A rotor assembly is provided for a gas turbine engine. This rotor assembly includes a first rotor disk, a second rotor disk, a plurality of rotor blades and a plurality of vanes. The first rotor disk is configured to rotate about a rotational axis. The second rotor disk is configured to rotate about the rotational axis. The rotor blades are arranged circumferentially around the rotational axis. Each of the rotor blades is axially between and mounted to the first rotor disk and the second rotor disk. The vanes are arranged circumferentially around the rotational axis. The vanes include a first vane that is integral with the first rotor disk and projects axially to the second rotor disk.

A rotor assembly is provided for a gas turbine engine. This rotor assembly includes a first rotor disk, a second rotor disk, a plurality of rotor blades and a plurality of disk mounts. The first rotor disk is configured to rotate about a rotational axis. The second rotor disk is configured to rotate about the rotational axis. The rotor blades are arranged circumferentially around the rotational axis. Each of the rotor blades is axially between and mounted to the first rotor disk and the second rotor disk. The disk mounts connect the first rotor disk and the second rotor disk together. The disk mounts include a first disk mount. The first disk mount is integral with the first rotor disk. The first disk mount projects axially through the second rotor disk.

An apparatus is provided for a rotor assembly with a rotational axis. This apparatus includes a rotor blade including an airfoil, a neck and an attachment. The neck radially connects the airfoil and the attachment. The attachment extends axially between an attachment first axial side and an attachment second axial side. A first end portion of the attachment projects axially out from the neck to the attachment first axial side. A second end portion of the attachment projects axially out from the neck to the attachment second axial side.

A turbine shroud assembly for use with a gas turbine engine includes a carrier assembly coupled to a blade track segment, and a sheet-metal seal that seals on axial and radial facing surfaces therebetween. The blade track segment includes a shroud wall that extends circumferentially partway around an axis and an attachment feature that extends radially outward from the shroud wall. The carrier is coupled with the attachment feature to support the blade track segment.

A gas turbine exhaust casing includes a tubular casing wall, a bearing box housed in the casing wall, a diffuser portion forming an annular exhaust gas flow passage between the casing wall and the bearing box, a plurality of struts disposed at intervals in a circumferential direction of the casing wall, and coupling the casing wall and the bearing box, and a plurality of fastening bolts disposed on the casing wall. The casing wall includes an upper half casing forming an upper half of the casing wall and a lower half casing forming a lower half of the casing wall. The plurality of fastening bolts fasten the upper half casing and the lower half casing. The plurality of struts include a penetrated strut which has an end penetrated by at least one fastening bolt of the plurality of fastening bolts.

A turbine shroud assembly for use with a gas turbine engine includes a turbine outer case, a blade track segment, and a carrier assembly. The turbine outer case is arranged around an axis. The blade track segment is configured to define a portion of a gas path of the gas turbine engine. The carrier assembly is coupled to the turbine outer case and supports the blade track segment.

An assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a gas turbine engine component that has a first interface portion, and a support that has a mounting portion and a second interface portion, the mounting portion attachable to an engine static structure, a first retention feature that releasably secures the first interface portion to the support in a first installed position of the gas turbine engine component, and a second retention feature dimensioned to secure the first interface portion to the second interface portion in a second installed position of the gas turbine engine component. The first installed position differs from the second installed position, and one of first and second retention features is dimensioned to carry the gas turbine engine component in response to release of another one of the first and second retention features. A method of sealing for a gas turbine engine is also disclosed.

A turbine assembly adapted for use with a gas turbine engine includes an outer case, a blade track segment, and a carrier. The outer case extends circumferentially at least partway around an axis of the engine. The blade track segment is configured to define a portion of a gas path of the turbine assembly. The carrier is coupled with the outer case and the blade track segment to support the blade track segment in position radially relative to the axis.

A turbine shroud assembly for use with a gas turbine engine includes a carrier assembly coupled to a blade track segment, and a sheet-metal seal that seals on axial and radial facing surfaces therebetween. The blade track segment includes a shroud wall that extends circumferentially partway around an axis and an attachment feature that extends radially outward from the shroud wall. The carrier is coupled with the attachment feature to support the blade track segment.

A vane arm assembly for a gas turbine engine is provided including: a vane arm having a first end, a second end opposite the first end, and an aperture proximate the second end, the aperture being defined by an aperture wall; a vane stem extending through the aperture of the vane arm; a mechanical fastener retaining a position of the vane arm in the longitudinal direction of the vane stem; and an impedance clip partially enclosing a portion of the second end of the vane arm to provide redundant position retention of the vane arm in the longitudinal direction of the vane stem.