébastien Bourgoin

A rotor disk comprises a plurality of circumferentially distributed hooks, the set of hooks defining an annular groove adapted to cooperate with at least two flange sectors. At least one of the hooks comprises a second element through which a recess is formed which opens up at each of the transverse flanks of the second element and at the internal peripheral surface of the second element.

Rotor disk including a plurality of hooks

Unbalanced mass effects can occur at the low pressure compressor () of an aircraft engine. Stiffeners () are proposed to increase the stiffness of the assembly and therefore reduce possible cracks due to accidental unbalanced masses, one end () of the stiffener can be fixed to the engine casing () at the structural arm (), and the other end () can be fixed to the compressor (), preferably at the upstream face of the third guide vane (RD). Advantageously, the stiffeners () are made of two parts fixed to each other; their manufacturing is optimized to limit the additional weight due to their presence.

Stiffener for low pressure compressor for an aircraft engine

Turboshaft engine including two subassemblies defining between them an annular chamber housing a seal. The two subassemblies are assembled under axial stress thereby defining an annular chamber housing the seal and an interposed part is inserted between the butting surfaces of the two parts of the annular chamber.

Turboshaft engine comprising two subassemblies assembled under axial stress

A control lever for the pitch angle of a blade in a turbomachine, said lever having a first end intended to be mounted on a blade pivot so as to rotate it and a second end comprising a cylindrical peg for mounting on a control annulus, this peg being fixed by crimping of one of its ends in an orifice of the second end of the lever and comprising an annular flange to which is applied the second end of the lever, wherein stress distribution means are interposed between the second end of the lever and the crimped end of the peg.

Control lever for the pitch angle of a blade in a turbomachine

The invention relates to a bladed disk for a turbomachine, the disk including blades which extend into a conical stream and which are held in a peripheral groove of said disk by hammerhead type fasteners, each of said blades further including a platform whose radially-outer face defines the boundary of the gas flow stream and whose radially-inner face presents an upstream rib and a downstream rib disposed in planes that are perpendicular to the axis of rotation of said disk and that are radially adjacent respectively to an upstream ring and a downstream ring formed at the periphery of said disk on either side of said groove in order to provide leaktightness in these zones, wherein the thickness of the downstream rib in the axial direction is greater than the thickness of the upstream ring.

Retention capacity of a blade having an asymmetrical hammerhead fastener, with the help of platform stiffeners

The invention relates to a method of improving the retention capacity of a blade having an asymmetrical hammerhead connection and extending in a conical stream, with the root of the blade being retained in a peripheral groove in a disk, said groove having an upstream lip and a downstream lip presenting respective bearing surfaces that extend in planes that are asymmetrical relative to planes perpendicular to the axis of rotation of said disk, and against which the surfaces of the upstream and downstream flanks of said root come to bear, the bearing surface of said upstream lip being connected to the bottom wall of said groove via a rounded surface, and the upstream flank presenting, in the vicinity of said rounded surface, a heel situated inside a circle of radius R centered on the axis about which said blade tends to pivot when axial stress is applied thereto, said circle outlining, in the upstream lip, a crescent shape of thickness, wherein:

Retention capacity of blade having an asymmetrical hammerhead connection

A variable geometry exhaust nozzle is disclosed in which the follower flaps of the first, upstream ring of flaps and the second, downstream ring of flaps have a seal to seal the gap between the upstream and downstream follower flaps throughout the range of movement of the variable nozzle flaps. The sealing device has a plate extending between the downstream edge portion of an upstream follower flap and the upstream edge portion of a downstream follower flap and across the entire circumferential width of the flaps. The plate has an upstream portion pivotally connected with the downstream edge portion of the upstream follower flap and a downstream portion which has a bead pivotally contacting an inner surface of the upstream edge portion of a downstream follower flap.

Seal for a variable geometry nozzle

A turbo-machine compressor which includes variable incidence stator vanes the angular adjustment of which is controlled by a control ring coupled to individual vanes by individual links. Each link has at least one contact surface on each of its longitudinal edges, such surfaces being either plane or convex. In the event of failure of any link, the change in orientation is controlled within narrow limits by contact with the contact surfaces of adjacent links which have not failed.

Turbo-machine compressor with variable incidence stator vanes

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Draveil, France

Claude R Lejars