A fiber-reinforced component for use in a gas turbine engine includes a first braided fiber sleeve forming a cooling channel and a plurality of fiber plies enclosing the first braided fiber sleeve, with the plurality of fiber plies forming first and second walls separated by the first braided fiber sleeve. The fiber-reinforced component further includes a matrix material between fibers of the braided fiber sleeve and the plurality of fiber plies.

A gas turbine engine includes a compressor section and a turbine section. The turbine section includes at least one rotor and at least one blade extending radially outwardly from the rotor to a radially outer tip. A blade outer air seal assembly is positioned radially outwardly of the radially outer tip of the blade. The blade outer air seal has forward and aft hooks. The forward and aft hooks support the blade outer air seal. The blade outer air seal is formed with a central web. The forward and aft hooks extending from the central web at a T-joint. There is a pair of mating inner laminate at the T-joint each having an axially extending portion and a vertically extending portion. The pair of mating inner laminates have an interwoven connection. A method is also disclosed.

A component for a gas turbine engine including a core and an outer enclosure. The core includes an exterior surface extending along a length between a first end and a second end and at least partially defines a cooling cavity on the exterior surface extending from the first end along at least a portion of the length. The cooling cavity is fluidly coupled to an air supply at the first end. The outer enclosure includes an outer surface. The outer enclosure is positioned outside the core and extends from the first end of the core along at least a portion of the length of the core and at least partially defines the cooling cavity.

In some examples, techniques of repairing and/or reinforcing oxide-oxide ceramic matrix composite (CMC) materials using a metallic material. In one example, a method including applying a metallic material at an edge of an oxide-oxide CMC substrate; and heating the metallic material to diffuse the metal material into the oxide-oxide CMC substrate at the edge. In another example, a method including applying a metallic material onto a damaged area of the oxide-oxide CMC; applying a reinforcing phase material onto the damaged area of the oxide-oxide CMC; and heating the metallic material to diffuse the metallic material into the oxide-oxide CMC and attach the reinforcing phase material to the damaged area of the oxide-oxide CMC.

A method for modifying a composite component may include positioning a barrier segment between an infiltrated segment of the composite component and a green segment to form an assembly; and initiating an infiltration process. The barrier segment may have a barrier segment permeability that is lower than a permeability of the infiltrated segment, a permeability of the green segment, or both. A composite component may include an infiltrated segment infiltrated with a molten material during a prior infiltration process; a green segment that is uninfiltrated; and a barrier segment having a microstructure different from the infiltrated segment, the green segment, or both. The microstructure of the barrier segment may be configured to slow a flow of material between the infiltrated segment and the green segment during a subsequent infiltration process.

An airfoil for a gas turbine engine is made from ceramic matrix composite materials. The airfoil has an inner surface that defines a cooling cavity in the body and an outer surface that defines a leading edge, a trailing edge, a pressure side, and a suction side of the body. The airfoil is formed with a plurality of cooling passages that extend from the cooling cavity through the airfoil.

A method to produce a protective surface layer having a predetermined topography on a ceramic matrix composite is described. The method includes applying a slurry layer to a surface of a fiber preform, and drying the slurry layer to form a particulate layer. A surface of the particulate layer is machined to improve surface smoothness and to form a machined surface. A ceramic tape is attached to the machined surface, and a tool comprising one or more features to be imprinted is placed on the ceramic tape, thereby forming a compression assembly. Heat and pressure are applied to the compression assembly to consolidate and bond the ceramic tape to the machined surface, while the one or more features of the tool are imprinted. Thus, a protective surface layer having a predetermined topography is formed.

A method of processing a CMC component includes preparing a fiber preform having a predetermined shape, and positioning the fiber preform with tooling having holes facing one or more surfaces of the fiber preform. After the positioning, a clamping pressure is applied to the tooling to force portions of the one or more surfaces of the fiber preform into the holes, thereby forming protruded regions of the fiber preform. During the application of the clamping pressure, the fiber preform is exposed to gaseous reagents at an elevated temperature, and a matrix material is deposited on the fiber preform to form a rigidized preform including surface protrusions. After removing the tooling, the rigidized preform is infiltrated with a melt for densification, and a CMC component having surface bumps is formed. When the CMC component is assembled with a metal component, the surface bumps may reduce diffusion at high temperatures.

A method is provided in which multiple layers are formed. Each of the layers includes at least a first set of ceramic fibers and a second set of ceramic fibers. The first set is arranged at an angle with respect to the second set. The first set and the second set define a plurality of pores therebetween. The layers are arranged on top of each other to form a porous preform. The pores of the layers arranged on top of each other are aligned. The pores define a plurality of channels extending continuously through the porous preform from a first side of the porous preform to a second side of the porous preform. Each channel comprises one inlet at the first side of the porous preform and one outlet at the second side of the porous preform. The porous preform is infiltrated with a matrix material.

A method is described for manufacturing a ceramic composite structure. The method includes wrapping ceramic fibers (22), such as SiC fibers, about the external surface of at least one form. The method further includes heating the wrapped fibers (22) to a temperature no greater than a first temperature, infiltrating voids (24) in the wrapped fibers (22) with the ceramic composite in a first vessel (12) at the first temperature, transferring the infiltrated wrapped fibers (22) from the first vessel (12) to a second vessel (14), distinct from the first vessel (12), and coating the infiltrated wrapped fibers (22) with the ceramic composite in the second vessel (14) at a second temperature, higher than the first temperature.