Method for manufacturing a composite material part includes injecting a slurry containing a refractory ceramic particle powder into a fibrous texture, draining the liquid from the slurry that passed through the fibrous texture and retaining the refractory ceramic particle powder inside said texture so as to obtain a fibrous preform loaded with refractory ceramic particles, and demoulding of the fibrous preform. The method includes, after demoulding the fibrous preform, checking the compliance of the demoulded fibrous preform. If the preform is noncompliant, the method also includes, before a sintering, immersing the demoulded fibrous preform in a bath of a liquid suitable for decompacting the refractory ceramic particles present in the fibrous preform, and additionally injecting a slurry containing a refractory ceramic particle powder into the fibrous preform present in the mould cavity.

A fiber reinforced composite component may include interleaved textile layers and ceramic particle layers coated with matrix material. The fiber reinforced composite component may be fabricated by forming a fibrous preform and densifying the fibrous preform. The fibrous preform may be fabricated by forming a first ceramic particle layer over a first textile layer, disposing a second textile layer over the first ceramic particle layer, forming a second ceramic particle layer over the second textile layer, and disposing a third textile layer over the second ceramic particle layer.

Embodiments of the invention include articles incorporating fibrous fragments of mats of silica fibers and methods for producing such articles. The fiber mats may be formed via electrospinning of a sol gel produced with a silicon alkoxide reagent, such as tetraethyl ortho silicate, alcohol solvent, and an acid catalyst.

The present invention provides a means that can improve density and mechanical strength in a sintered body of a composition containing a sintering aid and a silicon carbide particle, and a molded article containing the sintered body. The present invention relates to a coated silicon carbide particle powder containing a silicon carbide particle, and a coating layer coating the silicon carbide particle, in which the coating layer contains an aluminum element, and the mass of the aluminum element per unit surface area of the silicon carbide particle is 0.5 mg/m.sup.2 or more.

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.

The present disclosure discloses a hybrid woven fiber preform-reinforced composite material, including a fiber preform, a composite material interface and a matrix, where the fiber preform is a three-dimensional fabric hybrid woven by 2-5 high-performance inorganic fibers, and the matrix is selected from the group consisting of resin, light alloy, carbon and ceramic. A preparation method of the composite material includes: preparing ceramic slurry, fiber bundle impregnation treatment, fiber weaving, molding of three-dimensional overall structure preform, preform heat treatment, preparing interface and preparing matrix. The present disclosure improves the weaving performance of inorganic rigid fibers, and the prepared hybrid woven fiber preform-reinforced composite material has desirable integrity, high interlayer bonding strength, and is not easy to layer. Meanwhile, the present disclosure realizes the functions of wave transmission, wave-absorbing, high-temperature structural material, thermal insulation and thermal prevention through the combination of hybrid woven fibers.

The present disclosure discloses a continuous electrophoretic deposition modified carbon fiber reinforced multi-matrix composite and a preparation method thereof, composing of a carbon fiber with a volume fraction of 30-55%, an inorganic powder with a volume fraction of 3-25% and a matrix with a volume fraction of 20-67%, wherein the inorganic powder is wrapped on the surface of the carbon fiber filament or embedded in the carbon fiber bundle, and the concentration gradually decreases from the fiber filament to the surface of the fiber bundle. The preparation method of the composite is as follows: (1) pretreating the carbon fibers; (2) preparing a slurry of the inorganic powder; (3) widening the pretreated carbon fiber to form a carbon fiber strip, and then carrying out electrophoretic deposition on the inorganic powders; (4) preparing a preform from the deposited carbon fibers; and (5) compounding a matrix in the preform.

A non woven web including a multiplicity of non-respirable, polycrystalline, aluminosilicate ceramic filaments entangled to form a cohesive mat, the polycrystalline, aluminosilicate ceramic filaments having an average mullite percent of at least 75 wt %. The cohesive mat preferably exhibits a compression resilience after 1,000 cycles at 900° C. when measured according to the Fatigue Test, of at least 30 kPa. Insulation articles including the cohesive mats or formed by chopping the ceramic mats into ceramic fibers, pollution control devices including the insulation articles, and methods of making the non-respirable, polycrystalline, aluminosilicate ceramic filaments and fibers, nonwoven webs, insulation articles, and pollution control devices, are also described.

A ceramic matrix composite includes at least one ply of ceramic fibers and a a ceramic matrix material deposited on the ceramic fibers. A fiber volume fraction is between about 35-45% and an areal weight fibers is between about 150-450 g/m2. A method of fabricating a ceramic matrix composite component is also disclosed.

A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal that has 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 includes one or more braided core plies having a first fiber construction and arranged to establish an internal cavity. An overwrap having one or more braided overwrap plies follows a perimeter of the one or more braided core plies to establish the engagement portion and the sealing portion. The one or more braided overwrap plies have a second fiber construction differing from the first fiber construction. A method of fabricating a seal for a gas turbine engine is also disclosed.