A method for forming an ultra-high temperature (UHT) composite structure includes dispensing a first polymeric precursor with a spinneret; forming a first plurality of nanofibers from the first polymeric precursor; depositing the first plurality of nanofibers with a collector; and applying a fluid, with a nozzle, onto the first plurality of nanofibers disposed on the collector. The fluid includes a second polymeric precursor.

A composite structure formed of a fiber reinforced composite material may include a plurality of fiber layers and a carbon matrix surrounding the plurality of fiber layers. A first fiber layer of the plurality of fiber layers may include a carbon fiber tow. A second fiber layer of the plurality of fiber layers may include a non-carbon fiber tow. The coefficient of thermal expansion of the non-carbon fiber tow is greater than the coefficient of thermal expansion of the carbon fiber tow.

A method of improving surface roughness of ceramic matrix composites (CMCs) is provided. The method includes completing a formation of the CMCs and a chemical vapor infiltration (CVI) process to initially coat the CMCs, inspecting a CMC surface, identifying, from a result of the inspecting, a defect in the CMC surface that negatively impacts a surface roughness characteristic thereof, locally targeting and ablating the defect and re-inspecting the CMC surface to ensure that the defect is correct.

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.

Provided are a dispersion for a silicon carbide sintered body having a small environmental load, high dispersibility, and excellent temporal stability, and a manufacturing method thereof. The dispersion is a dispersion for a silicon carbide sintered body, containing: silicon carbide particles; boron nitride particles; a resin having a hydroxyl group; and water, wherein the dispersion has a pH at 25° C. of less than or equal to 7.0, and the silicon carbide particles and the boron nitride particles have charges of the same sign. The dispersion is manufactured by a manufacturing method of a dispersion for a silicon carbide sintered body, including a mixing step of mixing a water dispersion containing silicon carbide particles, a water dispersion containing boron nitride particles, and an aqueous solution containing a resin having a hydroxyl group.

The present invention relates to a process for the production of fiber-reinforced composite materials with an ultra-refractory, high tenacity, high ablation resistant matrix with self-healing properties, prepared from highly sinterable slurries. The composite material is produced using techniques of infiltration and drying at ambient pressure or under vacuum, and consolidated by sintering with or without the application of gas or mechanical pressure.

A method for producing SiC/SiC composite material according to the present invention includes impregnating a substrate with a slurry containing particles of a flaky lubricant to obtain an impregnated body, drying out a solvent of the slurry from the impregnated body, forming an interface layer on surfaces of the SiC fibers by bending the impregnated body, and transferring the particles of the flaky lubricant to the surfaces of the SiC fibers while stretching the particles, and forming a SiC matrix inside the substrate on which the interface layer is formed. Since a thin interface layer of the flaky lubricant can be formed on the surfaces of the SiC fibers by transferring the flaky lubricant to the surfaces of the SiC fibers, the interface layer reaching inside of the substrate can be easily formed.

A seal assembly for a gas turbine engine includes a seal including a main body extending circumferentially between opposed mate faces. The main body has a sealing portion and an engagement portion extending outwardly from sealing portion along at least one of the mate faces. The main body has a core including one or more core plies arranged to establish an internal cavity. An overwrap has one or more overwrap plies arranged to follow a perimeter of the one or more core plies to establish the engagement portion and the sealing portion. A platform insert extends between portions of the core and the overwrap to establish the sealing portion. A method of fabricating a seal for a gas turbine engine is also disclosed.

The disclosure relates to, among other things, an abrasive article comprising a plurality of 4D-ceramic structures, wherein the 4D-ceramic structures are made by a method comprising sequentially: at least partially removing a strain from a second strained primary polymer ceramic precursor, comprising a polymeric substrate and ceramic precursor particles dispersed therein, to give a 4-D ceramic precursor comprising a polymeric substrate; and thermolytically removing the polymeric substrate from the 4-D ceramic precursor comprising a polymeric substrate to provide a 4D-ceramic structure.

The present disclosure includes a system and method for monitoring degradation of a high temperature composite component (HTC). The HTC is defined by a volume that includes a matrix material and a fiber formed from at least one of ceramic and carbon material. One or more electrical conductors are disposed within the volume and connected directly or indirectly to a monitoring system.