Snecma

Safran Aircraft Engines

Herakles

Amaury Roussely-Rousseau

Guy Burlet

Son Le Hong

Jean Pierre Mareix

Didier Fabre

Emmanuel Berche

Jean-Pierre Mareix

Hubert Illand

A turbine rotor for a turbomachine, including a disk containing slots for mounting vane roots, each slot being defined by two adjacent teeth of the disk, the vane roots including contact surfaces bearing on contact surfaces of the teeth of the disk. Foils are mounted on the teeth of the disk, each foil having a general U-shape including lateral bearing parts inserted between the corresponding contact surfaces of the vane roots and teeth of the disk, and a central part facing the peak of the corresponding tooth of the disk and defining a cavity between said peak and the foil. The turbine rotor also includes a device for supplying cooling air into said cavity.

Turbine rotor for a turbomachine

A turbine wheel in a turbine engine is provided. The wheel includes a disk having a plurality of blades with roots that are axially engaged and radially retained in longitudinal slots in the outer periphery of the disk, the blades having platforms that extend circumferentially end to end and that are radially facing longitudinal teeth of the disk that define the slots. Protection members for protecting the flanks of the slots and made out of sheet metal are mounted on the teeth of the disk and held thereon by co-operating shapes, the protection members bear radially against the platforms of the blades in order to oppose circumferential tilting of the blades, and at least partially close the radial gaps between the teeth and the platforms of the blades.

Turbine wheel in a turbine engine

A device for attaching blades to a rotor disk of a turbine engine is provided. The device includes: a rotor disk provided at its outer periphery with a plurality of slots, each slot being formed between two adjacent disk teeth and extending axially between front and rear faces of the disk; a plurality of blades, each having a respective root mounted in a slot of the disk; and at least one pin mounted in the rotor disk to pass through the roots of at least two adjacent blades and extending between the front and rear faces of the rotor disk so as to attach the blades to the rotor disk.

Device for attaching blades to a turbine engine rotor disk

Bleeding cooling air to cool a subassembly, e.g. such as a turbine, with automatic adjustment of the air flow section as a function of the speed of the engine. According to the invention, a shutter element is fastened to co-operate with a bleed hole, with the material that constitutes either the shutter element or the wall in which the hole is formed being of a type in which it is possible to create eddy currents, and a magnet is mounted to move past said arrangement.

Growing community of inventors

Toulouse, France

Amaury Roussely-Rousseau