Snecma

Safran Aircraft Engines

David Mathieu

Ba-Phuc Tang

Guillaume Klein

Denis Gabriel Trahot

Sebastien Congratel

Raphael Dupeyre

Sebastien Digard Brou De Cuissart

Eric Herzer

Yannick Collin

Arnaud Nicolas Negri

Christian Bariaud

Sébastien Digard Brou De Cuissart

Christophe Remy

Damien Alquier

Sébastien Serge Francis Congratel

Bruno Richard

Josserand Bassery

Slim Bensalah

Thomas Lardellier

Sibylle Doremus

Raphaël Jean Philippe Dupeyre

Xavier Godfrind

Bruno Marie Benjamin Jacques Richard

Sébastien Congratel

Eric Rene Herzer

Bruno Marie Richard

Arnaud Negri

Eric René Herzer

Raphaël Dupeyre

A turbomachine rotor blade includes an outer part at its distal end. The outer part includes a platform defining an outside surface of a passage for gas passing through a turbomachine and presenting first and second opposite side edges; and upstream and downstream sealing wipers extending outwards from the platform, each wiper extending between two lateral faces situated respectively at the first and second side edges. The two lateral faces of the upstream or the downstream wiper are covered at least in part in an anti-wear material.

Turbomachine rotor blade

A blade preform includes a strut connecting a plat-form to a blade root portion extending longitudinally in an upstream-downstream direction, an upstream web and a downstream web, which each extend in a direction substantially perpendicular to the longitudinal direction of the blade root and are formed at the upstream and downstream ends of the strut. The upstream and downstream webs connect the upstream and downstream ends of the plat-form to the upstream and downstream ends of the blade root. The blade root extends in a direction perpendicular to the longitudinal direction of the blade root over a distance smaller than that of the upstream and downstream webs and the side edges of each web are extended by walls that converge at the flanks of the blade root.

Turbine engine blade preform

A method for producing a rotor vane () for a turbomachine, including producing a rough casting, the heel of which has a downstream lip () with a transverse increased thickness () such that the lip has an upstream surface () substantially parallel to an axis The method further includes machining said increased thickness so that the downstream lip has an upstream surface () inclined in relation to the axis.

Method for producing a rotor vane for a turbomachine

A turbine engine blade includes an airfoil connected by a platform to a middle radial wall extending axially and prolonged radially inwards by a blade root that is mountable in a slot of a disk, and the platform and the middle radial wall defining two lateral cavities situated on either side of the middle radial wall and opening out circumferentially to receive scaling members. The cavities are open downstream with two fins projecting on either side of the middle radial wall at downstream end of the middle radial wall, the fins coming to bear against two adjacent teeth of the disk between which the slot is formed. The downstream end of the middle radial wall includes a setback extending between at least one rib of the platform and the fins.

Turbine engine blade

A turbomachine vane for cooperating with a vane retention disk including a plurality of peripheral teeth, the vane including a shank including a neck and a bulb for cooperating with a socket of the disk so as to radially hold the shank in the socket, the socket being a space bounded by two successive teeth of the disk, a pole on top of the neck, including two side walls facing the active surface side of the vane and two side walls facing the passive surface side of the vane, each wall having a rib at a lower end of the pole, the rib extending in the direction of the side wall facing the wall and providing a function of holding the vane when the vane is retained in the disk.

Turbomachine vane cooperating with a vane retention disk

A turbine nozzle for a turbomachine, the nozzle including two coaxial platforms interconnected by radial vanes, an inner platform being connected to an annular partition that is festooned or crenellated and on which there is fastened an annular support carrying elements made of abradable material. The support is capable of sliding circumferentially over the partition between a mounting-and-dismounting position and a position for locking the support on the partition.

Turbine nozzle for a turbomachine

A movable blade for a turbomachine, the blade including at its distal end a top portion including opposite first and second side edges and upstream and downstream sealing wipers. Each of the first and second side edges has a substantially Z-shaped profile between the upstream and downstream wipers. On a side of the first side edge, the platform includes a first outwardly projecting rim not connected to either of the upstream and downstream wipers. The platform includes a second outwardly projecting rim, the second rim including a downstream portion connected to the downstream wiper and extending along the second edge, and an upstream portion extending the downstream portion as far as the upstream wiper, and set back relative to the second side edge.

Movable blade for a turbomachine

A method of manufacture of a wax model of an annular bladed turbomachine stator assembly includes in succession the positioning, in a mold, of a core intended to form the impression of a cavity of a blade of the assembly, the injection of a wax in the mold, and the removal of the wax model fitted with the core from the mold. The core is manufactured in metal and is positioned such that its radially internal end is housed in the portion of the mold defining the blade including the cavity, away from the radially internal end of this portion of the mold.

Method of lost-wax manufacture of an annular bladed turbomachine assembly, metal mould and wax model for implementing such a method

Growing community of inventors

Chelles, France

David Mathieu