A turbine shroud adapted for use in a gas turbine engine is disclosed in this paper The turbine shroud includes a blade track segment comprising ceramic matrix composite materials and an attachment unit comprising metallic materials The attachment unit is coupled to the blade track segment and is configured to interface with other metallic components in the gas turbine engine

Turbine shroud assembly having ceramic matrix composite track segments with metallic attachment features

Fan blade containment system includes circular tile layer of annular ceramic tiles attached to and extending radially inwardly from a shell, radially inner and outer annular surfaces of ceramic tiles bonded to a radially inner composite layer and the shell respectively with elastomeric inner and outer adhesive layers respectively. Elastomeric adhesive layers between circumferentially adjacent overlapped or scarfed edges along circumferential edges of the ceramic tiles overlap and mate along oppositely facing surfaces of adjacent ones of the ceramic tiles. Inner and outer adhesive layers and elastomeric adhesive layer may be a double-sided adhesive foam tape. Scarfed edges may be bevels or rabbets. Shell may be made of a metal or composite material. Fan blade containment system may be bonded to and extend inwardly from fan case circumscribing fan blades of a fan. Inner composite layer and composite outer shell may be co-cured with ceramic tiles therebetween.

Ceramic tile fan blade containment

A shroud assembly for a turbine engine comprises a plurality of circumferentially arranged shroud segments, each terminating in circumferentially spaced first and second shiplap elements, where the first shiplap element of one shroud segment can overlap the second shiplap element of an adjacent shroud segment.

Turbine engine shroud assembly

A panel for lining a gas turbine engine fan casing includes a honeycomb core sandwiched between a backing skin and an outer skin. The backing skin is attached to an inner surface of the casing such that the outer skin forms a radially inward facing surface of a fan duct of the engine. The panel is joined along its sides to similar neighbouring panels such that, in use, the joined panels form a row of panels along the inner surface of the casing. The outer skin or the backing skin includes two face sheets bonded on top of each other, which are arranged such that their edges along each panel side that joins to a neighbouring panel are staggered in the direction of the row. The interfaces between the abutting face sheet edges are therefore correspondingly staggered in the direction of the row.

Panel for lining a gas turbine engine fan casing

Component retention assemblies and flowpath assemblies are provided. An exemplary retention assembly comprises a flange attached to a support structure, a retention ring received in a flange groove, and an attachment bracket comprising a component of a gas turbine engine. A first segment of the attachment bracket is axially disposed between the flange and a support structure first portion, and a second segment of the attachment bracket is radially disposed between the flange and a support structure second portion. The flange axially loads and the retention ring radially loads the attachment bracket into the support structure. An exemplary flowpath assembly comprises a retention assembly including a flange attached to a casing, a retention ring, and a CMC attachment bracket comprising a plurality of CMC components. The flange axially loads the attachment bracket into an axial stop, and the retention ring radially loads the attachment bracket into the casing.

Retention assembly for gas turbine engine components

A turbine shroud for a gas turbine engine is disclosed in this paper. The turbine shroud includes a ceramic-matrix composite blade track. The ceramic-matrix composite blade track includes a plurality of track segments located circumferentially adjacent to one another to form a track ring. Features of the track segments provide tortuous paths for gasses trying to pass through the ceramic-matrix composite blade track that may reduce leakage through the blade track.

Segmented turbine shroud with sealing features

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.

Hanger system for a turbine engine component

The present disclosure is related to turbine wheel assemblies for gas turbine engines. Such turbine wheel assemblies may include ceramic matrix composite airfoil components mounted with different types of coupling to a central disc.

Ted J. Freeman

Papers

Segmented turbine shroud with sealing features

Hanger system for a turbine engine component

Turbine wheel assembly