Abstract: A turbine shroud for positioning radially outside of blades of a turbine rotor includes a carrier, a blade track, and a track attachment system. The blade track is moved radially outwardly into a cavity of the carrier, and the track attachment system is adjusted to block radially inward movement of the blade track out of the cavity.

Abstract: A gas turbine engine composite vane assembly and method for making same are disclosed. The method includes providing at least two gas turbine engine airfoil composite preform components. The airfoil composite preform components are interlocked with a first locking component so that mating faces of the airfoil composite preform components face each other. A filler material is inserted between the mating surfaces of the airfoil composite preform components.

Abstract: A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. Each blade is formed from a composite comprising ceramic matrix material. The blades each include a root that fits within dovetail slots of the rotor disk and cooperates with a blade retention assembly to couple the blades to the rotor disk.

Abstract: A method of forming a composite article includes impregnating an inorganic fiber preform with a slurry composition. The slurry composition includes a particulate, a solvent, and a pre-gellant material. Gelling of the pre-gellant material in the slurry composition is initiated to immobilize the particulate and yield a gelled article, and substantially all solvent is removed from the gelled article to form a green composite article. The green composite article is then infiltrated with a molten infiltrant to form the composite article.

Abstract: An assembly for a gas turbine engine includes a carrier and a supported component comprising ceramic matrix composite materials. The assembly also includes a retention assembly for coupling the supported component to the carrier.

Abstract: A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. Each blade is formed from a composite comprising ceramic matrix material. The blades each include a root that fits within dovetail slots of the rotor disk and cooperates with a blade retention assembly to couple the blades to the rotor disk.

Abstract: A turbine engine including a turbine shroud for positioning radially outside of blades of the turbine rotor. The turbine shroud includes a carrier, a retention assembly, and a blade track. The blade track is clamped by the retention assembly, and the retention assembly is supported by the carrier.

Abstract: A ceramic matrix composite component for use in a gas turbine engine and method for making the same are described herein. The component includes a body and an outer region. The body includes a silicon containing ceramic composite. The outer region is on an outer surface of the body.

Abstract: A gas turbine engine includes a turbine having turbine blades and a shroud having a blade track for positioning radially outside of the blades. At least one of the blades and the blade track are secured in place using a dovetail connection between a dovetail receiver and a dovetail assembly formed to include a contoured root.

Abstract: Integrated ceramic matrix composite components for use in gas turbine engines are disclosed along with methods for making the same. The methods include coinfiltrating a greenbody assembly with ceramic matrix to produce an integrated component.

Abstract: A method of forming a ceramic matrix composite are described herein. The method may include infiltrating a fiber preform with a solution comprising a refractory precursor in solution with a solvent. The refractory precursor may include a compound having at least one refractory metal element. The method may further include removing the solvent from the fiber preform, and reducing the refractory precursor to form a refractory metal that includes the refractory metal element.

Abstract: A ceramic matrix composite component and methods of making are described herein. The ceramic matrix composite may include a silicon containing matrix and refractory fibers embedded within the silicon containing matrix. The ceramic matrix composite component may further include a silicide layer sandwiched between the silicon containing matrix and the refractory fibers. A method of forming a ceramic matrix composite may include infiltrating a fluid that includes a refractory metal element containing compound into a fiber preform that includes fibers. The method may further include depositing the refractory metal element from the refractory metal element containing compound onto the fibers and forming, from the refractory metal element deposited onto the fibers, a refractory metal silicide.

Abstract: A turbine engine including a turbine shroud for positioning radially outside of blades of the turbine rotor. The turbine shroud includes a carrier, a retention assembly, and a blade track. The blade track is clamped by the retention assembly, and the retention assembly is supported by the carrier.

Abstract: A turbine shroud for positioning radially outside of blades of a turbine rotor includes a carrier, a blade track, and a track attachment system. The blade track is moved radially outwardly into a cavity of the carrier, and the track attachment system is adjusted to block radially inward movement of the blade track out of the cavity.

Abstract: Integrated ceramic matrix composite components for use in gas turbine engines are disclosed along with methods for making the same. The methods include coinfiltrating a greenbody assembly with ceramic matrix to produce an integrated component.

Abstract: A method of forming a ceramic matrix composite are described herein. The method may include infiltrating a fiber preform with a solution comprising a refractory precursor in solution with a solvent. The refractory precursor may include a compound having at least one refractory metal element. The method may further include removing the solvent from the fiber preform, and reducing the refractory precursor to form a refractory metal that includes the refractory metal element.

Abstract: A ceramic matrix composite component for use in a gas turbine engine and method for making the same are described herein. The component comprising a body and an outer region. The body having a silicon containing ceramic composite. The outer region on an outer surface of the body.

Abstract: A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. Each blade is formed from a composite comprising ceramic matrix material. The blades each include a root that fits within dovetail slots of the rotor disk and cooperates with a blade retention assembly to couple the blades to the rotor disk.

Abstract: A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. Each blade is formed from a composite comprising ceramic matrix material. The blades each include a root that fits within dovetail slots of the rotor disk and cooperates with a blade retention assembly to couple the blades to the rotor disk.

Abstract: An assembly for use in a gas turbine engine and method for making the same are described herein. The assembly comprising a CMC component, a metallic component spaced apart from the CMC component, and a spacer. The spacer having a first surface in contact with the CMC and a second surface opposite the first surface in contact with the metallic component, the spacer comprising a CMC substantially free of silicon metal with a porosity of between about 5 percent and about 40 percent by volume to chemically isolate the CMC component from the metallic component.