Safran Aircraft Engines

Erwan Perrot

Simon Jean-Marie Bernard Cousseau

Marc-Antoine Anatole Got

Camille Maryse Martine Palomba

Antoine Frédéric Jean Satre

Antoine Frederic Jean Satre

A turbine unit for an aircraft turbine engine, comprises a rotor disc () axially continued by a rim () and carrying rotary blades () defining together with the disc () channels for air flow (); an annular flange () including a bearing end () and defining together with the rim () an air passage () communicating with the channels for air flow (); a member () for axially retaining the blades applied against the disc () by the bearing end (), this turbine unit being characterised in that at least one element, out of the retaining member () and the flange (), comprises a groove () formed facing the other element, out of the retaining member () and the flange (), and into which a sealing joint () against which the other element axially bears is inserted.

Turbine unit for aircraft turbine engine with improved disc-cooling circuit

A turbine includes a stator and a movable rotor, rotating around an axis, in relation to the stator. The rotor comprises at least one disc, the radially outer periphery of which comprises cavities. The rotor further includes blades, each having a blade root axially engaged in a cavity of the disc so as to radially hold the blade on the disc. At least one of the blade roots has an axially flaring shape, with the corresponding cavity having a matching shape so as to axially lock the blade root in the cavity in a first axially oriented direction. Locking means lock the blade root in the cavity in a second axially oriented direction, opposite the first direction.

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Moissy-Cramayel, France

Erwan Perrot