A seal system includes a ceramic component, a metallic component, a silicon-containing layer, and a barrier layer. The ceramic component has a first surface region that defines a first surface roughness. The metallic component is situated adjacent to the first surface region and has a second surface region facing the first surface region. The silicon-containing layer is on the first surface region of the ceramic component and has a contact surface that defines a second surface roughness which is less than the first surface roughness. The barrier layer is on the metallic component and in contact with the silicon-containing layer and serves to limit interaction between silicon of the silicon-containing layer and the metallic component. The barrier layer includes at least one of alumina or MCrAlY.

A method includes forming a ceramic matrix composite component by infiltrating an array of ceramic-based fibers with a ceramic-based matrix; forming a plurality of cooling holes in the ceramic matrix composite component; applying a slurry of particles in a carrier fluid to the ceramic matrix composite component such that the slurry passes through the cooling holes and wicks into the ceramic matrix composite material; and processing the ceramic matrix composite component to remove the carrier fluid, thereby leaving a filler at a wall surface of the plurality of cooling holes. A component is also disclosed.

Disclosed herein is a composite comprising a ceramic matrix composite comprising a ceramic matrix and ceramic fibers; and one or more sacrificial fibers woven into the ceramic matrix composite; where the sacrificial fibers are operative to undergo oxidation or melting upon being subjected to an elevated temperature; and wherein the sacrificial fibers leave cooling holes in the composite preform upon being subjected to oxidation or melting.

A method of forming a component for a gas turbine engine using ceramic matrix composites (CMCs) is provided. The method includes preforming the aerodynamic component into an initial desired shape using the CMCs, executing partial densification of the CMCs, repeating the preforming operations and the executing of the partial densification until a final desired shape of the aerodynamic component is achieved, machining or cutting the CMCs during one or more of the preforming operations and the executing of the partial densification to remove defects from the CMCs and executing a full densification of the CMCs.

The present invention relates to a method of printing a composite material (1), for example polymeric, carbonaceous, siliconic or metallic comprising steps of: i) providing a plurality of bundles (2) of reinforcement fibres (4), wherein the reinforcement fibres (4) have a length in the range 3-50 mm and are in the number of about 1,000-100,000 in each bundle (2); ii) aligning the bundles (2) along a predetermined path (X, X′); iii) incorporating at least part of the bundles (2) into a matrix (6, 8), for example polymeric, carbonaceous, siliconic or metallic, preserving the alignment along said path (X, X′); iv) laying and solidifying at least one layer (8) of the matrix (6, 8) of step iii) to make the composite material (1).

An inter-turbine duct includes a first annular wall with a ceramic composite material and including a first plurality of layers and a second plurality of layers, the first plurality of layers including a slot extending therethrough; and a first vane with a material of a metal alloy or a ceramic material. The first vane has a first end and a flange extending through the slot with the flange extending away from the first end and being retained between the first plurality of layers and the second plurality of layers of the first annular wall.

A nuclear reactor fuel rod is a fuel rod for a light-water reactor. The nuclear reactor fuel rod includes a fuel cladding tube and an end plug, both of which are formed of a silicon carbide material. A bonding portion between the fuel cladding tube and the end plug is formed by brazing with a predetermined metal bonding material interposed, and/or by diffusion bonding. The predetermined metal bonding material has a solidus temperature of 1200° C. or higher. An outer surface of the bonding portion, and a portion of an outer surface of the fuel cladding tube and the end plug, which is adjacent to the outer surface of the bonding portion are covered by bonding-portion coating formed of a predetermined coating metal. The predetermined metal bonding material and the predetermined coating metal have an average linear expansion coefficient which is less than 10 ppm/K.

A system and method for forming a ceramic matrix composite blade track is provided. The method may include stacking a plurality of first plies to form a first porous preform layer, the first plies including a plurality of first ceramic fibers. The method may further include stacking a plurality of second plies to form a second porous preform layer, the second plies including a plurality of second ceramic fibers. The method may further include combining the first porous preform layer and the second porous preform layer to form a unified porous preform. The method may further include forming a structural layer by infiltrating the first porous preform with a first ceramic matrix material, and forming an abradable layer by infiltrating the second porous preform with a second ceramic matrix material.

There is provided a manufacturing method of a fluid flow straightening member having a structure in which disturbance of an air flow does not easily arise. In at least one of outermost layers of an outer circumferential surface or an inner circumferential surface which configures a tubular portion of the fluid flow straightening member, ceramic fibers are oriented in a direction along a plane including a central axis which is surrounded by the tubular portion.

An automated preparation method of a SiC.sub.f/SiC composite flame tube, comprising the following steps: preparing an interface layer for a SiC fiber by a chemical vapor infiltration process, and obtaining the SiC fiber with a continuous interface layer; laying a unidirectional tape on the SiC fiber with the continuous interface layer and winding the SiC fiber with the continuous interface layer to form and obtaining a preform of a net size molding according to a fiber volume and a fiber orientation obtained in a simulation calculation; and adopting a reactive melt infiltration process and the chemical vapor infiltration process successively for a densification and obtaining a high-density SiC.sub.f/SiC composite flame tube in a full intelligent way. The SiC.sub.f/SiC composite flame tube prepared by the present disclosure not only has a high temperature resistance, but also has a low thermal expansion coefficient, high thermal conductivity and high thermal shock resistance.