Safran Aircraft Engines

Jean-Baptiste Vincent Desforges

Gaël Frédéric Claude Cyrille Evain

Alain Dominique Gendraud

Maurice Guy Judet

Ba-Phuc Tang

Arnaud Lasantha Genilier

Olivier Arnaud Fabien Lambert

Damien Bernard Quelven

Reda Oudyi

A method of assembling a turbine for a turbine engine that includes mounting annular sectors around the blades to form an abradable ring that includes a groove in a sector of the annular sectors. The method also includes engaging a first wiper of a particular blade of the blades with the groove of the sector. The method further includes axially engaging an assembly comprising the blades and the annular sectors in a casing of a turbine, so that fixing members of the annular sectors cooperate with flanges of the casing to fix the annular sectors in the casing, around the blades. The fixing members comprise at least one upstream fixing member fixed on a radially internal facing side of an upstream end of the annular sectors and at least one downstream fixing member arranged at a downstream end of the annular sectors.

Turbine for a turbine engine and method of assembling same

An assembly includes a securing stud held by a locking key that rotates with the stud and is provided with bearing surfaces for sitting on an edge of one of the parts to be assembled.

Assembly comprising a locked securing stud

A turbine for a turbine engine, the turbine comprising a rotor including blades the radially external periphery of which includes at least one first wiper radially extending outwards, sealing means radially extending about the blades and including a ring made of abradable material, with the radially external ends of the wipers cooperating with said ring made of abradable material so as to form a labyrinth-type seal, wherein said ring includes at least one first portion axially extending upstream of the first wiper and a second portion, different from the first portion, axially extending downstream of the first wiper, with the first portion and/or the second portion including a groove, wherein the first wiper has been inserted, with said groove being defined by the first portion and by the second portion.

Turbine for a turbine engine

The present invention relates to a turbine assembly () of a turbine engine (), comprising at least: a first bladed rotor (), a bladed stator () and a second bladed rotor () arranged in series, the rotors () being mounted on a shaft (); a sealing plate () extending between the stator () and the shaft () and separating a first recess (C) arranged between the first rotor () and the stator (), from a second recess (C) arranged between the stator () and the second rotor (); and pressure-reducing means () positioned inside the first recess (C), the assembly being characterized in that said pressure-reducing means () comprise a plurality of substantially radial recompression fins () extending into the first recess (C).

Growing community of inventors

Moissy-Cramayel, France

Jean-Baptiste Vincent Desforges