Techspace Aero S.a.

Safran Aero Boosters Sa

Techspace Aero

Georges Duchaine

Xavier Wery

Thomas Colmant

Philippe Laurent

Georges Broers

André Lhoest

Michel Philipet

Michel Philippet

The present application relates to a method for assembling a stator stage of a turbomachine, the stage having an inner ring, an outer ring, and vanes extending radially between the inner ring and the outer ring. The method includes at least the following essential step: applying at least one inflatable bladder against at least one opening between a vane and one of the inner ring and the outer ring on that face of the ring which is opposite the face for application of a sealing material, so as to form one or more retention surfaces for the sealing material. The present application also relates to an assembly device designed for implementing the method.

Application of a connection joint to a stator stage by means of inflatable bladders

The invention relates to a casing, particularly of an axial turbomachine compressor. This casing comprises a support of cylindrical overall shape made of composite material, a metal ring fitted by bonding to the internal surface of the support, and a layer of abradable material fitted by plasma spray onto the internal surface of the metal ring. The metal ring is preferably made of stainless steel and is preferably perforated. The perforation allows better keying of the adhesive and allows the degassing thereof. The external surface of the metal ring is preferably sandblasted prior to bonding. Its internal surface is also preferably sandblasted prior to the plasma spraying of the abradable material.

Axial turbomachine compressor outer casing

The present invention relates to a method for manufacturing a turbine-engine composite rectifier comprising a ferrule provided with a plurality of stator vanes (), said stator vanes each comprising a blade () and optionally a platform (), said method comprising at least the following steps:

Method for manufacturing a rectifier

The present invention relates to an automated method for manufacturing layer by layer a composite part with rotational symmetry and complex cross-section, comprising the following stages:

Manufacture of complex composite parts

A turbo-engine stator blading is disclosed. The turbo-engine stator blading includes a crown of fixed blades mounted on a ring. Each blade includes a platform and each blade is fastened to the ring. The ring includes a plurality of individual receptacles for the each of the platforms, the receptacles being machined in the thickness of the ring, the form of each receptacle being complementary to that of the corresponding platform. By means of the receptacles, the mounting of the blades within the blading is both simple and accurate.

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Warsage, Belgium

Georges Duchaine