Techspace Aero S.a.

Techspace Aero

Safran Aero Boosters Sa

Xavier Wery

Alain Derclaye

Georges Duchaine

Enrique Penalver Castro

Thomas Colmant

Georges Broers

André Lhoest

Christine Brassine

A segmented composite shell for an axial turbomachine compressor, each segment formed of a first polymeric material and comprises at least one working surface formed of a second polymeric material co-injected with the first polymeric material. The working surface can be a contact surface with a blade, wherein the working surface has a lipped profile and is made of an elastomeric material. The working surface can be the inner surface for bonding an abradable material, wherein the material can be silicone to facilitate the bonding of the abradable material to the silicone base. The working surface can be a lateral face of the shell that contacts a mating fixed surface, wherein the material can comprise TEFLON&#xae;, i.e. Polytetrafluoroethylene (PTFE), so as to form a working surface with dry friction properties. Such features enable the shell to have additional technical features implemented directly during the injection moulding of the shell segments.

Co-injected composite shell for an axial turbomachine compressor

The present invention relates to a rotor stage of a compressor drum () for an axial turbomachine comprising a row of rotor vanes () each provided with a platform (), and a wall () that is generally symmetrical in revolution relative to the rotation axis of the turbomachine and forming a hollow body, said wall () comprising a partition wall and a support zone () that is raised relative to the partition wall in a direction oriented towards the outside of the hollow body, said support zone () having a central portion () and side walls () connecting the central portion () to the partition wall of the drum, said platform () of each of said vanes () being assembled to said central portion () by means of one or more fastening elements.

Lightened axial compressor rotor

The present invention relates to a turbine engine rectifier stage comprising a plurality of fixed vanes connecting an inner ferrule supportto an outer ferrule support, said inner ferrule support and said outer ferrule support defining an aerodynamic vein and comprising a set of contiguously assembled sectorsrespectively, the plurality of fixed vanes comprising so-called structural vanessurrounding so-called non-structural or aero vanesso as to form boxes, said structural vanesbeing rigidly attached to the ends of the sectors of the inner ferrule supportby means of attachment elementsin order to impart increased stiffness to the boxes

Architecture of a compressor rectifier

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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Liege, Belgium

Xavier Wery