Snecma

Safran Aircraft Engines

Yvon Marie-Joseph Louesdon

Daniel Quach

Patrick Wehrer

Jean-Louis Martial Verger

Patrick Pourfilet

Damien Alquier

Florian Le Merdi

Joseph Tami-Lizuzu

Fadoua Cisse

Didier Legeai

Joseph Tami

Sabine Maltaverne

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 method for finishing a shape of a component by machining, in which one area is produced by smelting with a thickened portion forming a first surface with a surrounding profile and a theoretical profile defined by a second surface, the method including: defining, on the second surface, a grid forming nodes and squares; defining each point over which the machining tool is to pass according to weighting coefficients equal to weight to be given to the nodes of the square in which the tool is located, to be the barycenter of assigned nodes of the coefficients; measuring, for each node located outside an outer limit, the delta between the first surface at the node and the theoretical position of the node; calculating deltas for each node within the outer limit by interpolation from already known deltas; using the weighting coefficients, defining the delta to be applied at each point.

Adaptive machining method for smelted blades

A mold for producing a part, such as a turbomachine blade model, by injecting wax into a cavity, the cavity including at least two cavity elements, each of which is supported in a cavity block. The two cavity blocks are mobile relative to one another between a closed position for injecting the wax and an open position for removing the part following the injection of the wax. The two cavity blocks are mobile in a horizontal plane.

Mold for producing parts by wax injection

Growing community of inventors

Taverny, France

Yvon Marie-Joseph Louesdon