Snecma

Franck Boisnault

Maurice Guy Judet

Patrice Jean-Marc Rosset

Sébastien Serge Francis Congratel

David Thien-Roger Nguyen

Laetitia Person

A turbine blade for an aircraft turbomachine including a root, an airfoil and a platform inserted between the airfoil and the root and delimiting a gas circulation flowpath, the platform having two axial ends each forming an angel wing of which at least one has an internal cavity that will be supplied with air from the root of the blade. At least one of the two angel wings is drilled with at least one bleed hole for passage of a bleed flow from the internal cavity that will limit/prevent gas recirculation outside the flowpath.

Mobile turbine blade with an improved design for an aircraft turbomachine

A turbine wheel for a turbine engine comprising a disc carrying blades. Each blade comprises an upstream radial wall and a downstream radial wall which extend inwards from the platform of the blade. Inter-blade cavities each accommodate one inter-blade sealing and vibration damping member. According to the invention, each inter-blade sealing and vibration damping member comprises at least a first transverse partition wall axially arranged at a distance from a downstream (or upstream, respectively) portion of the member and axially opposite two upstream (or downstream, respectively) so as to obstruct a flow of incoming air into the cavity between two adjacent upstream radial walls or two adjacent downstream radial walls.

Growing community of inventors

Ris Orangis, France

Franck Boisnault