Techspace Aero S.a.

Safran Aero Boosters Sa

Enrique Penalver Castro

Alain Derclaye

Xavier Wery

Benoît Baldewijns

Yves Culot

Rémy Princivalle

Matthieu Janssens

A turbomachine assembly and, in particular, a low-pressure compressor of an aircraft turbojet engine includes an annular row of upstream vanes with trailing edges extending radially from an upstream support; an annular row of downstream vanes with leading edges axially facing the trailing edges and extending radially from a downstream support; an annular passageway delimited by the upstream support and the downstream support. The downstream support has a profile with: an upstream portion delimiting the annular passageway forming an annular slide, a downstream portion axially at the level of downstream vanes, and a connecting arc connecting the upstream portion to the downstream portion. The connecting arc is arranged downstream of the leading edges.

Passageway between a shroud and a rotor platform in a turbine engine

A rectifier stage of an axial turbine engine compressor is placed directly downstream of the input blower of a turbo-reactor or turboshaft engine compressor. The blade roots of the rectifier stage are housed inside the inner shroud by insertion into respective slots. The blade roots include at least one opening protruding from the slot of the shroud, so as to receive a spiral ring having at least two loops so as to prevent the blade roots from escaping from the respective slots of the inner shroud, and so as to form a connection between the blade roots. A method for retaining blades of a rectifier stage of an axial turbine engine compressor on an inner shroud, in particular a rectifier stage placed directly downstream of the input blower of a turbo-reactor or turboshaft engine compressor, includes positioning a spiral ring having at least two loops inside the openings of the blade roots by threading one end of the ring successively into the openings until all of the spirals of the ring are housed inside the openings.

Blade retention at a compressor rectifier stage for impact resistance

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

The present invention relates to a method for manufacturing a turbomachine rectifier comprising an outer ring () and a plurality of stator vanes (), said vanes comprising a platform () and a blade (), wherein said method comprises at least the following steps:

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Soumagne, Belgium

Enrique Penalver Castro