Snecma

Safran Aircraft Engines

Safran Helicopter Engines

Guillaume Klein

Ba-Phuc Tang

David Mathieu

Sebastien Congratel

Raphael Dupeyre

Denis Gabriel Trahot

Arnaud Nicolas Negri

Matthieu Jean Luc Vollebregt

Sebastien Digard Brou De Cuissart

Sébastien Digard Brou De Cuissart

Stéphane Lavignotte

Damien Alquier

Sébastien Serge Francis Congratel

Josserand Bassery

Slim Bensalah

Raphaël Jean Philippe Dupeyre

Sibylle Doremus

Thomas Joseph Lardellier

Guillaume Carrerot

Sébastien Congratel

Julien Jerome Mathieu Reingpach

Marine Laeticia Camille Chevalier

Raphaël Dupeyre

A turbomachine blade that includes an airfoil that includes an intrados wall, an extrados wall, a leading edge, a trailing edge, an internal cavity and a plurality of cooling holes made in the walls and leading and trailing edges, each cooling hole connecting the internal cavity to the exterior, one end of each cooling hole opening up into the cavity, the other end of each cooling hole opening to the exterior through an outlet, wherein the cooling holes are distributed in at least one first alignment and a second alignment made in a wall of the airfoil, wherein this outlet of at least one of the cooling holes belonging to at least the second alignment is an oblong shape with its long dimension along the principal direction of said second alignment.

Turbomachine blade with improved cooling holes

A tubular ventilation sleeve for a turbomachine distributor, in particular for an aircraft, the sleeve having a generally elongate shape along an axis (A-A) and including a perforated tubular wall around said axis, one of the axial ends of the sleeve being open and the other being closed by a bottom wall, wherein it further includes support beams when the sleeve is made by additive manufacturing, the beams extending inside the sleeve between the tubular wall and the bottom wall and having a longitudinal cross-section with a generally triangular shape, two sides of which are respectively connected to the tubular wall and the bottom wall and the last side of which is free and extends inside the sleeve, perforations in the tubular wall being provided between the support beams.

Impact-cooling tubular insert for a turbomachine distributor

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

Growing community of inventors

Mery sur Oise, France

Guillaume Klein