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.

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.

The disclosure describes articles having coating systems configured to inhibit or prevent crystallization of TGO at the operating temperature of the article. An article includes a substrate defining a surface; a bond coat on the surface of the substrate; a coating layer that includes a boron dopant configured to inhibit crystallization of amorphous silicon dioxide thermally grown oxide on the bond coat at an operating temperature of the article. By inhibiting or preventing TGO crystallization, the described coating systems may increase a useable life of the component.

A ceramic matrix composite component and method of fabrication including a plurality of longitudinally extending ceramic matrix composite plies in a stacked configuration forming a densified body and one or more elongate functional features formed therein and in alignment with the plurality of longitudinally extending ceramic matrix composite plies. Each of the elongate functional features includes an inlet configured to be in fluid communication with a flow of cooling fluid from a fluid source. One or more bores cut through the plurality of ceramic matrix composite plies from at least one of the one or more elongate functional features to an outlet proximate to an outer surface of the ceramic matrix composite component. One or more film cooling throughholes cut through the ceramic matrix composite plies from an inner surface of the ceramic matrix composite component to an outlet proximate to the outer surface of the ceramic matrix composite component.

A ceramic matrix composite component and method of fabrication including a plurality of longitudinally extending ceramic matrix composite plies in a stacked configuration forming a densified body and one or more elongate functional features formed therein and in alignment with the plurality of longitudinally extending ceramic matrix composite plies. Each of the elongate functional features includes an inlet configured to be in fluid communication with a flow of cooling fluid from a fluid source. One or more bores cut through the plurality of ceramic matrix composite plies from at least one of the one or more elongate functional features to an outlet proximate to an outer surface of the ceramic matrix composite component. One or more film cooling throughholes cut through the ceramic matrix composite plies from an inner surface of the ceramic matrix composite component to an outlet proximate to the outer surface of the ceramic matrix composite component.

A combustion assembly for a gas turbine engine may be provided. The combustion assembly may include a ceramic matrix composite combustor shell, which may include a chamber defined by a wall of the ceramic matrix composite combustor shell, and the ceramic matrix composite combustor shell may include a ceramic matrix composite chute integral with the ceramic matrix composite combustor shell. The ceramic matrix composite chute may extend towards a midline of the chamber. A method for fabricating a ceramic matrix composite chute may be provided. At least one chute may be woven in three dimensions into a ceramic preform. A layup tool may be inserted into the chute. The chute may be enlarged with the layup tool. The ceramic preform may be formed into a ceramic matrix composite body, which includes a combustor shell and the chute.

A combustion assembly for a gas turbine engine may be provided. The combustion assembly may include a ceramic matrix composite combustor shell, which may include a chamber defined by a wall of the ceramic matrix composite combustor shell, and the ceramic matrix composite combustor shell may include a ceramic matrix composite chute integral with the ceramic matrix composite combustor shell. The ceramic matrix composite chute may extend towards a midline of the chamber. A method for fabricating a ceramic matrix composite chute may be provided. At least one chute may be woven in three dimensions into a ceramic preform. A layup tool may be inserted into the chute. The chute may be enlarged with the layup tool. The ceramic preform may be formed into a ceramic matrix composite body, which includes a combustor shell and the chute.

A blade made of composite material includes a fibrous reinforcement and an at least partially ceramic matrix, wherein the fibrous reinforcement includes a first structural portion formed by three-dimensional or multilayer weaving, and a second functional portion, distinct from the first portion, including short fibers.

The invention relates to a refractory container 1 for use in a furnace for heat treatment of workpieces, comprising a mat 5 of long fibers that are embedded in a ceramic shell, with the mat 5 being shaped into a container that forms a receiving space for workpieces, and to a green body of such a container 1. Furthermore, advantageous uses of the container 1 as well as a method for manufacturing a green body or container 1 according to the invention are specified.

The invention relates to a refractory container 1 for use in a furnace for heat treatment of workpieces, comprising a mat 5 of long fibers that are embedded in a ceramic shell, with the mat 5 being shaped into a container that forms a receiving space for workpieces, and to a green body of such a container 1. Furthermore, advantageous uses of the container 1 as well as a method for manufacturing a green body or container 1 according to the invention are specified.