Snecma

Herakles

Mersen France Gennevilliers Sas

Safran Aircraft Engines

Nicolas Christian Triconnet

Patrick Jean-Louis Reghezza

Jean-Pierre Lombard

Claude Robert Louis Lejars

Claude R Lejars

Francois Maurice Garcin

Bruce Pontoizeau

Mathieu Caucheteux

Jean-Luc Soupizon

Clement Roussille

Nicolas Eberling-Fux

Son Le Hong

Jean-Bernard Forgue

Michael Delapierre

Richard Staessen

Christophe Yvon Gabriel Tourne

Christophe Follonier

Sebastien Bourgoin

Frederick Thise

Dominique Gaveau

Bruce Daniel Jean Pontoizeau

Thomas Chrzastek

Claude Robert Lejars

Christophe Tourne

François Garcin

Sébastien Bourgoin

Frédérick Thise

A turbine engine turbine blade of ceramic matrix composite. The root of the blade includes a single densified fiber preform including at least one recess made by machining, each point of the root of the blade being situated at a distance from a free surface of the root that is no greater than twice the maximum penetration distance into the preform of densification gas for densifying the preform, and the distal portion of the root of the blade includes a distal wall that is continuous and in a single piece.

Turbine engine turbine blade made of a ceramic-matrix composite with recesses made by machining

A turbomachine rotor including a disc including a rim and axial slots machined in the rim for the individual housing of blades, a ring being attached to one face of the rim, the ring being pierced with holes in the axial continuation of the slots, at least some of the holes in the continuation of the slots including a plug. The plug includes a first half-plug made of a first wear-resistant material and a second half-plug made of a second material, one of the two half-plugs bearing on one side of the ring and the other bearing on the other side of the ring and being connected to one another through the hole. The plug is configured to form an anti-wear device.

Turbomachine rotor comprising an anti-wear plug, and anti-wear plug

An anti-wear device of a turbomachine rotor including a disk with a rim and axial recesses machined on the rim for the individual housing of blades; and a ring being fitted to one face of the rim, the ring being pierced with holes in the axial extension of the recesses, is disclosed. At least one of the holes in the extension of the recesses is closed by a plug including a metal head forming a bearing surface for the blades. The plug includes a stud in the extension of the metal head, an insert made of deformable material surrounding at least partly the stud, and a clamping device. The insert is made of deformable material being deformed by the clamping device so as to immobilize the plug in the hole.

Anti-wear device of a turbomachine rotor

A cylindrical casing for a turbomachine that is suitable for receiving a rotor fitted with at least one bladed wheel is disclosed. The casing includes a device for preventing instability during contact between the casing and the bladed wheel. The device includes a succession of elements disposed around the circumference of the casing, and presenting different stiffnesses between two adjacent elements. The number of elements having the same stiffness not being equal to a multiple of the wave number of the vibratory mode of the bladed wheel that is to be inhibited. The invention is applicable to a compressor, a turbine, or a fan.

Turbomachine casing including a device for preventing instability during contact between the casing and the rotor

The invention relates to a turbomachine thermomechanical part forming a body of revolution about a longitudinal axis, and including at least one abradable ring for a labyrinth seal. In characteristic manner, the abradable ring is made up of angular sectors that present different stiffnesses between adjacent pairs of sectors. The invention is applicable to a compressor, a turbine, or to a rotor and stator assembly.

Thermomechanical part constituting a body of revolution about a longitudinal axis and including at least one abradable ring for a sealing labyrinth

A turbomachine rotor wheel includes a disk carrying blades having roots engaged and held in an annular recess of the disk. The roots are connected to platforms for co-operating with an annular gasket mounted in an annular groove of the disk. The annular sealing gasket exerts a resilient force on the blade platforms holding the blades in a proper position for operation while the turbomachine is at rest.

Turbomachine rotor wheel

Control lever for the angular setting of a stator blade, comprising a first end intended to be fitted in a fixed manner on a blade pivot, a second end comprising a cylindrical pin for fitting on a control ring, and a flat intermediate part connecting the first and second ends having shapes and dimensions determined in order to increase the natural frequencies of the lever in flexion and in torsion above the vibratory frequencies of the turboshaft engine upstream of the lever and in order to retain the stiffness of the lever.

Control lever for the angular setting of a stator blade in a turboshaft engine

Growing community of inventors

Saint Fargeau Ponthierry, France

Nicolas Christian Triconnet