Safran Aircraft Engines

Damien Bernard Quelven

Maurice Guy Judet

Ba-Phuc Tang

Jean-Baptiste Vincent Desforges

Jean-Baptise Vincent Desforges

A mobile vane for a turbine engine, including a root designed to be inserted into a receiving element of a rotor disk for a turbine engine, a platform carried by the root, and a blade extending from the platform. The platform includes an upstream edge. The upstream edge includes a lug for engaging in a locking notch of the disk in such a way as to hold the vane axially in relation to the disk, according to the longitudinal direction of the receiving element.

Mobile vane for a turbine engine, comprising a lug engaging in a locking notch of a rotor disk

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).

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Paris, France

Damien Bernard Quelven