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 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 for an aircraft engine of an aircraft having a direction of travel, has: a turbine exhaust duct (TED) having an annular inlet conduit extending around a central axis for directing combustion gases generally in an axial direction and outlet conduits communicating with the annular inlet conduit and extending generally radially outward relative to the annular inlet conduit; and an exhaust case enclosing the TED, the exhaust case extending from a forward end to a rearward end relative to the direction of travel, the exhaust case having openings, each of the outlet conduits received through a respective one of the openings; and reinforcing members secured to the exhaust cases between the forward end and the rearward end, the reinforcing members being located opposite circumferential sides of the openings and locally increasing a thickness of the exhaust case.

Abstract: An exhaust system for an aircraft engine, has: a turbine exhaust duct (TED) having an annular inlet conduit extending around a central axis for directing combustion gases generally in an axial direction, 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: a frustoconical section extending from a fore end at an intersection with a remainder of the exhaust case to an aft end securable to a turbine case of the aircraft engine, the frustoconical section converging towards the central axis from the fore end to the aft end; and a connecting flange at the aft end, the connecting flange protruding inwardly towards the central axis.

Abstract: A turbine exhaust duct (TED) for an aircraft engine, has: an annular inlet conduit extending around a central axis for directing combustion gases generally in an axial direction; outlet conduits communicating with the annular inlet conduit and extending generally radially outward relative to the annular inlet conduit, the outlet conduits extending from inlet ends at intersections with the annular inlet conduit to outlet ends, an outlet conduit of the outlet conduits having: a forward section facing an axially forward direction and a rearward section opposite the forward section, the forward section and the rearward section conjointly defining an outlet end of the outlet ends; and a reinforcement plate secured to the forward section, the reinforcement plate having a thickness greater than a baseline thickness of the outlet conduit outside the reinforcement plate.

Abstract: An exhaust system for an aircraft engine, has: a turbine exhaust duct (TED) having an annular inlet conduit extending around a central axis for directing combustion gases generally in an axial direction, and outlet conduits branching off from the annular inlet conduit; and an exhaust case surrounding the TED, the exhaust case being frustoconical and having outlet openings each communicating with a respective one of the outlet conduits, a probe opening extending through the exhaust case and bounded by a periphery, and a probe interface mounted to the periphery of the probe opening, the probe interface including an interfacing plate secured to the periphery of the probe opening and defining an aperture sized to receive a probe therethrough, the aperture located radially inwardly of the probe opening.

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.