Abstract: Blade of a turbomachine turbine including a airfoil extending along a first direction between an internal end and an external end, a base secured to said internal end, and a root secured to said external end and extending, along a second direction perpendicular to said first direction, between an upstream edge, and a downstream edge and, along a third direction orthogonal to the first and second directions, between first and second lateral edges, the first side edge having, in a plane including the second and third directions, a shape complementary to that of the second lateral edge. The first lateral edge includes a first portion extending from the upstream edge, and a second portion externally protruding along the third direction at an acute angle with the first portion.

Abstract: A method optimizing a composite material blade profile for a rotor wheel of a turbine engine, and a blade including a tang compensated by the method. The method includes: compensating a blade airfoil by subdividing the airfoil into slices, and for each airfoil slice and a predetermined rotation speed of a disk of the wheel, calculating centrifugal force applied to the slice, calculating an aerodynamic force moment acting on a bottom section of the slice, and calculating shift values to be applied to a center of gravity of the slice to cancel the aerodynamic force moment; and compensating the blade tang by calculating centrifugal force applied to a blade portion situated beyond the airfoil neck, calculating an aerodynamic force moment acting on a bottom section of the blade tang, and calculating shift values to be applied to a center of gravity of the blade tang to cancel the aerodynamic force moment.

Abstract: A device for connecting a fixed turbine engine portion and a distributor foot of a turbine engine turbine is provided. The device includes a ring-shaped body adapted so as to be connected and secured to the fixed turbine engine portion, and two ring-shaped upstream and downstream brackets secured to the body, both brackets being adapted so as to clamp the foot of the distributor. At least one bracket is interrupted by forming an expansion or retraction slot, the slot allowing an expansion of the bracket tending to close the slot or retraction of the bracket tending to further open the slot, under the effect of a difference in internal temperatures of the device.

Abstract: A turbine for a gas turbine engine comprising at least one turbine stator and one turbine rotor, said turbine stator comprising at least one inner annular platform, said inner platform comprising a radial wall delimiting at least one cavity between the turbine stator and the turbine rotor, wherein the turbine rotor comprises at least one elongate element positioned substantially axially and defining a sealing baffle in said cavity, and in that the turbine stator comprises at least one element made of abradable material designed to engage with said elongate element of the turbine rotor so as to form a labyrinth seal.

Abstract: A sealing device for a nozzle of a turbomachine turbine including a turbine rotor. The turbine nozzle includes at least one inner annular platform. The turbine rotor includes a downstream spoiler disposed substantially axially. The sealing device includes at least one sealing sheet disposed, radially, between the inner face of the inner platform and the downstream spoiler of the rotor of the turbine so as to form an overlap clearance.

Abstract: A vibration damper between outer platforms of adjacent composite-material blades of a turbine engine rotor wheel, the damper including a peg having a substantially spherical portion at each of its two ends, and two hollow inserts for being received in tangential cavities that are provided facing each other in outer platforms of two adjacent composite-material blades of a turbine engine rotor wheel, each spherical portion of the peg coming to bear with point contact against the inside of one of the inserts.

Abstract: A vibration damper between outer platforms of adjacent composite-material blades of a rotor wheel of a turbine engine, the damper including a strip for inserting lengthwise in tangential cavities that are formed facing each other in the outer platforms of two adjacent composite-material blades of a turbine engine rotor wheel.

Abstract: A sealing device for a nozzle of a turbomachine turbine including a turbine rotor. The turbine nozzle includes at least one inner annular platform. The turbine rotor includes a downstream spoiler disposed substantially axially. The sealing device includes at least one sealing sheet disposed, radially, between the inner face of the inner platform and the downstream spoiler of the rotor of the turbine so as to form an overlap clearance.

Abstract: A turbine for a gas turbine engine comprising at least one turbine stator and one turbine rotor, said turbine stator comprising at least one inner annular platform, said inner platform comprising a radial wall delimiting at least one cavity between the turbine stator and the turbine rotor, wherein the turbine rotor comprises at least one elongate element positioned substantially axially and defining a sealing baffle in said cavity, and in that the turbine stator comprises at least one element made of abradable material designed to engage with said elongate element of the turbine rotor so as to form a labyrinth seal.

Abstract: A turbine nozzle for a turbomachine, including inner and outer annular platforms connected together by vanes, the inner platform carrying annular elements of abradable material co-operating with annular wipers of a rotor of the turbomachine to form a labyrinth seal, these elements of abradable material being carried by annular sheet-metal sectors of substantially L-, S-, or C-shaped section that are fastened by brazing or welding at their outer peripheries to the inner platform and at their inner peripheries to the elements of abradable material.

Abstract: A method optimizing a composite material blade profile for a rotor wheel of a turbine engine, and a blade including a tang compensated by the method. The method includes: compensating a blade airfoil by subdividing the airfoil into slices, and for each airfoil slice and a predetermined rotation speed of a disk of the wheel, calculating centrifugal force applied to the slice, calculating an aerodynamic force moment acting on a bottom section of the slice, and calculating shift values to be applied to a center of gravity of the slice to cancel the aerodynamic force moment; and compensating the blade tang by calculating centrifugal force applied to a blade portion situated beyond the airfoil neck, calculating an aerodynamic force moment acting on a bottom section of the blade tang, and calculating shift values to be applied to a center of gravity of the blade tang to cancel the aerodynamic force moment.

Abstract: A vibration damper between outer platforms of adjacent composite-material blades of a rotor wheel of a turbine engine, the damper including a strip for inserting lengthwise in tangential cavities that are formed facing each other in the outer platforms of two adjacent composite-material blades of a turbine engine rotor wheel.

Abstract: A vibration damper between outer platforms of adjacent composite-material blades of a turbine engine rotor wheel, the damper including a peg having a substantially spherical portion at each of its two ends, and two hollow inserts for being received in tangential cavities that are provided facing each other in outer platforms of two adjacent composite-material blades of a turbine engine rotor wheel, each spherical portion of the peg coming to bear with point contact against the inside of one of the inserts.

Abstract: A rotor wheel of a turbine engine includes a plurality of CMC blades each having a first portion constituting a blade airfoil and root and made as a single piece with a second portion forming an outer platform. The blades are held under twisting prestress by mutual engagement via contact zones between the outer platforms of adjacent blades, and the contact zones that are situated on opposite sides of the outer platform of a blade are defined by at least one insert that is integrated in the outer platform and that is, for example, made of a carbon-based material.

Abstract: A sectorized nozzle for a turbomachine, the nozzle being made up of cylindrical sectors and comprising two annular platforms interconnected by substantially radial vanes, together with an annular rail for supporting elements of abradable material, each inner platform having longitudinally-extending edges that are V-shaped, and each rail sector having, on at least one of its sides, means for bearing axially on corresponding means provided on an adjacent nozzle sector.

Abstract: The monocrystalline turbomachine blade according to the invention that is cast and directionally solidified, is disclosed. The blade includes an airfoil with a leading edge, a pressure face, a suction face, a trailing edge, a skeleton and having a longitudinal axis, the faces and having a neck line, respectively a pressure face neck and a suction face neck relative to the adjacent blade in the turbomachine rotor of which it forms an element; an endpiece of the airfoil, such as a heel or a platform, having an airfoil end face, on the stream side, forming an angle with the axis ZZ; and a connection zone between the airfoil and the airfoil end face. The connection zone forms a fattening of the airfoil. The connection zone extends about the leading edge between a point P1 situated on the suction face of the airfoil upstream of the suction face neck and a point P3 situated on the pressure face of the airfoil upstream of the pressure face neck.

Abstract: A turbine nozzle for a turbomachine, including inner and outer annular platforms connected together by vanes, the inner platform carrying annular elements of abradable material co-operating with annular wipers of a rotor of the turbomachine to form a labyrinth seal, these elements of abradable material being carried by annular sheet-metal sectors of substantially L-, S-, or C-shaped section that are fastened by brazing or welding at their outer peripheries to the inner platform and at their inner peripheries to the elements of abradable material.

Abstract: A bladed stator sector for a turbo-engine reduces the occurrence of thermally-induced stress cracks in stator blades by increasing the flexibility of the sectors by using one or more cutouts. The stator sector includes at least one stator blade between inner and outer platforms and at least one flange on one or more of the platforms. Each flange has a first end portion fixed to one of the platforms and a second end portion that is not fixed to either of the platforms. The one or more cutouts may be located on the flange and may be non-opening.

Abstract: A sectorized nozzle for a turbomachine, the nozzle being made up of cylindrical sectors and comprising two annular platforms interconnected by substantially radial vanes, together with an annular rail for supporting elements of abradable material, each inner platform having longitudinally-extending edges that are V-shaped, and each rail sector having, on at least one of its sides, means for bearing axially on corresponding means provided on an adjacent nozzle sector.

Abstract: The monocrystalline turbomachine blade according to the invention that is cast and directionally solidified, comprising: an airfoil with a leading edge, a pressure face, a suction face, a trailing edge, a skeleton and having a longitudinal axis, the faces and having a neck line, respectively a pressure face neck and a suction face neck relative to the adjacent blade in the turbomachine rotor of which it forms an element, an endpiece of the airfoil, such as a heel or a platform, having an airfoil end face, on the stream side, forming an angle with the axis ZZ and a connection zone between the airfoil and said airfoil end face, said connection zone forming a fattening of the airfoil, is characterized in that said connection zone extends about the leading edge between a point P1 situated on the suction face of the airfoil upstream of the suction face neck and a point P3 situated on the pressure face of the airfoil upstream of the pressure face neck.