Abstract: A turbomachine moving blade without a top platform, the blade including a fastener root (110) surmounted by an airfoil (112) that presents an end face (114), a pressure-side face (116), and a suction-side face, said fastener root and said end face being situated respectively at bottom and top ends of the blade that are spaced apart along the main axis (A) of the blade. The airfoil presents a projecting edge defined between a portion (124) of its end face and a top portion (122) of its pressure-side face, these portions forming between each other a mean edge angle that is strictly less than 90°. The top portion (122) of the pressure-side face is corrugated, and in a section plane perpendicular to the main axis of the blade, it follows an outline formed by an alternating succession of concave curves (129) and convex curves (131).

Abstract: A moving blade for a turbomachine with a central portion that is geometrically subdivided into four adjacent pressure-side zones disposed on the pressure side of the blade, and into four adjacent suction-side zones disposed on the suction side of the blade, the pressure-side and suction-side zones being distributed on either side of the skeleton of the blade, and the blade including in its central portion a pressure-side cooling circuit and a suction-side cooling circuit, the pressure-side cooling circuit including three radial cavities occupying three adjacent pressure-side zones, and the suction-side cooling circuit including three radial cavities occupying the four suction-side zones and the remaining pressure-side zone.

Abstract: A turbomachine moving blade without a top platform, the blade including a fastener root (110) surmounted by an airfoil (112) that presents an end face (114), a pressure-side face (116), and a suction-side face, said fastener root and said end face being situated respectively at bottom and top ends of the blade that are spaced apart along the main axis (A) of the blade. The airfoil presents a projecting edge defined between a portion (124) of its end face and a top portion (122) of its pressure-side face, these portions forming between each other a mean edge angle that is strictly less than 90°. The top portion (122) of the pressure-side face is corrugated, and in a section plane perpendicular to the main axis of the blade, it follows an outline formed by an alternating succession of concave curves (129) and convex curves (131).

Abstract: A hollow blade has an internal cooling passage, an open cavity situated at the free end of the blade and defined by an end wall extending over the entire end of the blade and by a rim. The blade includes cooling channels connecting the internal cooling passage and the outside face of the pressure side wall. The pressure side wall presents a projecting end portion whose outside face is inclined relative to the outside face of the pressure side wall. The cooling channels are disposed in the end portion, being parallel to the outside face of the end portion so that they open out into the tip of the end portion towards the free end of the blade.

Abstract: A moving blade for a turbomachine, the blade comprising an aerodynamic surface extending radially between a blade root and a blade tip, and at least one internal cooling circuit made up of at least one radial cavity, at least one air admission opening formed in the blade root and opening out into the cavity(ies), and a plurality of outlet orifices opening out from the cavity(ies) and leading to the outside of the blade, the blade root having lower swellings and upper swellings defining bearing surfaces for fastening the blade to a rotor disk. The air admission openings of the cooling circuit(s) open out into a common cavity that is formed in the blade root and that extends radially from the base of the blade root at least as far as the upper swelling of said root.

Abstract: The invention relates to moving blade for a turbomachine. The central portion of the blade is geometrically subdivided into four adjacent pressure-side zones disposed on the pressure side of the blade, and into four adjacent suction-side zones disposed on the suction side of the blade, the pressure-side and suction-side zones being distributed on either side of the skeleton of the blade, and the blade including in its central portion a pressure-side cooling circuit and a suction-side cooling circuit, the pressure-side cooling circuit comprising three radial cavities occupying three adjacent pressure-side zones, and the suction-side cooling circuit comprising three radial cavities occupying the four suction-side zones and the remaining pressure-side zone.

Abstract: The invention relates to a hollow blade having an internal cooling passage, an open cavity situated at the free end of the blade and defined by an end wall extending over the entire end of the blade and by a rim, and cooling channels connecting said internal cooling passage and the outside face of the pressure side wall. In characteristic manner, the pressure side wall presenting a projecting end portion whose outside face is inclined relative to the outside face of the pressure side wall, and said cooling channels being disposed in said end portion, being parallel to the outside face of said end portion so that they open out into the tip of said end portion towards the free end of the blade. The blade is applicable to a high pressure turbine without a heel.