Abstract: Rotor blade for a compressor or a gas turbine, in particular for a turbojet engine, including a suction side and a pressure side, which are joined at their upstream ends by a leading edge and at their downstream ends by a trailing edge for the gases, a platform connecting the suction side and the pressure side to a blade root, and a stiffener formed beneath the downstream part of the platform and including at least one notch or a cut-away in line with the trailing edge, in order to reduce the stresses in the joint region between the aerofoil and the platform.

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.