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 π-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.

Turbine ring assembly

Fibrous preform for a turbo machine blade, which preform is obtained by one-piece three-dimensional weaving. According to the invention, the preform comprises a first longitudinal portion (41) able to form a blade root, a second longitudinal portion (42) extending the first longitudinal portion and able to form a blade section, and a first transverse portion (51) extending transversely from the junction between the first and second longitudinal portions (41, 42) and able to form a first platform.

Monobloc preform and blade for turbo machine

The invention relates to a method for producing a fibrous preform for the manufacture of a turbomachine blade made of composite material, the method involving using three-dimensional weaving to create a fibrous rough form (100) in a single piece with layers of longitudinal threads (c1 to c24) joined together by threads of layers of transverse threads (t1 to t24), and shaping the fibrous rough form to obtain a fibrous preform in a single piece having a part that forms the aerofoil preform and at least a part that forms a platform preform. During the course of the weaving process, the threads (c5 to c7) of a first group of longitudinal threads are led out from the fibrous rough form on the side of one of the lateral faces (110a) of the rough form to form a part (120) that corresponds to a preform of a blade platform, and threads (c3 and c4) of a second group of longitudinal threads are injected into the fibrous rough form with mutual criss-crossing between the threads of the first group and the threads of the second group. The invention also relates to a preform obtained using this method.

Fibrous preform of a turbomachine blade made of composite material with in-built platform, and method of producing same

According to the invention, a fibrous blank is formed by means of multilayer weaving, said blank having a longitudinal direction corresponding to that of the vane to be produced and the thickness thereof comprising a first portion (102) with multiple interwoven layers of yarns, a second woven portion and a third woven portion. The first portion is located between the second portion and the third portion and it is interwoven therewith along only part of the longitudinal dimension thereof. A preform of the vane to be produced is formed by unfolding, on both sides of the first portion, segments (104a, 106a, 104b, 106b) of the second and third portions that are not connected to the first portion, by shaping the first portion in order to form a preform part for the blade of the vane to be produced, and by shaping the unfolded segments of the second and third portions in order to form preform parts for the internal and external platforms of the vane to be produced, and the vane preform is densified using a matrix in order to obtain a vane made from composite material and including integrated platforms.

Method for producing a turbomachine vane made from composite material and including integrated platforms

A method for fabricating turbine engine blade or vane made of composite material includes: performing three-dimensional weaving to make a single-piece fiber blank; shaping the fiber blank to obtain a single-piece fiber preform having a first portion forming a preform for at least a blade/vane airfoil, at least one second portion forming a preform for an inner part of a blade/vane inner platform or for an outer part of a blade/vane outer platform, and at least one third portion forming a preform for an outer part of a blade/vane inner platform or for an inner part of a blade/vane outer platform; and densifying the fiber preform with a matrix to obtain a composite material blade, and forming a single piece with an inner and/or outer platform(s) incorporated therein.

Turbine engine blade or vane made of composite material, turbine nozzle or compressor stator incorporating such vanes and method of fabricating same

The invention relates to a method for producing a turbomachine blade from a composite material, having an integrated platform and/or shroud. The method comprises the following steps: the three-dimensional weaving of a flexible fibrous blank as a single part comprising blade vane (220) and root (230) preform portions; the separate production of a blade platform (400) or blade shroud (500) element comprising a stiffened fibrous reinforcement, whereby at least one opening in the shape of the vane profile of the blade to be produced is formed in the platform or shroud element; the mounting of the platform or shroud element, by means of the opening therein, on the flexible fibrous blank, with deformation of the latter, for assembly with the fibrous blank; the forming of the fibrous blank with the assembled platform or shroud element in order to obtain a preform (200) having a shape similar to that of the blade to be produced; the setting of the shape of the preform in a former; and the introduction of a matrix in the preform in order to obtain a blade made from a composite material and having an integrated platform or shroud.

Method for producing a turbomachine blade made from a composite material

Un procede de fabrication d'une aube de turbomachine en materiau composite a plate-forme et/ou talon integre comprend les etapes de : - realisation par tissage tridimensionnel d'une ebauche fibreuse souple en une seule piece comprenant des parties de preforme de pale (220) et de pied (230) d'aube, - realisation separee d'un element de plate-forme d'aube (400) ou talon d'aube (500) comprenant un renfort fibreux rigidifie, au moins une ouverture ayant une forme de profil de pale de l'aube a fabriquer etant formee dans l'element de plate-forme ou talon, - engagement de l'element de plate-forme ou talon par son ouverture sur l'ebauche fibreuse souple, avec deformation de celle-ci, pour assemblage avec l'ebauche fibreuse, - mise en forme de l'ebauche fibreuse avec l'element de plate-forme ou talon assemble pour obtenir une preforme (200) ayant une forme voisine de celle de l'aube a fabriquer, - consolidation de la preforme dans sa forme dans un conformateur, et - introduction finale d'une matrice dans la preforme pour obtenir une aube en materiau composite a plate-forme ou talon integre.

Procede de fabrication d'une aube de turbomachine en materiau composite

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.

Composite material turbomachine blade with a reinforced root

L'ensemble d'anneau de turbine comprend une pluralite de secteurs d'anneau (10) en une seule piece en materiau composite a matrice ceramique et une structure de support d'anneau, chaque secteur d'anneau ayant une premiere partie (12) formant base annulaire avec une face interne definissant la face interne de l'anneau de turbine et une face externe a partir de laquelle s'etendent deux parties formant pattes (14, 16) dont les extremites sont engagees dans des logements de la structure de support d'anneau. Les secteurs d'anneau (10) sont a section sensiblement en forme de π et les extremites (14a, 16a) des pattes (14, 16) sont maintenues sans jeu radial par la structure de support d'anneau. De preference, les pattes (14, 16) ont, en section meridienne, une longueur libre au moins egale a 3 fois leur largeur moyenne.

Hubert Illand

Papers

Turbine ring assembly

Method for producing a turbomachine blade made from a composite material

Procede de fabrication d'une aube de turbomachine en materiau composite

Composite material turbomachine blade with a reinforced root

Ensemble d'anneau de turbine