Abstract: A method of fabricating a turbine engine blade root out of composite material including fiber reinforcement densified by a matrix, the method including making a central fiber strip and two outer fiber strips from three sets of yarn layers interlinked by three-dimensional weaving, passing the two outer strips through the central strip with the two outer strips crossing each other inside the central strip, eliminating the portions of the two outer strips lying outside the central strip by cutting them off, shaping the fiber blank in order to obtain a preform having a main portion forming a blade-root preform integral with two secondary portions forming bearing-plate preforms, and densifying the preform densified by the matrix.

Abstract: A device for attaching blades to a rotor disk of a turbine engine is provided. The device includes: a rotor disk provided at its outer periphery with a plurality of slots, each slot being formed between two adjacent disk teeth and extending axially between front and rear faces of the disk; a plurality of blades, each having a respective root mounted in a slot of the disk; and at least one pin mounted in the rotor disk to pass through the roots of at least two adjacent blades and extending between the front and rear faces of the rotor disk so as to attach the blades to the rotor disk.

Abstract: A method of fabricating a turbine engine blade root out of composite material including fiber reinforcement densified by a matrix, the method including making a central fiber strip and two outer fiber strips from three sets of yarn layers interlinked by three-dimensional weaving, passing the two outer strips through the central strip with the two outer strips crossing each other inside the central strip, eliminating the portions of the two outer strips lying outside the central strip by cutting them off, shaping the fiber blank in order to obtain a preform having a main portion forming a blade-root preform integral with two secondary portions forming bearing-plate preforms, and densifying the preform densified by the matrix.

Abstract: A turbine ring assembly includes a ring support structure and a plurality of ring sectors, each including a single piece of ceramic matrix composite material. Each ring sector includes a first portion forming an annular base with an inside face defining an inside face of the turbine ring and an outside face from which there extends two tab-forming portions including ends that are engaged in housings in the ring support structure. The ring sectors present a section that is substantially ?-shaped and the ends of the tabs are held without radial clearance by the ring support structure. The tabs can have a free length in meridian section that is not less than three times their mean width.

Abstract: A method of fabricating a composite-material turbomachine blade having platform incorporated therein includes separately making a blade platform element that includes rigidified fiber reinforcement and that has a shape close to that of a platform of the blade to be fabricated, with at least one opening being formed through the platform element. The opening has the shape of the profile of the airfoil of the blade to be fabricated. Three-dimensional weaving is used to make a flexible fiber blank as a single piece that includes blade airfoil-and-root preform portions. The platform element is engaged, via its opening, on the flexible fiber blank while deforming it so as to assemble the platform element with the fiber blank. The fiber blank is shaped together with the platform element assembled thereon to obtain a blade preform of a shape that is close to the shape of the blade to be fabricated. After shaping, the blade preform is consolidated in its shape in a shaper.

Abstract: The invention provides a device for attaching blades to a rotor disk of a turbine engine, comprising: a rotor disk provided at its outer periphery with a plurality of slots, each formed between two adjacent disk teeth and extending axially between front and rear faces of the disk; a plurality of blades, each having a respective root mounted in a slot of the disk; and at least one pin mounted in the rotor disk to pass through the roots of at least two adjacent blades and extending between the front and rear faces of the rotor disk so as to attach the blades to the rotor disk.

Abstract: A method of fabricating a composite-material turbomachine blade having platform incorporated therein includes separately making a blade platform element that comprises rigidified fiber reinforcement and that has a shape close to that of a platform of the blade to be fabricated, with at least one opening being formed through the platform element. The opening has the shape of the profile of the airfoil of the blade to be fabricated. Three-dimensional weaving is used to make a flexible fiber blank as a single piece that includes blade airfoil-and-root preform portions. The platform element is engaged, via its opening, on the flexible fiber blank while deforming it so as to assemble the platform element with the fiber blank. The fiber blank is shaped together with the platform element assembled thereon to obtain a blade preform of a shape that is close to the shape of the blade to be fabricated. After shaping, the blade preform is consolidated in its shape in a shaper.

Abstract: A turbine ring assembly includes a ring support structure and a plurality of ring sectors, each including a single piece of ceramic matrix composite material. Each ring sector includes a first portion forming an annular base with an inside face defining an inside face of the turbine ring and an outside face from which there extends two tab-forming portions including ends that are engaged in housings in the ring support structure. The ring sectors present a section that is substantially ?-shaped and the ends of the tabs are held without radial clearance by the ring support structure. The tabs can have a free length in meridian section that is not less than three times their mean width.

Abstract: The invention relates to a turbomachine blade made of composite material including fiber reinforcement, the blade being obtained by three-dimensionally weaving yarns and densifying with a matrix. The blade comprises a single piece constituting both the airfoil and the root of the blade. The blade root has two substantially plane opposite side flanks that are formed in register with the pressure side and suction side surfaces respectively of the airfoil and it is clamped between two metal plates that are fastened against the side flanks of the root.