Abstract: An assembly comprising a structural component and a sacrificial layer, and method for producing the same. The structural component may comprise silicon carbide fibers within a silicon carbide matrix. The sacrificial layer may be joined to the structural component and may comprising unarranged ceramic fibers, wherein the sacrificial layer may comprise a volume fiber fraction lower than a volume fiber fraction of the structural component.

Abstract: A blade track for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form the blade track.

Abstract: An assembly for use in a gas turbine engine is disclosed. The assembly includes a first component arranged adjacent to a second component to form a gap therebetween and a pressure activated seal that resists flow through the gap.

Abstract: A turbine shroud for a gas turbine engine includes an annular metallic carrier and a ceramic-containing blade track. A connection is formed between the annular metallic carrier and the ceramic-containing blade track by insert pins extending through metallic carrier into the ceramic-containing blade track.

Abstract: A turbine shroud for a gas turbine engine includes an annular metallic carrier, a blade track, and a cross-key connection formed between the annular metallic carrier and the ceramic blade track. The cross-key connection locates the ceramic blade track relative to the metallic carrier.

Abstract: A gas turbine engine includes a body and a turbine-vane ring coupled to the body. The turbine-vane ring includes a plurality of turbine-vane assemblies. Each turbine-vane assembly includes a vane unit and a heat shield configured to reduce heat transfer to the vane unit from hot exhaust gases during operation of the gas turbine engine.

Abstract: A turbine wheel assembly adapted for use in a gas turbine engine is disclosed. The turbine wheel assembly includes a disk configured to rotate about an axis during operation of the gas turbine engine, turbine blades coupled with the disk, and heat shields arranged between turbine blades. The turbine wheel assembly includes components optionally made from ceramic matrix composite materials such as the turbine blades and/or heat shields.

Abstract: A turbine shroud or blade track assembly adapted to extend around a turbine wheel assembly is disclosed. The turbine shroud includes a carrier and a blade track coupled to the carrier. The blade track is movable between a radially-inward position having a first inner diameter and a radially-outward position having a second inner diameter larger than the first inner diameter.

Abstract: A turbine shroud for a gas turbine engine includes a carrier and a blade track segment. The carrier is formed to include an inwardly opening blade track channel and the blade track segment is positioned in the blade track channel to couple the blade track segment with the carrier.

Abstract: A gas turbine engine assembly includes adjacent components and a seal assembly. The seal assembly being configured to block gasses from passing through the interface of the adjacent components.

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: An apparatus adapted for use in a gas turbine engine includes a first circumferential member and a second circumferential member. The first circumferential member includes an end portion that defines a recess and includes a first seal surface. The second circumferential member includes an end portion that includes a second seal surface. The end portion of the second circumferential member is configured to be at least partially disposed in the recess of the first circumferential member to collectively form at least a portion of a circumferential assembly of a gas turbine. The first seal surface of the first circumferential member is forms a first seal with a seal member and the second seal surface of the second circumferential member is forms a second seal with the seal member when the end portion of the second circumferential member is disposed in the recess of the first circumferential member.

Abstract: A gas turbine engine may comprise a blade track and a method of making the same. The blade track may be constructed of ceramic matrix composite components including segments and joints.

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 turbine shroud for a gas turbine engine includes an annular metallic carrier, a blade track, and a cross-key connection formed between the annular metallic carrier and the ceramic blade track. The cross-key connection is formed between the annular metallic carrier and inserts included in the blade track.

Abstract: An assembly for a gas turbine engine includes ceramic material containing (i.e. ceramic matrix composite) segments and joints that couple the segments together.

Abstract: A gas turbine engine may comprise a blade track and a method of making the same. The blade track may be constructed of ceramic matrix composite components including main body members and joints.

Abstract: A turbine shroud for use in a gas turbine engine that includes a metallic carrier, a blade track, and a seal is disclosed. The seal is engaged with surfaces of the metallic carrier and the blade track to block ingress of hot gasses at the interface of the blade track and the metallic carrier.

Abstract: A component of a turbine is disclosed. The component includes an carrier segment having a rail, an frame segment including a hanger having a flange supported on the rail of the carrier segment, and an inner surface having a section of a track for a turbine blade defined therein. The component also includes a retainer segment secured to the carrier segment such that the hanger is secured between the retainer segment and the carrier segment.

Abstract: An assembly for a gas turbine engine includes a carrier and a supported component comprising ceramic matrix composite materials. The supported component includes an annular runner and a plurality of inserts that extend radially outward away from the annular runner. The inserts extend into the carrier to couple the supported component with the carrier.