Snecma Moteurs

Snecma

Sagem Defense Securite

Bruce Pontoizeau

Claude R Lejars

Patrick Reghezza

Christophe Follonier

François Dufresne De Virel

Nicolas Christian Triconnet

Alain Bassot

Michel Pealat

Patrice Suet

Richard Staessen

Patrick Joyez

Sylvie Wintenberger

Jerome Mace

Hervé Buisson

Jérôme Mace

Anne Thenaisie

Christophe Follonnier

Eric Inghels

Nicolas Triconnet

Sebastien Bourgoin

Jean-François Lacuisse

Alexandre Roy

Marica Mesic

Christophe Tourne

Sébastien Bourgoin

An engine and pod assembly for an aircraft includes a pod receiving an engine having an air intake. A rotating nose cone extends on the nose cone, as well as a device for limiting the formation of ice. The device includes means for creating a circumferential heterogeneity of ice on the nose cone.

Engine and pod assembly for an aircraft, equipped with an anti-icing device including a source of radiation and pulse control unit connected to the source of radiation

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

A restraining device for a fan blade root, in which a packing member is constituted by a metal structure having hollowed out portions filed in by overmolding with a semi-rigid elastomer material, in particular on a lateral edge concave side between an upstream end zone and a downstream end zone, which end zones are entirely of metal structure, on a lateral edge convex side between the end zones and a central zone that is essentially of metal structure, and on two top portions of the packing member that extend between the elastomer lateral edges on either side of the metal central zone. The metal structure also includes a bottom recess extending over its entire surface between the upstream end zone and the downstream end zone. Hence, the metal structure behaves like a spring blade when the blade turns following a violent impact.

Restraining device for fan blade root

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

Growing community of inventors

Paris, France

Bruce Pontoizeau