Abstract: A hollow blade includes an internal cooling passage, an open cavity located at the tip of the blade and bounded by an end wall and a rim and cooling channels that connect the internal cooling passage to the outer face of the pressure wall. The cooling channels are inclined to the pressure wall in such a way that they emerge on the outer face of the pressure wall near the top of the rim. A reinforcement of material is present between the rim and the end wall of the cavity along at least one portion of the pressure wall, whereby the rim is widened at its base adjacent to the end wall in such a way that the cooling channels emerge near the top of the rim without reducing the mechanical strength of the tip of the blade.

Abstract: A hollow blade includes an internal cooling passage, an open cavity located at the tip of the blade and bounded by an end wall and a rim and cooling channels that connect the internal cooling passage to the outer face of the pressure wall. The cooling channels are inclined to the pressure wall in such a way that they emerge on the outer face of the pressure wall near the top of the rim. A reinforcement of material is present between the rim and the end wall of the cavity along at least one portion of the pressure wall, whereby the rim is widened at its base adjacent to the end wall in such a way that the cooling channels emerge near the top of the rim without reducing the mechanical strength of the tip of the blade.

Abstract: A turbine blade of a turbomachine, having at least a bottom platform connected to the base of the blade by a bottom connection zone, and a cooling circuit consisting of at least one cooling cavity, of a plurality of evacuation slots arranged along the trailing edge of the blade, said blade having a bottom evacuation slot that is disposed near the blade base, the bottom evacuation slot including an end wall provided with an opening that opens into the cavity, a setback wall, a bottom wall disposed beside the blade base, a bottom edge formed between the setback wall and the bottom wall, and a bottom shoulder formed between the bottom wall and the bottom connection zone, both the bottom edge of the bottom evacuation slot and the bottom shoulder of the bottom evacuation slot having respective right sections of substantially rounded shape, thereby avoiding any protruding angles between the opening of said slot and the bottom connection zone.

Abstract: A plugged assembly of cores includes a first core having a first end portion, and a second core having a second end portion. The first end portion of the first core is connected to the second end portion of the second core by a mortise and tenon type connection to form an assembly of the two cores having residual spaces formed by the mortise and tenon type connection, such residual spaces being liable to give rise to flashings when metal is poured over the assembly if not plugged. Residual spaces formed by the mortise and tenon type connection in the assembly of the two cores contain a material configured to reduce the possibility of flashings.

Abstract: A hollow blade includes an internal cooling passage, an open cavity located at the tip of the blade and bounded by an end wall and a rim and cooling channels that connect the said internal cooling passage to the outer face of the pressure wall. The cooling channels are inclined to the pressure wall in such a way that they emerge on the outer face of the pressure wall near the top of the said rim. A reinforcement of material is present between the rim and the end wall of the cavity along at least one portion of the pressure wall , whereby the said rim is widened at its base adjacent to the said end wall in such a way that the cooling channels emerge near the top of the rim without reducing the mechanical strength of the tip of the blade.

Abstract: The present invention relates to a turbine module for a gas turbine engine comprising at least one turbine disk (3) and a disk-shaped component (5) mounted on the turbine disk upstream relative to the gas flow, said module comprising a means of assembly to the compressor of said engine, wherein the component (5) is preassembled to the turbine disk (3), before the module is assembled to the compressor, by bolting to an attachment flange (31) fixedly attached to the turbine disk (3).

Abstract: The present invention concerns a process for manufacturing the blade of a turbomachine using the lost-wax moulding technique, where the blade includes a first central longitudinal cavity and at least one second longitudinal cavity together forming a cooling circuit and communicating with each other at one longitudinal end via a transverse channel, where the process includes the manufacturing stage of first and second cores corresponding to the said cavities, where the two cores each have an end portion, by which they are connected together, and where the assembly of the two cores is then positioned in a shell mould and the metal poured into the said mould, characterised by the fact that the said end portions, are connected together by an assembly of the mortise and tenon type.

Abstract: The invention relates to a device for balancing a turbomachine rotor comprising at least one counterweight 20 fitted to the rotor, characterized in that the counterweight 20 comprises two radial bearing surfaces 23, 24 oriented in two opposite radial directions, the said surfaces interacting with two radial bearing surfaces 10A1, 10B1 made on the rotor, the counterweight 20 being held against the rotor by an axial retention means. In particular, the axial retention means is a bolt 30 with a nut 32, the bolt holding the counterweight against a coupling flange 10 fixedly attached to the rotor, comprising an axial bearing surface 10B and the said radial bearing surfaces 10A1, 10B1.

Abstract: A rotor blade for a gas turbine, in particular a turbojet, the blade comprising an airfoil, a platform connecting the airfoil to a blade root and having at least one stiffener extending under the downstream portion of the platform, together with means for cooling the blade by a flow of cooling fluid in ducts formed in the blade and in a cavity formed in the stiffener substantially in register with the trailing edge of the blade, and including outlet orifices facing downstream.

Abstract: A turbine blade of a turbomachine, having at least a bottom platform connected to the base of the blade by a bottom connection zone, and a cooling circuit consisting of at least one cooling cavity, of a plurality of evacuation slots arranged along the trailing edge of the blade, said blade having a bottom evacuation slot that is disposed near the blade base, the bottom evacuation slot including an end wall provided with an opening that opens into the cavity, a setback wall, a bottom wall disposed beside the blade base, a bottom edge formed between the setback wall and the bottom wall, and a bottom shoulder formed between the bottom wall and the bottom connection zone, both the bottom edge of the bottom evacuation slot and the bottom shoulder of the bottom evacuation slot having respective right sections of substantially rounded shape, thereby avoiding any protruding angles between the opening of said slot and the bottom connection zone.

Abstract: A ventilation device for a high pressure turbine rotor in a turbomachine, the turbine comprising upstream and downstream turbine disks fitted with blades, the device comprising a cooling circuit being supplied by a cooling airflow D taken from the back of the combustion chamber. The circuit is such that the airflow passes through orifices formed in an upstream flange of the upstream disk, such that this airflow circulates in the axial direction towards the downstream side between an inner reaming of the upstream disk and a downstream flange of the downstream disk, the device also comprising a labyrinth inserted between the two disks, such that the airflow is divided into a first flow F1 and a second flow circulating on each side of labyrinth towards the blades.

Abstract: The invention relates to a hollow blade comprising an internal cooling passage (24), an open cavity (30) located at the tip (14) of the blade and bounded by an end wall (26) and a rim (28) and cooling channels (32) that connect the said internal cooling passage (24) to the outer face of the pressure wall (16), the said cooling channels (32) being inclined to the pressure wall (16) in such a way that they emerge on the outer face of the pressure wall (16) near the top (28a) of the said rim. By way of feature, a reinforcement of material (34) is present between the rim (28) and the end wall (26) of the cavity (30) along at least one portion of the pressure wall (16), whereby the said rim (28) is widened at its base adjacent to the said end wall (26) in such a way that the cooling channels (32) emerge near the top (28a) of the rim (28) without reducing the mechanical strength of the tip (14) of the blade.

Abstract: The invention relates to ventilation device for a high pressure turbine rotor in a turbomachine, the turbine comprising upstream (3) and downstream (5) turbine disks fitted with blades (4, 6), the device comprising a cooling circuit being supplied by a cooling airflow D taken from the back of the combustion chamber. According to the invention, the circuit is such that the airflow passes through orifices (74) formed in an upstream flange (66) of the upstream disk, such that this airflow circulates in the axial direction towards the downstream side between an inner reaming (48) of the upstream disk and a downstream flange (78) of the downstream disk, the device also comprising a labyrinth (80) inserted between the two disks, such that the airflow is divided into a first flow F1 and a second flow F2 circulating on each side of the labyrinth towards the blades (4, 6).

Abstract: A moving blade for a high pressure turbine of a turbomachine, the blade having at least one cooling circuit comprising at least one cavity extending radially between a tip and a base of the blade, at least one air admission opening at a radial end of the cavity(ies) to feed the cooling circuit(s) with cooing air, and a plurality of slots opening out into the cavity(ies) and opening out into the concave side of the blade between the base and the tip of the blade in a manner that is substantially perpendicular to a longitudinal axis of the blade, a connection zone being provided between a slot closest to the base of the blade and a top surface of a platform defining an inside wall for a stream of combustion gas flowing through the high pressure turbine, and the moving blade further comprising an additional cooling air exhaust slot opening out into said cavity and opening out into said connection zone in line with the trailing edge.

Abstract: A cooling system is disclosed for cooling the platforms of turbine blades fixed to the periphery of a turbine rotor, each turbine blade having an airfoil portion, a platform with opposite longitudinal edges, a root portion affixed to the turbine rotor, and a shank portion connecting the root portion to the platform. Adjacent turbine blades are located such that a longitudinal edge of one platform is adjacent to a longitudinal edge of an adjacent platform. A cavity is formed bounded by a portion of the periphery of the turbine rotor, the shank portions of the adjacent turbine blades, and the platforms of the adjacent turbine blades. A cooling air passage supplies cooling air to the cavity. One or more cooling channels are formed in a side of the platform facing the turbine rotor, each cooling channel having a cooling air collector at an end located adjacent to the air supply passage and communicating with the cavity.