Snecma

Safran Aircraft Engines

Damien Alquier

Ba-Phuc Tang

Daniel Quach

Sebastien Digard Brou De Cuissart

Denis Gabriel Trahot

Sébastien Digard Brou De Cuissart

David Mathieu

Jacques Auguste Amedee Boury

Guillaume Klein

Sebastien Congratel

Pascal Courtin

Raphael Dupeyre

Yvon Marie-Joseph Louesdon

Florian Le Merdi

Huu-Thanh Tran

Joseph Tami

Fadoua Cisse

Sabine Maltaverne

Jacques Auguste Amédée Boury

A method for manufacturing a turbine engine blade including an airfoil with a profile defined by a theoretical digital model, the method including: manufacturing a blank having a thickened portion along a trailing edge of the airfoil relative to the theoretical profile; removing the thickened portion by adaptive machining, including: positioning the blank in a reference frame; acquiring, by probing at a predetermined number of points on a first surface of the blank along the trailing edge, positions of the points in the reference frame; determining differences, in one direction, in position from corresponding points of the theoretical model; producing machining grids on the blank surface, peaks of the grids determined from the points; determining an amount of material to be removed from the surface of the grids, based on the position of the points relative to the peaks and the deviations in position; and machining the airfoil.

Method for machining the trailing edge of a turbine engine blade

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

An inter-blade sealing for a turbine or compressor wheel of a turbine engine includes inserts engaged in longitudinal cavities in side edges of platforms of blades and bearing, in operation, against facing side edges of platforms of adjacent blades. Each insert has a cylindrical elongate shape and includes in its outer cylindrical surface at least one annular groove for passing platform cooling air.

Inter-blade sealing for a turbine or compressor wheel of a turbine engine

A method of manufacturing a metal blading sector for low-pressure guide vanes of a turbomachine of which at least one blade includes an internal cavity configured to accept or communicate with a gas detection probe and at least one hole formed in the wall constituting a passage for gas from a low-pressure zone of the turbomachine toward the cavity and the probe through the fitting, into a casting mold, of a core corresponding to the cavity and the casting of a molten metal in the cavity of the casting mold. The core includes, for each hole for communication with the cavity, a protrusion penetrating the internal surface of the mold and constituting the only element holding the core in position in the casting mold.

Method of manufacturing a blading component

Growing community of inventors

Paris, France

Damien Alquier