A method of infiltrating a fiber structure with a coating and a matrix material includes connecting a wave guide to a fiber structure comprising a plurality of fibers, applying vibration to the fiber structure to separate adjacent fibers at contact points, and depositing a coating on a surface of each of the fibers including contact point surfaces where adjacent fibers have been separated.

Brake disks with integrated heat sink are provided. Brake disk includes a fiber-reinforced composite material and an encapsulated heat sink material impregnated into the fiber-reinforced composite material. The encapsulated heat sink material comprises a heat sink material encapsulated within a silicon-containing encapsulation layer. Methods for manufacturing the brake disk with integrated heat sink and methods for producing the encapsulated heat sink material are also provided.

A gas turbine engine component includes a gas turbine engine component body formed of a ceramic matrix composite material having at least one fastener integrally formed with the gas turbine engine component body as a single-piece structure. The gas turbine engine component body initially comprises a rigidized preform structure formed from a polymer based material. The at least one fastener connects the gas turbine engine component body to an engine support structure.

A heat insulation material obtained by sintering a raw material comprising: 52 to 93 weight % of alumina particles having an average particle diameter of 100 nm or smaller, 1 to 45 weight % of one or more crystal transition suppression materials selected from silica particles, silica stone, talc, mullite, silicon nitride, silica fume, wollastonite, bentonite, kaolin, sepiolite and mica particles, 0 to 40 weight % of a radiation scattering material, and 1 to 20 weight % of fibers.

Brake disks with integrated heat sink are provided. Brake disk includes a fiber-reinforced composite material and an encapsulated heat sink material impregnated into the fiber-reinforced composite material. The encapsulated heat sink material comprises a heat sink material encapsulated within a silicon-containing encapsulation layer. Methods for manufacturing the brake disk with integrated heat sink and methods for producing the encapsulated heat sink material are also provided.

A vehicle coating to thermally insulate the vehicle's interior is provided. The vehicle coating may be applied to the exterior (e.g., roof) of any suitable moving vehicle, such as a bus, RV, delivery truck, construction vehicle (e.g., cement mixer), train car. When applied to a vehicle's exterior, the vehicle coating provides the benefit of insulating the vehicle's interior from some of the sun's thermal energy, which would otherwise radiate into the vehicle and increase the interior temperature. The vehicle coating demonstrates advantageous thermal insulation properties (e.g., low thermal conductivity) over a wide range of temperatures and when applied with minimal thickness. The provided vehicle coating demonstrates high reflectance, high emissivity, low thermal conductivity, and high solar reflectance index (SRI), and is suitable for high vibration high uplift winds, which all contribute to its desirable properties for use as a thermally insulating vehicle coating.

A honeycomb structure includes latticed partition walls defining a plurality of polygonal cells which extends from one end face to the other end face and forms through channels for fluid, the partition walls are porously formed by using aggregates and a bonding material different from a material of the aggregates, and the partition walls have a relation indicating that a surface porosity of a surface region from a partition wall surface of each of the partition walls to a depth of 15% of a partition wall thickness T and an inner porosity of an inner region from the partition wall surface to a depth of 15% to 50% of the partition wall thickness are different from each other, and a difference obtained by subtracting the surface porosity from the inner porosity is in excess of 1.5%.

A gas turbine engine component includes a gas turbine engine component body formed of a ceramic matrix composite material having at least one fastener integrally formed with the gas turbine engine component body as a single-piece structure. The gas turbine engine component body initially comprises a rigidized preform structure formed from a polymer based material. The at least one fastener connects the gas turbine engine component body to an engine support structure.

A process for providing inorganic polymer ceramic-like materials. The process comprises providing a first material which comprises at least one non-oxide ceramic powder, and, at least one metal oxide, and providing a second material which comprises a caustic slurry composed of alkaline water and a solvent, and, combining the materials with stirring. There is also provided a composition of matter provided by the above-mentioned process which is a chemically bonded ceramic polymer comprising metal oxide and non-oxide ceramic bonds.

According to a method set forth herein a plurality of preform plies having first and second preform plies can be associated together to define a preform. The preform can be subject to chemical vapor infiltration (CVI) processing to define a ceramic matrix composite (CMC) structure.