Abstract: A ceramic matrix composite includes a plurality of ceramic fibers and an interface coating disposed on the plurality of ceramic fibers. The interface coating includes a carbon-based layer disposed on each ceramic fiber of the plurality of ceramic fibers and a boron-nitride based layer disposed on the first carbon-based layer. The ceramic matrix composite also includes a ceramic matrix surrounding the plurality of ceramic fibers. A ceramic matrix composite and a method of forming a ceramic matrix composite component are also disclosed.

Abstract: A coated fiber structure for use in a ceramic matrix composite comprises a fiber and a fiber coating arrangement applied to and at least partially circumscribing the fiber. The fiber coating arrangement comprises a first boron nitride layer comprising exfoliated hexagonal boron nitride, a silicon carbide layer extending at least partially coaxially with and in direct contact with the first boron nitride layer, and a second boron nitride layer radially opposite the silicon carbide layer, with respect to the first boron nitride layer.

Abstract: A ceramic matrix composite includes a fiber, a first interface coating layer disposed adjacent to an outer surface of the fiber, and a first protective layer disposed outward of the first interface coating layer and the fiber. The first protective layer comprises a high entropy ceramic. A method of protecting a fiber of a ceramic matrix composite includes depositing, by chemical vapor deposition or chemical vapor infiltration, a first interface coating layer on the fiber; and depositing, by chemical vapor deposition or chemical vapor infiltration, a first protective layer outward of the first interface coating layer. The first protective layer comprises a high entropy ceramic.

Abstract: A coated fiber structure for use in a ceramic matrix composite comprises a fiber and a coating system applied to and circumscribing the fiber. The coating system comprises an interface coating layer in direct contact with the fiber, the interface coating layer comprising one of boron nitride and a boron-doped pyrocarbon, at least one intermediate layer extending coaxially with and in direct contact with the interface layer, the at least one intermediate layer comprising at least one of silicon and boron nitride, and an outer layer extending coaxially with and in direct contact with the interface layer. At least one of the interface coating layer, the at least one intermediate layer, and the outer layer comprises a metallic element.

Abstract: A method of forming an aerodynamic component for use in a gas turbine engine using ceramic matrix composites (CMCs) is provided. The method includes executing a full densification of the CMCs once a final shape of the aerodynamic component is achieved, identifying first and second sectors of an exterior surfaces of the aerodynamic component which have a surface roughness of less than a first roughness level and identifying second sectors of the exterior surface of the component which have a surface roughness of greater than a second roughness level, machining the first sectors to increase the surface roughness to greater than the first roughness level and machining the second sectors to decrease the surface roughness to less than the second roughness level.

Abstract: A method of forming a ceramic matrix composite includes depositing particles on a ceramic fabric formed from a plurality of ceramic tows, applying a binder to at least the particles to form a stabilized ceramic fabric, forming a preform using the stabilized ceramic fabric, and densifying the preform. The ceramic tows are formed from a first material and the particles are formed from at least a second material.

Abstract: A method of spreading fiber tows includes applying a coupling medium to a surface of a fibrous structure, positioning an ultrasonic probe adjacent to the surface of a fibrous structure, such that a tip of the ultrasonic probe is in contact with the coupling medium, moving at least one of the ultrasonic probe and the fabric structure relative to the other of the ultrasonic probe and the fibrous structure according to a first pattern, and imparting ultrasonic vibration with the ultrasonic probe to the surface of the fibrous structure while moving the ultrasonic probe along the surface of the fibrous structure. Imparting ultrasonic vibration to the surface of the fibrous structure spreads tows of the fibrous structure.

Abstract: A method includes forming a ceramic matrix composite component by infiltrating an array of ceramic-based fibers with a ceramic-based matrix; forming a plurality of cooling holes in the ceramic matrix composite component; applying a slurry of particles in a carrier fluid to the ceramic matrix composite component such that the slurry passes through the cooling holes and wicks into the ceramic matrix composite material; and processing the ceramic matrix composite component to remove the carrier fluid, thereby leaving a filler at a wall surface of the plurality of cooling holes. A component is also disclosed.

Abstract: A method of forming a component for a gas turbine engine using ceramic matrix composites (CMCs) is provided. The method includes preforming the aerodynamic component into an initial desired shape using the CMCs, executing partial densification of the CMCs, repeating the preforming operations and the executing of the partial densification until a final desired shape of the aerodynamic component is achieved, machining or cutting the CMCs during one or more of the preforming operations and the executing of the partial densification to remove defects from the CMCs and executing a full densification of the CMCs.

Abstract: A method of forming an aerodynamic component for use in a gas turbine engine using ceramic matrix composites (CMCs) is provided. The method includes executing a full densification of the CMCs once a final shape of the aerodynamic component is achieved, identifying first and second sectors of an exterior surfaces of the aerodynamic component which have a surface roughness of less than a first roughness level and identifying second sectors of the exterior surface of the component which have a surface roughness of greater than a second roughness level, machining the first sectors to increase the surface roughness to greater than the first roughness level and machining the second sectors to decrease the surface roughness to less than the second roughness level.

Abstract: A ceramic matrix composite includes a plurality of ceramic fibers and an interface coating disposed on the plurality of ceramic fibers. The interface coating includes a carbon-based layer disposed on each ceramic fiber of the plurality of ceramic fibers and a boron-nitride based layer disposed on the first carbon-based layer. The ceramic matrix composite also includes a ceramic matrix surrounding the plurality of ceramic fibers. A ceramic matrix composite and a method of forming a ceramic matrix composite component are also disclosed.

Abstract: A method for forming a self-healing ceramic matrix composite (CMC) component includes depositing a first self-healing particulate material in a first region of a CMC preform of the CMC component and depositing a second self-healing particulate material having a different chemical composition than the first self-healing particulate material in a second region of the CMC preform distinct from the first region.

Abstract: A method for forming a self-healing ceramic matrix composite (CMC) component includes depositing a first self-healing particulate material in a first region of a CMC preform of the CMC component and depositing a second self-healing particulate material having a different chemical composition than the first self-healing particulate material in a second region of the CMC preform distinct from the first region.

Abstract: An air foil includes a body and a filler. The body may include a chamber formed therein and includes a first metallic material. The filler may at least partially occupy the chamber of the body and may include a second metallic material. The second metallic material may have a comparatively more negative electrode potential than the first metallic material.

Abstract: A method for forming a self-healing ceramic matrix composite (CMC) component includes depositing a first self-healing particulate material in a first region of a CMC preform of the CMC component and depositing a second self-healing particulate material having a different chemical composition than the first self-healing particulate material in a second region of the CMC preform distinct from the first region.

Abstract: An air foil includes a body and a filler. The body may include a chamber formed therein and includes a first metallic material. The filler may at least partially occupy the chamber of the body and may include a second metallic material. The second metallic material may have a comparatively more negative electrode potential than the first metallic material.