Disclosed herein is a composite comprising a ceramic matrix composite comprising a ceramic matrix and ceramic fibers; and one or more sacrificial fibers woven into the ceramic matrix composite; where the sacrificial fibers are operative to undergo oxidation or melting upon being subjected to an elevated temperature; and wherein the sacrificial fibers leave cooling holes in the composite preform upon being subjected to oxidation or melting.

The present invention describes various methods for manufacturing gel composite sheets using segmented fiber or foam reinforcements and gel precursors. Additionally, rigid panels manufactured from the resulting gel composites are also described. The gel composites are relatively flexible enough to be wound and when unwound, can be stretched flat and made into rigid panels using adhesives.

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 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.

An additive manufacturing apparatus includes powder supplies, a preceramic binder supply, and a mixer device downstream from the powder supplies and the preceramic binder supply and configured to generate a powder-integrated preceramic mixture. The additive manufacturing apparatus also includes a nozzle device downstream from the mixer device and configured to output the powder-integrated preceramic mixture, and a heat source configured to heat the powder-integrated preceramic mixture to initiate a self-sustainable ceramization reaction to generate a ceramic matrix composite.

A method for injecting a loaded suspension into a fibrous texture having a three-dimensional or multilayer weaving includes the injection of a suspension containing a powder of solid particles into the volume of the fibrous texture. The injection of the loaded suspension is carried out by at least one hollow needle in communication with a loaded suspension supply device, each needle being movable in at least one direction extending between a first face and a second opposite face of the fibrous texture so as to inject the loaded suspension at one or more determined depths in the fibrous texture.

The present invention describes various methods for manufacturing gel composite sheets using segmented fiber or foam reinforcements and gel precursors. Additionally, rigid panels manufactured from the resulting gel composites are also described. The gel composites are relatively flexible enough to be wound and when unwound, can be stretched flat and made into rigid panels using adhesives.

A ceramic spinner and a method of making the same is provided. The ceramic spinner includes: a top portion with a first opening, the first opening having a first diameter; a base portion with a second opening, the second opening having a second diameter smaller than the first diameter; a cylindrical portion extending between the top portion and the base portion, the cylindrical portion including a peripheral outer wall, a peripheral inner wall, and a plurality of through holes extending between the peripheral outer wall and the peripheral inner wall. The cylindrical portion may include a material having a module of rupture (MOR) exceeding 100 MPa, a Mohs hardness exceeding 8, or a Young's Modulus exceeding 250 GPa, or any combinations thereof.

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 invention relates to surface-treated prepreg composites and corresponding methods of surface treating an inorganic fabric to form a surface-treated fabric reinforced prepreg composite. The method comprises infiltrating an inorganic fabric with a first slurry mixture to form an infiltrated fabric; optionally drying the infiltrated fabric; infiltrating an inorganic paper with a second slurry mixture to form an infiltrated paper; optionally drying the infiltrated paper; and applying the infiltrated paper to at least one surface of the infiltrated fabric to form a surface-treated prepreg composite.