Safran Aircraft Engines

Safran Ceramics

Arthur De Castro

Sébastien Serge Francis Congratel

Matthieu Arnaud Gimat

Patrick Joseph Marie Girard

Nicolas Xavier Trappier

Didier René André Escure

Baptiste Dorian Lawniczek

Patrice Jean-Marc Rosset

A bladed assembly () includes two adjacent blades (). Each blade () a platform () located at a free radial end. The platform () of the first blade () includes a lateral face () which is located circumferentially opposite an associated lateral face () of the platform () of the second blade (). The platform () of the second blade () comes into contact with the platform () of the second blade () only via an excrescence () which projects circumferentially with respect to the lateral face () of the platform () of the first blade () in the direction of the platform () of the second blade (), and the excrescence () is received in a groove () formed in the platform () of the second blade.

Turbomachine blading assembly comprising means for limiting vibration between platforms

Blade of a turbomachine turbine including a airfoil extending along a first direction between an internal end and an external end, a base secured to said internal end, and a root secured to said external end and extending, along a second direction perpendicular to said first direction, between an upstream edge and a downstream edge and, along a third direction orthogonal to the first and second directions, between first and second lateral edges, the first side edge having, in a plane including the second and third directions, a shape complementary to that of the second lateral edge. The first lateral edge includes a first portion extending from the upstream edge, and a second portion externally protruding along the third direction at an acute angle with the first portion.

Turbine blade of a turbine engine with self-generated interlock contact force in operation

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Moissy-Cramayel, France

Arthur De Castro