Abstract: A gas turbine engine is provided that includes a compressor section, a combustor section, and a turbine section. The turbine section includes a rotor stage and an annular shroud assembly. The annular shroud assembly is disposed radially outside of a bladed rotor, and extends circumferentially around the bladed rotor, and is coupled with a turbine support case. The annular shroud assembly includes a shroud, a shield member, a shroud retaining ring, and a cover. The shroud includes a plurality of shroud segments. Each shroud segment includes a ring portion, a forward leg, and an aft leg. The shield member has a central channel. The shroud retaining ring is disposed in the central channel. The cover is coupled with the turbine support case. The shield member is disposed between the shroud retaining ring and the shroud. The shroud is mounted to the cover and the turbine support case.

Abstract: A gas turbine engine is provided that includes a compressor section, a combustor section, and a turbine section. The turbine section includes a rotor stage and an annular shroud assembly. The rotor stage includes a bladed rotor. The annular shroud assembly is disposed radially outside of the bladed rotor, and extends circumferentially around the bladed rotor, and is coupled with a turbine support case. The annular shroud assembly includes a shroud, a shroud segment housing, a cover, and a plurality of shroud pins. The shroud includes a plurality of shroud segments that collectively form the shroud. Each shroud segment includes a ring portion, a forward leg, and an aft leg. The shroud pins are disposed to connect the shroud to the shroud segment housing and the cover. The shroud segment housing and the turbine support case are engaged with one another and are configured to permit relative movement therebetween.

Abstract: A scroll case configured for directing combustion gases to a turbine section of an aircraft engine, comprises an outer shell extending around a central axis and having an inlet for receiving the combustion gases, and an inner casting received inside the outer shell and defining therewith a conduit extending around the central axis from the inlet to an axially oriented outlet for directing the combustion gases to the turbine section of the aircraft engine. The inner casting has vanes circumferentially distributed around the central axis and projecting axially across the conduit from a front axially facing surface of the inner casting to a rear axially facing surface of the outer shell. The vanes are fastened to the rear axially facing surface of the outer shell around the axially oriented outlet.

Abstract: An aircraft engine, has: a combustion engine having an exhaust and drivingly engaged to a load rotatable relative to a central axis; a turbine section engaged with the load; and a scroll case assembly interconnecting the exhaust to the turbine section and having a plurality of sheet metal parts interconnected via braze or weld joints to define a conduit, the sheet metal parts including: a housing extending from a fore end to an aft end; a fore cover having a fore outer periphery secured to the fore end of the housing and a fore inner periphery, an aft cover extending radially from an aft outer periphery secured to the aft end to an aft inner periphery; and vanes distributed around the central axis and located radially between the housing and the fore cover, opposite ends the vanes secured to the radial portion of fore cover and to the aft cover.

Abstract: An aircraft engine including a scroll case extending around a central axis and having an inlet fluidly connected to a source of combustion gases and an outlet, and a conduit extending around the central axis from the inlet to the outlet. The conduit includes an outer wall and a radially inward inner wall, the outlet defined radially between the inner wall and the outer wall. A turbine is downstream of the outlet of the scroll case relative to a flow of the combustion gases. Vanes are circumferentially distributed around the central axis, the vanes being removably mounted to the scroll case proximate to the outlet of the conduit and radially between the inner wall and the outer wall.

Abstract: A gas turbine engine has a bearing housing concentrically disposed inside the inner case of a turbine exhaust case (TEC). The bearing housing has a tubular body and an outer flange projecting from a radially outer surface of the tubular body. The outer flange has an axially extending segment spaced from the radially outer surface of the tubular body by an annular gap. The axially extending segment has a radially outer end surface connectable, such as by welding, to a mating flange projecting radially inwardly from the inner case of the TEC.

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.