FIELD: machine building.
SUBSTANCE: gas turbine engine vane comprises a blade, a first platform at a longitudinal end of the blade and at least one functional element. Platform has an inner face delimiting vein and an outer face opposite the inner face. Functional element extends from the outer face of the first platform connecting to the outer face in a circumferential direction. Vane is an integral blank made of composite material comprising a multi-layer woven fibrous reinforcement densified by a matrix. Fibrous reinforcement is an integral blank with the first portion forming the reinforcement for the blade of the vane, and the second portion forming the reinforcement for the first platform of the vane and for at least one functional element. Second portion of the reinforcement includes a set of layers of threads linked together by weaving, apart at a separation zone between the one or each reinforcing functional element and the reinforcing first platform. In the manufacture of said vane, the fibrous preform is made as an integral blank by multi-weaving. Fibrous blank is formed to produce a fibrous preform as an integral blank comprising a first portion forming a preform for a blade of the vane and a second portion forming a preform for the first platform and a preform for at least one functional element. Densifying the fibrous preform with a matrix to obtain a composite material vane having a fibrous reinforcement formed by the preform and densified by the matrix and forming a single piece comprising a blade, first platform and at least one functional element. Second portion of the preform comprises a set of layers of threads linked to each other by weaving with at least one unbound zone located therein, allowing the deployment of the preform of the one or each functional element relative to the preform of the first platform. Portion of the fibrous preform corresponding to the second portion of the preform includes one or more layers of threads taken from the portion of the fibrous preform corresponding to the preform of the blade at one or more locations in the longitudinal direction. Preform of the blade has a variable thickness in the longitudinal direction. According to other embodiments of the vane and the corresponding embodiments of the manufacture method, a vane is a rotor or stator vane and comprises on the platform ridges, mounting hooks or a supporting element for abradable coating, respectively. Other inventions of the group relate to a turbine wheel or gas turbine engine compressor comprising said vanes made of composite material with a ceramic or organic matrix. Another invention of the group relates to a gas turbine engine comprising the above-mentioned rotor wheel.
EFFECT: group of inventions provides the simplified method for manufacturing a fibrous preform of a gas turbine engine vane, reduced risk of thread breakage and simplified design of machine tools for preform forming.
23 cl, 36 dwg
