Abstract: 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.

Abstract: A turbine engine vane is made of composite material comprises a hollow airfoil with an internal passage extending along its entire length, an inner platform, and an outer platform. The airfoil is extended on the outside of the outer platform by an upstream attachment portion and a downstream attachment portion for mounting the vane in a casing. The attachment portions are formed by an attachment extending from the outer longitudinal ends of the pressure side wall and the suction side wall of the airfoil with continuity of the fiber reinforcing texture of the composite material between the walls and the attachment tabs.

Abstract: 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.

Abstract: 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.

Abstract: A turbine engine vane is made of composite material comprises a hollow airfoil with an internal passage extending along its entire length, an inner platform, and an outer platform. The airfoil is extended on the outside of the outer platform by an upstream attachment portion and a downstream attachment portion for mounting the vane in a casing. The attachment portions are formed by an attachment extending from the outer longitudinal ends of the pressure side wall and the suction side wall of the airfoil with continuity of the fiber reinforcing texture of the composite material between the walls and the attachment tabs.

Abstract: 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.