Safran Aircraft Engines

Snecma

Slim Bensalah

Arnaud Nicolas Negri

Arnaud Negri

Ba-Phuc Tang

Sebastien Digard Brou De Cuissart

Denis Gabriel Trahot

Sébastien Digard Brou De Cuissart

David Mathieu

Guillaume Klein

Alexandre Gimel

Thomas Lardellier

Sibylle Doremus

Romain Bard

A turbomachine rotor blade includes an outer part at its distal end. The outer part includes a platform defining an outside surface of a passage for gas passing through a turbomachine and presenting first and second opposite side edges; and upstream and downstream sealing wipers extending outwards from the platform, each wiper extending between two lateral faces situated respectively at the first and second side edges. The two lateral faces of the upstream or the downstream wiper are covered at least in part in an anti-wear material.

Turbomachine rotor blade

A turbomachine rotor blade, said blade having, at the distal end thereof, a heel comprising: a platform () having a first edge () on the lower side and a second edge () on the upper side, at least one sealing member having a first end portion () on the lower side and a second end portion () on the upper side, said sealing member having a sealing top that extends radially outwards from said platform () between said first and second end portions (), characterized in that, for at least one sealing member, the heel () comprises, on at least at one of the edges (), a portion forming a bowl () extending along the end portion () of the sealing member which corresponds to the edge (), the portion forming the bowl () being suitable for receiving a deposit of anti-wear material.

Growing community of inventors

Moissy-Cramayel, France

Slim Bensalah