# US 11,306,598 B2 · Method for manufacturing a turbine engine vane made of a composite material, resulting vane and turbine engine including same > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 11,306,598 B2 - Document ID: US11306598B2 - Status: Granted - Kind: B2 - Application number: 16/676,551 - Filed: 2019-11-07 - Published: 2020-07-23 - Granted: 2022-04-19 - Earliest claimed: 2014-05-22 - Assignees: Safran Aircraft Engines - Applicants: Safran Aircraft Engines - Inventors: Clément Roussille; Jéremy Blachier; Marie Lefebvre - Web page: https://patentgrep.com/patent/US11306598B2 ## CPC - F01D 5/282: {Selecting composite materials, e.g. blades with reinforcing filaments} - C04B 35/565: based on silicon carbide - C04B 35/71: Ceramic products containing macroscopic reinforcing agents (C04B35/66 takes precedence {; infiltration of a porous ceramic matrix with a material forming a non-ceramic phase C04B41/00, reaction infiltration with Si in order to form SiC C04B35/573, in order to form Si3N4 C04B35/591}) - C04B 35/80: Fibres, filaments, whiskers, platelets, or the like - C08J 5/042: {with carbon fibres} - C08J 5/043: {with glass fibres} - D03D 25/005: {Three-dimensional woven fabrics} - F01D 5/225: {by shrouding} - F01D 5/284: {Selection of ceramic materials} - F01D 9/02: Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} - F04D 29/324: {Blades} - F04D 29/542: {Bladed diffusers (fixing blades to stators F01D9/042)} - B29B 11/16: comprising fillers or reinforcement {(non-woven fabrics per se D04H1/00, D04H3/00)} - C04B 2235/48: Organic compounds becoming part of a ceramic after heat treatment, e.g. carbonising phenol resins - C04B 2235/5244: Silicon carbide - C04B 2235/5252: having a specific pre-form - C04B 2235/5256: Two-dimensional, e.g. woven structures - C04B 2235/5268: Orientation of the fibers - C04B 2235/614: Gas infiltration of green bodies or pre-forms - C04B 2235/616: Liquid infiltration of green bodies or pre-forms - C08J 2400/00: Characterised by the use of unspecified polymers - F01D 11/122: {with erodable or abradable material (blades having cutting or grinding tips F01D5/20)} - F05D 2220/30: in turbines - F05D 2230/50: Building or constructing in particular ways - F05D 2240/80: Platforms for stationary or moving blades - F05D 2300/6033: Ceramic matrix composites [CMC] - F05D 2300/6034: Orientation of fibres, weaving, ply angle - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D) - C04B: LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE {(roofing granules E04D7/005)}; CERAMICS (devitrified glass-ceramics C03C10/00); REFRACTORIES; TREATMENT OF NATURAL STONE - C08J: WORKING-UP; GENERAL PROCESSES OF COMPOUNDING; AFTER-TREATMENT NOT COVERED BY SUBCLASSES C08B, C08C, C08F, C08G or C08H (working, e.g. shaping, of plastics B29) - D03D: WOVEN FABRICS; METHODS OF WEAVING; LOOMS - F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02) - B29B: PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract The invention relates to a method of fabricating a turbine engine blade out of composite material comprising fiber reinforcement densified by a matrix, the blade comprising an airfoil, a platform situated at a longitudinal end of the airfoil, and at least one functional element projecting from the outside face of the platform. The method comprises: making a single-piece fiber blank by multilayer weaving; shaping the fiber blank to obtain a single-piece fiber preform having a first portion (302) forming a preform for the blade airfoil (320) and a second portion (314) forming a preform for the platform (340) and at least one preform for a functional element (352; 354); and densifying the fiber preform with a matrix. The second preform portion comprises a set of yarn layers interlinked by weaving with at least one zone of non-interlinking being provided to make it possible to deploy the functional element preform relative to the first platform preform. ## Claims ### Claim 1 A turbine engine blade comprising an airfoil, a first platform situated at a longitudinal end of the airfoil and having an inside face defining a flow passage and an outside face opposite from the inside face, and at least one functional element extending from the outside face of the first platform and connecting with said outside face in a direction that is substantially circumferential; the blade being a single piece of composite material comprising multilayer woven fiber reinforcement densified by a matrix; and the fiber reinforcement being a single piece with a first portion forming reinforcement for the airfoil and a second portion forming reinforcement for the first blade platform and for the at least one functional element; in which blade the second portion of the fiber reinforcement comprises a set of yarn layers all interlinked by weaving, apart from in a separation zone between the reinforcement for the or each functional element and the reinforcement for the first platform, wherein the separation zone is formed during the weaving of the set of yarn layers. ### Claim 2 (depends on 1) A blade according to claim 1, in which the set of yarn layers of the second reinforcement portion includes a group of yarn layers in common with the airfoil reinforcement. ### Claim 3 (depends on 1) A turbine or compressor wheel for a turbine engine and including blades according to claim 1 made of ceramic matrix composite material. ### Claim 4 (depends on 3) A turbine engine having at least one turbine or compressor rotor wheel according to claim 3. ### Claim 5 (depends on 1) A turbine engine compressor wheel including turbine engine blades according to claim 1 made of organic matrix composite material. ### Claim 6 (depends on 5) A turbine engine having at least one turbine or compressor rotor wheel according to claim 5. ### Claim 7 (depends on 1) The turbine engine blade of claim 1, wherein the fiber reinforcement is configured such that the airfoil is solid with respect to a transverse cross-sectional area. ### Claim 8 A turbine engine rotor blade comprising an airfoil, an outer platform forming a blade head situated at a longitudinal end of the airfoil and having an inside face defining a flow passage and an outside face opposite from the inside face, and head wipers extending from the outside face of the head and connecting with said outside face in a direction that is substantially circumferential; the blade being a single piece of composite material comprising multilayer woven fiber reinforcement densified by a matrix; and the fiber reinforcement being a single piece with a first portion forming reinforcement for the airfoil and a second portion forming reinforcement for the head and reinforcement for the head wipers; in which blade the second portion of the fiber reinforcement comprises a set of yarn layers all interlinked by weaving, apart from in separation zones between the reinforcement for the head wipers and the reinforcement for the head, wherein the separation zones are formed during the weaving of the set of yarn layers. ### Claim 9 (depends on 8) A blade according to claim 8, in which the set of yarn layers of the second portion of the fiber reinforcement includes a group of yarn layers taken from the first portion of the fiber reinforcement. ### Claim 10 (depends on 8) A turbine or compressor wheel for a turbine engine and including blades according to claim 8 made of ceramic matrix composite material. ### Claim 11 (depends on 8) A turbine engine compressor wheel including blades according to claim 8 made of organic matrix composite material. ### Claim 12 A turbine engine stator blade comprising an airfoil, a first platform situated at a longitudinal end of the airfoil and having an inside face defining a flow passage and an outside face opposite from the inside face, and blade mounting hooks extending from the outside face of the first platform and connecting with said outside face in a direction that is substantially circumferential; the blade being a single piece of composite material comprising multilayer woven fiber reinforcement densified by a matrix; and the fiber reinforcement being a single piece with a first portion forming reinforcement for the airfoil and a second portion forming reinforcement for the first platform and reinforcement for the mounting hooks; in which blade the second fiber reinforcement portion comprises a set of yarn layers all interlinked by weaving, apart from in separation zones between the reinforcement for the mounting hooks and the reinforcement for the first platform, wherein the separation zones are formed during the weaving of the set of yarn layers. ### Claim 13 (depends on 12) A blade according to claim 12, in which the set of yarn layers of the second reinforcement portion includes a group of yarn layers in common with the airfoil reinforcement. ### Claim 14 (depends on 12) A turbine or compressor wheel for a turbine engine and including blades according to claim 12 made of ceramic matrix composite material. ### Claim 15 (depends on 12) A turbine engine compressor wheel including blades according to claim 12 made of organic matrix composite material. ### Claim 16 A turbine engine stator blade comprising an airfoil, a first platform situated at a longitudinal end of the airfoil and having an inside face defining a flow passage and an outside face opposite from the inside face, and at least one abradable support element extending from the outside face of the first platform and connecting with said outside face in a direction that is substantially circumferential; the blade being a single piece of composite material comprising multilayer woven fiber reinforcement densified by a matrix; and the fiber reinforcement being a single piece with a first portion forming reinforcement for the airfoil and a second portion forming reinforcement for the first platform and reinforcement for the at least one abradable support element; in which blade the second fiber reinforcement portion comprises a set of yarn layers all interlinked by weaving, apart from in separation zones between the reinforcement for the or each abradable support element and the reinforcement for the first platform, wherein the separation zones are formed during the weaving of the set of yarn layers. ### Claim 17 (depends on 16) A turbine or compressor wheel for a turbine engine and including blades according to claim 16 made of ceramic matrix composite material. ### Claim 18 (depends on 16) A turbine engine compressor wheel including blades according to claim 16 made of organic matrix composite material.