Safran Aero Boosters Sa

Techspace Aero S.a.

Eric Englebert

Laurent Schuster

Ludovic Bovyn

Maxime Peeters

A structural casing for an axial turbine engine includes an outer ring, an inner hub, and a plurality of struts extending radially from the hub to the ring, wherein the ring is made of a plurality of angular segments welded together. The segments extend circumferentially of different angles, some segments being larger angularly than others. The structural casing is adapted to be an intermediate casing between two compressors of a turbine engine.

Structural casing for an axial turbine engine

A method for selecting a milling cutter, which method makes it possible to select a milling cutter on the basis of a part to be machined such that the cutting force is constant while the part is being machined.

Method for selecting a milling cutter for machining

The present application relates to a stator of an axial turbomachine compressor. The stator includes a circular wall, such as an internal shroud, with a guiding surface in order to guide the primary flow of the turbomachine. The stator further includes a circular row of stator vanes, each of them including an airfoil which extends radially in the primary flow of the turbomachine, and a securing portion. The securing portion of the vane includes a lattice which has rods and which is secured and/or sealed in the shroud in order to fix the vanes to the shroud via the lattices. The stator includes a joint of abradable material which is arranged inside the internal shroud, and in which the lattice is secured in order to ensure retention, a fixing between the vane and the internal shroud. The vane is produced by means of additive production.

Vane with sealed lattice in a shroud of an axial turbomachine compressor

The invention relates to the design of rotor blades of an axial turbomachine compressor, especially the method of attaching the blades to the rotor. The blades comprise an aerofoil portion and a platform for attaching them to the rotor. The platform comprises, along the main axis of the blade, a first layer forming a surface bounding the fluid stream and skirting the aerodynamic surfaces and a second layer, underneath the first layer with respect to the aerodynamic surfaces, designed to be able to mate with the inner face of a wall of the rotor around an aperture in the rotor for the purpose of attaching it.

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Villers-le-Bouillet, Belgium

Eric Englebert