One aspect of the present disclosure includes a turbine vane assembly comprising a vane made from ceramic matrix composite material having an outer wall extending between a leading edge and a trailing edge and between a first end and an opposing second end; an endwall made at least partially from a ceramic matrix composite material configured to engage the first end of the vane; and a retaining region including corresponding bi-cast grooves formed adjacent the first end of the vane and a receiving aperture formed in the endwall; wherein a bond is formed in the retaining region to join the vane and endwall together.

A fireproof structure includes: a first heat-absorbing material that includes an inorganic porous formed body that has absorbed water, or a second heat-absorbing material that includes particles that include magnesium phosphate hydrate and a binder; and a fibrous heat-insulating material that includes inorganic fibers having a shrinkage ratio of 5% or less when allowed to stand at 1,100° C. for 24 hours.

Provided is a structure including a first member (2); a second member (3) disposed opposite to the first member (2); and a glass layer (4) disposed between the first member (2) and the second member (3) so as to bond the first member (2) and the second member (3). A glass transition point of the glass layer (4) is lower than a temperature of the glass layer (4) under operation. In the glass layer (4), at least either of ceramic and metallic particles 4b, 4c is dispersed. In a temperature region lower than the glass transition point of the glass layer (4), a thermal expansion coefficient thereof falls in between thermal expansion coefficients of the first member (2) and the second member (3). This allows thermal strain caused within the structure (1) to be reduced when the structure (1) is operated at a higher temperature than a room temperature.

Single-airfoil vanes each having an inner platform, an outer platform, and an airfoil are obtained by three-dimensionally weaving a fiber blank in a single piece, by shaping the fiber blank to obtain a single-piece fiber preform, and by densifying the preform with a matrix to obtain a vane of composite material forming a single piece with inner and outer platforms incorporated therein. A plurality of vanes is assembled together at an intermediate stage of densification to form a multi-airfoil composite material guide vane sector for a turbine nozzle or a compressor diffuser and the assembled-together vanes are bonded together.

A hybrid component is provided including a plurality of laminates stacked on one another to define a stacked laminate structure. The laminates include a ceramic matrix composite material having certain features, such as a matrix porosity characteristic and a hierarchical fiber architecture, and at least one opening defined therein. A metal support structure may be arranged through each opening so as to extend through the stacked laminate structure.

The present disclosure relates to a method of fabricating a ceramic composite components. The method may include providing at least a first layer of reinforcing fiber material which may be a pre-impregnated fiber. An additively manufactured component may be provided on or near the first layer. A second layer of reinforcing fiber, which may be a pre-impregnated fiber may be formed on top the additively manufactured component. A precursor is densified to consolidates at least the first and second layer into a densified composite, wherein the additively manufactured material defines at least one cooling passage in the densified composite component.

Provided is a ceramic member in which the difference in thermal expansion coefficient between an insulating ceramic material and an electrically conductive ceramic material is extremely small and therefore any mismatch caused in association with this difference in thermal expansion coefficient does not occur, and which does not undergo any failure such as breakage, cracking, detachment or destruction. The ceramic member (1) includes an electrically conductive ceramic material (2) which contains yttrium oxide as the main component and additionally contains a fibrous electrically conductive substance such as carbon nanotubes in an amount of 0.1 to 3 vol % inclusive and an insulation ceramic material (3) which contains yttrium oxide as the main component, wherein the electrically conductive ceramic material (2) and the insulation ceramic material (3) are adhered to each other in an integrated manner through an adhesive layer (4) which includes an inorganic adhesive material.

A method is described for assembling at least two parts made of silicon carbide based materials by non-reactive brazing in an oxidizing atmosphere, each of the parts comprising a surface to be assembled, wherein the parts are placed in contact with a non-reactive brazing composition, the assembly formed by the parts and the brazing composition is heated to a brazing temperature sufficient for completely or at least partially melting the brazing composition, or rendering the brazing composition viscous, and the parts and the brazing composition are cooled so as to form, after cooling the latter to ambient temperature, a moderately refractory joint. The non-reactive brazing composition is a composition A consisting of silica (SiO.sub.2), alumina (Al.sub.2O.sub.3), and calcium oxide (CaO), or a composition B consisting of alumina (Al.sub.2O.sub.3), calcium oxide (CaO), and magnesium oxide (MgO), and, before heating the assembly formed by the parts and the brazing composition to the brazing temperature, a supply of silicon in a non-oxidized form is carried out on the surfaces to be assembled of the parts to be assembled, and/or on the surface layers comprising the surfaces to be assembled of the parts to be assembled, and/or in the brazing composition.

Disclosed are an inorganic nanofiber characterized in that the average fiber diameter is 2 μm or less, the average fiber length is 200 μm or less, and the CV value of the fiber length is 0.7 or less; and a method of manufacturing the same. In the manufacturing method, an inorganic nanofiber sheet consisting of inorganic nanofibers having an average fiber diameter of 2 μm or less is formed by electrospinning, and then, the inorganic nanofiber sheet is pressed using a press machine and crushed so that the average fiber length becomes 200 μm or less, and the CV value of the fiber length becomes 0.7 or less.

A composite production method includes impregnating a plate-shaped porous inorganic structure and a fibrous inorganic material with a metal while the fibrous inorganic material is arranged to be adjacent to the porous inorganic structure. In the composite structure, first and second phases are adjacent to each other by using a porous inorganic structure having a porous silicon carbide ceramic sintered body and the fibrous inorganic material, the first phase being a phase in which the porous silicon carbide ceramic sintered body is impregnated with the metal, the second phase being a phase in which the fibrous inorganic material is impregnated with the metal, a percentage of the porous silicon carbide ceramic sintered body in the first phase is 50 to 80 volume percent, and a percentage of the fibrous inorganic material in the second phase is 3 to 20 volume percent. A composite is produced by the method.