A method for forming an oxidation protection system on a composite structure is provided, which may comprise applying a ceramic layer slurry to the composite structure, wherein the ceramic layer slurry may comprise aluminum and silicon in a solvent or carrier fluid; heating the composite structure to form a ceramic layer on the composite structure, wherein the ceramic layer may comprise aluminum nitride; applying a sealing slurry to the composite structure, wherein the sealing slurry may comprise a sealing pre-slurry composition and a sealing carrier fluid, wherein the sealing pre-slurry composition may comprise a sealing phosphate glass composition; and/or heating the composite structure to form a sealing layer on the composite structure.

An environmental barrier coating includes a barrier layer which includes a matrix, diffusive particles, and gettering particles; and a calcium-magnesia alumina-silicate (CMAS)-resistant component. The CMAS-resistant component includes hafnium silicate and a rare earth hafnate. An article and a method of fabricating an article are also disclosed.

A mortar composition, in particular for preparing a viscoelastic structure and/or a fire barrier, including: a) 15-50 wt.-% of a hydraulic binder, b) 5-35 wt.-% of lightweight aggregates, c) 5-25 wt. % of further aggregates which have a particle density that is higher than the particle density of the lightweight aggregates, and d) 10-50 wt.-% of a polymer.

A barrier coating resin formulation comprising at least one polycarbosilane preceramic polymer, at least one organically modified silicon dioxide preceramic polymer, at least one filler, and at least one solvent. A barrier coating comprising a reaction product of the at least one polycarbosilane preceramic polymer and the at least one organically modified silicon dioxide preceramic polymer and the at least one filler is also disclosed, as are articles comprising the barrier coating, rocket motors comprising the barrier coating, and methods of forming the articles.

An oxidation protection system disposed on a substrate is provided, which may comprise a boron layer comprising a boron compound disposed on the substrate; a silicon layer comprising a silicon compound disposed on the boron layer; and at least one sealing layer comprising monoaluminum phosphate and phosphoric acid disposed on the silicon layer.

A method for forming an oxidation protection system on a composite structure may comprise: applying a ceramic layer slurry to the composite structure, wherein the ceramic layer slurry comprises aluminum and silicon in a solvent or carrier fluid; and heating the composite structure in an environment comprising nitrogen gas and oxygen gas to form a ceramic layer on the composite structure, wherein the ceramic layer comprises aluminum nitride and alumina.

The heat resistant structure of the flying body is provided with a tip part and a body part. The tip part is arranged in a front end of the flying body with respect to a direction of travel of the flying body. The body part is arranged in a back direction from the tip part with respect to the direction of travel of the flying body. The tip part is provided with a surface member, a base part, and an insulation member. The surface member is arranged on an outer surface of the tip part and has a melting point higher than a desired temperature. The base part couples the surface member to the body part. The insulation member is arranged between the surface member and the base part., and thermally insulates the base part from the surface member.

The present disclosure provides a method for coating a composite structure, comprising applying a single pretreating composition on a surface of the composite structure, the single pretreating composition comprising a first acid aluminum phosphate comprising a molar ratio of aluminum to phosphate between 1 to 2 and 1 to 3, and heating the composite structure to a first temperature sufficient to form an aluminum phosphate polymer layer on the composite structure.

The present disclosure provides a method for coating a composite structure comprising the steps of applying a first slurry of a first phosphate glass composition on an outer surface of the composite structure. The first slurry comprises a first additive including at least one of molybdenum disulfide or tungsten disulfide. The method may further include heating the composite structure to a temperature sufficient to form a base layer adhered to the composite structure.

An environmental barrier coating system for a turbine component, including an environmental barrier layer applied to a turbine component substrate containing silicon; the environmental barrier layer comprising an oxide matrix surrounding a fiber-reinforcement structure and a self-healing phase interspersed throughout the oxide matrix; wherein the fiber-reinforcement structure comprises at least one first fiber bundle oriented along a load bearing stress direction of said turbine component substrate; wherein the fiber-reinforcement structure comprises at least one second fiber bundle oriented orthogonal to the at least one first fiber bundle orientation; wherein the fiber-reinforcement structure comprises at least one third fiber woven between the at least one first fiber bundle and the at least one second fiber bundle.