Abstract: An aircraft engine having a turbine assembly including a bearing housing having a central axis, a first-stage vane ring and a second-stage vane ring. The first-stage vane ring is positioned in concentric relation with the bearing housing via a first circumferential array of lugs and slots between the bearing housing and the first-stage vane ring. The second-stage vane ring is positioned in concentric relation to the first-stage vane ring via a second circumferential array of lugs and slots between the first-stage vane ring and the second-stage vane ring.

Abstract: An apparatus is provided for a gas turbine engine. This apparatus includes a gas turbine engine case extending axially along and circumferentially around an axis. The gas turbine engine case includes a sheet of metal wrapped multiple times around the axis to form a containment structure having a multi-layered configuration. The containment structure is configured to contain at least one of a blade or a blade fragment from a bladed rotor of the gas turbine engine within the at least one of a plurality of sections.

Abstract: An aircraft engine, has: a turbine including a turbine rotor rotatable about a central axis; a scroll case having an inlet fluidly connected to a source of combustion gases and an outlet fluidly connected to the turbine, and a conduit extending around the central axis from the inlet to the outlet; a bearing housing extending around the central axis; and a flange connecting the scroll case to the bearing housing, the flange having a first end connected to the scroll case, a second end connected to the bearing housing, and a deflecting wall section extending between the first end and the second end, the deflecting wall section being spaced apart from the scroll case by an annular gap, the deflecting wall section of the flange being deformable in a radial direction.

Abstract: An aircraft propulsion system includes a turbocompressor unit, an engine exhaust assembly, and a tube assembly. The turbocompressor unit includes a compressor, a turbine, a turbocompressor rotational assembly, and a static structure. The static structure forms a first cavity and a second cavity. The engine exhaust assembly includes an annular scroll disposed between the first cavity and the second cavity. The annular scroll includes a scroll body and a plurality of hollow stator vanes. The plurality of hollow stator vanes is disposed within the flow channel. The tube assembly includes a tubular body. The tubular body extends through one of the plurality of hollow stator vanes between and to the first cavity and the second cavity. The tubular body forms an internal passage extending from the first axial tube end to the second axial tube end. The internal passage connects the first cavity in fluid communication with the second cavity.

Abstract: An exhaust system, has: a turbine exhaust duct (TED) having an annular inlet conduit extending around a central axis, and outlet conduits fluidly communicating with the annular inlet conduit and extending generally radially outward relative to the annular inlet conduit; and an exhaust case surrounding the TED, the exhaust case having openings, each of the outlet conduits received through a respective one of the openings; and exhaust conduits secured to the exhaust case and each extending around a respective one of the openings of the exhaust case, an exhaust conduit of the exhaust conduits including: a duct protruding away from the exhaust case and fluidly communicating with a respective one of the outlet conduits; a flange flaring away from the duct, the exhaust conduit secured to the exhaust case via the flange; and a stiffener protruding transversally from the flange, the flange located between the duct and the stiffener.

Abstract: An aircraft engine, has: a turbine including a turbine rotor rotatable about a central axis; a scroll case having an inlet fluidly connected to a source of combustion gases and an outlet fluidly connected to the turbine, and a conduit extending around the central axis from the inlet to the outlet; a bearing housing extending around the central axis; and a flange connecting the scroll case to the bearing housing, the flange having a first end connected to the scroll case, a second end connected to the bearing housing, and a deflecting wall section extending between the first end and the second end, the deflecting wall section being spaced apart from the scroll case by an annular gap, the deflecting wall section of the flange being deformable in a radial direction.

Abstract: An aircraft engine, has: a turbine including a turbine rotor rotatable about a central axis; a scroll case having an inlet connected to a source of combustion gases and an outlet connected to the turbine, and a conduit extending around the central axis from the inlet to the outlet; a bearing housing including a support flange; a turbine support case secured to the bearing housing, the scroll case disposed between the turbine support case and the bearing housing, the turbine support case having spokes extending through the scroll case and radially supported by the bearing housing, a spoke of the spokes having a distal end secured to the support flange via: one or more fasteners, and a bracket secured to the support flange, the bracket engaged in a slot having an axially facing surface trapped between the bracket and the support flange of the bearing housing.

Abstract: An engine includes a bearing assembly. The bearing assembly includes a bearing compartment housing, a first bearing, and a second bearing. The bearing compartment housing extends circumferentially about a rotational axis. The bearing compartment housing includes an outer housing body, an inner housing body, and a plurality of struts. The outer housing body surrounds and forms a bearing compartment. The inner housing body extends between and to an inner radial side and an outer radial side. The inner housing body forms a plurality of transverse slots extending through the inner housing body from the inner radial side to the outer radial side. The plurality of struts connect the inner housing body and the outer housing body. The first bearing is mounted on the inner housing body at a first axial position. The second bearing is mounted on the inner housing body at a second axial position.

Abstract: An assembly is provided for a powerplant. This powerplant assembly includes a first powerplant component, a second powerplant component, a plurality of fasteners and an insert. The first powerplant component includes a first component mount and a plurality of first component apertures. The first component apertures are arranged circumferentially about an axis and extend axially through the first component mount. The first component apertures include a plurality of first component fastener apertures and a first component insert aperture. The second powerplant component includes a second component mount and a plurality of second component fastener apertures. The fasteners attach the first component mount and the second component mount together. Each of the fasteners is mated with a respective one of the first component fastener apertures and a respective one of the second component fastener apertures. The insert is threaded into the first component insert aperture. The insert includes a threaded bore.

Abstract: An aircraft engine, has: a turbine including a turbine rotor rotatable about a central axis; a scroll case having an inlet connected to a source of combustion gases and an outlet connected to the turbine, and a conduit extending around the central axis from the inlet to the outlet; a bearing housing including a support flange; a turbine support case secured to the bearing housing, the scroll case disposed between the turbine support case and the bearing housing, the turbine support case having spokes extending through the scroll case and radially supported by the bearing housing, a spoke of the spokes having a distal end secured to the support flange via: one or more fasteners, and a bracket secured to the support flange, the bracket engaged in a slot having an axially facing surface trapped between the bracket and the support flange of the bearing housing.

Abstract: An engine includes a rotational assembly and a bearing assembly. The rotational assembly includes a shaft rotatable about a rotational axis. The bearing assembly includes a housing and a bearing. The housing surrounds and forms a bearing compartment. The housing includes a housing body extending circumferentially about the rotational axis. The housing body forms a first air flow path and a second air flow path. The first air flow path extends from a first inlet plenum to a first outlet plenum. The second air flow path extends from a second inlet plenum to a second outlet plenum. The second air flow path is disposed between and separating the first air flow path and the bearing compartment. The bearing is disposed within the bearing compartment. The bearing is rotationally engaged with the shaft.

Abstract: An assembly is provided for an aircraft powerplant. This powerplant assembly includes a bladed rotor and a stationary structure. The bladed rotor is rotatable about an axis. The bladed rotor includes a rotor disk and a plurality of rotor blades. The rotor disk includes a web and a rim with a concave disk surface at an inside corner between the web and the rim. The concave disk surface has a disk surface sectional geometry in a reference plane parallel with the axis. The rotor blades are arranged circumferentially around and project radially out from the rim. The stationary structure includes a lip with a convex lip surface. The convex lip surface is next to the concave disk surface. The convex lip surface has a lip surface sectional geometry in the reference plane that matches the disk surface sectional geometry.

Abstract: An engine includes a rotational assembly and a bearing assembly. The rotational assembly includes a shaft rotatable about a rotational axis. The bearing assembly includes a housing and a bearing. The housing surrounds and forms a bearing compartment. The housing includes a housing body extending circumferentially about the rotational axis. The housing body forms a first air flow path and a second air flow path. The first air flow path extends from a first inlet plenum to a first outlet plenum. The second air flow path extends from a second inlet plenum to a second outlet plenum. The second air flow path is disposed between and separating the first air flow path and the bearing compartment. The bearing is disposed within the bearing compartment. The bearing is rotationally engaged with the shaft.

Abstract: A gas turbine engine includes a turbine section, a turbine case, an inner case, and a damping seal baffle. The turbine section extends along a rotational axis of the gas turbine engine. The turbine case includes a cantilevered inner wall. The cantilevered inner wall extends circumferentially about the rotational axis. The cantilevered inner wall extends between and to an upstream axial end and a downstream axial end. The upstream axial end is disposed at and downstream of the turbine section. The cantilevered inner wall forms a seal platform surface. The inner case extends circumferentially about the rotational axis. The inner case is disposed radially inward of the upstream axial end. The damping seal baffle extends circumferentially about the rotational axis. The damping seal baffle is mounted to the inner case. The damping seal baffle is disposed in contact with the seal platform surface.

Abstract: An aircraft engine, has: a turbine rotatable about a central axis; a scroll case having an inlet and an outlet connected to the turbine, and a conduit extending around the central axis from the inlet to the outlet; a bearing housing extending around the central axis and including a support flange; and a turbine support case secured to the bearing housing, the turbine support case having spokes distributed around the central axis and extending along a direction having an axial component relative to the central axis, the spokes extending through the scroll case and radially supported by the bearing housing, one of the turbine support case and the scroll case defining lugs circumferentially distributed around the central axis, the other of the turbine support case and the scroll case defining slots, the turbine support case and the scroll case circumferentially locked to one another via the lugs engaging the slots.

Abstract: A turbine exhaust case is disclosed herein. The turbine exhaust case including an outer shroud having a cylindrical shape and extending in a first direction parallel to a center of axis and extending circumferentially around the center axis, an inner shroud having frustoconical shape, the inner shroud disposed within the outer shroud, the inner shroud extending circumferentially around the center axis, a plurality of struts coupled to the outer shroud and the inner shroud, an inner cone having a frustoconical shape, the inner cone coupled to and extending into the inner shroud, the inner cone extending circumferentially around the center axis, the inner cone tapering at a first angle with respect to the center axis, the first end of the inner cone being coupled to the second end of the inner shroud, and a flat surface coupled the second end of the inner cone.

Abstract: During a disassembly method, a nut is unthreaded from a tie shaft. Prior to the unthreading of the nut, the tie shaft is threaded into a first rotating structure, a second rotating structure is mounted to the first rotating structure by a first tight fit connection, a third rotating structure is mounted to the second rotating structure by a second tight fit connection, and the second rotating structure and the third rotating structure are axially stacked and secured between the first rotating structure and the nut. The tie shaft is unthreaded from the first rotating structure. The tie shaft is axially translated to abut a shoulder of the tie shaft against an axial distal end of the second rotating structure.

Abstract: A gas turbine engine includes a rotational assembly and a bearing assembly. The rotational assembly includes a shaft. The bearing assembly includes a bearing compartment housing and at least one bearing. The bearing compartment housing includes a housing body and at least one feed hole plug. The housing body forms a first air flow path. The first air flow path includes a first inlet plenum, a first outlet plenum, and a plurality of first air flow path feed holes. The plurality of first air flow path feed holes includes a plurality of first feed holes and a plurality of second feed holes connecting the first inlet plenum in fluid communication with the first outlet plenum. The plurality of first feed holes includes at least one obstructed feed hole and at least one unobstructed feed hole. The at least one bearing is mounted to the housing body. The at least one bearing is rotationally engaged with the shaft.

Abstract: A turbine exhaust duct (TED) for an aircraft engine, has: a body having a central axis and having an inner wall and an outer wall conjointly defining an annular inlet conduit and outlet conduits communicating with the annular inlet conduit and extending generally radially outward relative to the annular inlet conduit along conduit axes extending transversally to the central axis, the body defining a central passage located radially inwardly of the annular inlet conduit, the outlet conduits having transition areas transitioning from a mainly axial direction to a mainly radial direction; and stiffeners secured to the body and located within the central passage at circumferential positions being in register with the outlet conduits, the stiffeners secured to the transition areas of the outlet conduits, the stiffener extending transversally to both of the central axis and the conduit axes.

Abstract: During a disassembly method, a nut is unthreaded from a tie shaft. Prior to the unthreading of the nut, the tie shaft is threaded into a first rotating structure, a second rotating structure is mounted to the first rotating structure by a first tight fit connection, a third rotating structure is mounted to the second rotating structure by a second tight fit connection, and the second rotating structure and the third rotating structure are axially stacked and secured between the first rotating structure and the nut. The tie shaft is unthreaded from the first rotating structure. The tie shaft is axially translated to abut a shoulder of the tie shaft against an axial distal end of the second rotating structure.