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: 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: A core gas path boundary structure is provided that includes an annular housing panel and a baffle. The annular housing panel has a first end segment and a second end segment. The first end segment of the housing panel (HPFES) has an HPFES outer radial surface and a HPFES support rail extending radially outward from the HPFES outer radial surface. The baffle has a body and a first stiffening ring. The body has a baffle first end segment and a baffle second end segment. The first stiffening ring is attached to an inner radial surface of the baffle first end segment. The first stiffening ring has an edge surface. The baffle is engaged with the annular housing panel such that the baffle first end segment is in contact with the HPFES support rail. The edge surface of the first stiffening ring is radially aligned with the HPFES support rail.

Abstract: A non-bypass gas turbine engine is provided that includes compressor, combustor, and turbine sections, an engine compartment enclosure, an exhaust nozzle, and a secondary exhaust nozzle. The engine compartment enclosure is disposed radially outside of the compressor, combustor, and turbine sections and defines a first annular region outside of the compressor, combustor, and turbine sections. The exhaust nozzle is disposed downstream of the turbine section and is configured to receive the core gas flow exiting the turbine section. The exhaust nozzle includes a wall panel with a plurality of lobes that extend between forward and aft ends of the exhaust nozzle. Each lobe has a lobe height that increases in a direction from the forward end to the aft end of the exhaust nozzle. The lobes de-swirl the core gas flow exiting the turbine section and draw air from the first annular region during operation of the engine.

Abstract: A method of manufacturing an annular bearing housing for a gas turbine engine is provided that includes: producing a flange outer structure segment; producing an intermediate structure segment having an outer radial end, an inner radial end, a body that extends between the outer radial end and the inner radial end, and a branch member that extends outwardly from the body; producing a main body segment; attaching the flange outer structure segment to the outer radial end of the intermediate structure segment; and attaching the main body segment to the inner radial end of the intermediate structure segment. At least one of the flange outer structure segment, the intermediate structure segment, or the main body segment is produced using an additive manufacturing process.

Abstract: A containment ring for a turbine casing assembly, including: a main body portion, the main body portion having an outer periphery and an inner periphery and a forward end and an aft end each extending between the outer periphery and the inner periphery, the main body portion also including an outer containment zone and an inner containment zone, the inner containment zone is integrally formed with the outer containment zone in order to provide a single unitary structure and the inner containment zone being radially inward from the outer containment zone, the inner containment zone extending radially outward from the inner periphery and having a plurality of ribs extending between the forward end and the aft end.

Abstract: A containment ring assembly for a turbine casing assembly, including: a first inner containment ring; a second inner containment ring; an outer containment ring, the first inner containment ring and the second inner containment ring being radially inward from the outer containment ring, wherein a radial space is located between the outer containment ring and the first inner containment ring and the second inner containment ring, the radial space allowing deformation of the first inner containment ring and the second inner containment ring.

Abstract: A method of manufacturing an annular bearing housing for a gas turbine engine is provided that includes: producing a flange outer structure segment; producing an intermediate structure segment having an outer radial end, an inner radial end, a body that extends between the outer radial end and the inner radial end, and a branch member that extends outwardly from the body; producing a main body segment; attaching the flange outer structure segment to the outer radial end of the intermediate structure segment; and attaching the main body segment to the inner radial end of the intermediate structure segment. At least one of the flange outer structure segment, the intermediate structure segment, or the main body segment is produced using an additive manufacturing process.

Abstract: A containment ring assembly for a turbine casing assembly, including: a first containment ring; a second containment ring, the first containment ring being radially inward from the second containment ring, wherein a radial space is located between the first containment ring and the second containment ring, the radial space allowing deformation of the first containment ring prior to the first containment ring contacting the second containment ring.

Abstract: A containment ring for a turbine casing assembly, including: a main body portion, the main body portion having an outer periphery and an inner periphery and a forward end and an aft end each extending between the outer periphery and the inner periphery, the main body portion also including an outer containment zone and an inner containment zone, the inner containment zone is integrally formed with the outer containment zone in order to provide a single unitary structure and the inner containment zone being radially inward from the outer containment zone, the inner containment zone extending radially outward from the inner periphery and having a plurality of ribs extending between the forward end and the aft end.

Abstract: A containment ring assembly for a turbine casing assembly, including: a first inner containment ring; a second inner containment ring; an outer containment ring, the first inner containment ring and the second inner containment ring being radially inward from the outer containment ring, wherein a radial space is located between the outer containment ring and the first inner containment ring and the second inner containment ring, the radial space allowing deformation of the first inner containment ring and the second inner containment ring.

Abstract: A containment ring assembly for a turbine casing assembly, including: a first containment ring; a second containment ring, the first containment ring being radially inward from the second containment ring, wherein a radial space is located between the first containment ring and the second containment ring, the radial space allowing deformation of the first containment ring prior to the first containment ring contacting the second containment ring.

Abstract: A method of manufacturing an annular bearing housing for a gas turbine engine is provided that includes: producing a flange outer structure segment; producing an intermediate structure segment having an outer radial end, an inner radial end, a body that extends between the outer radial end and the inner radial end, and a branch member that extends outwardly from the body; producing a main body segment; attaching the flange outer structure segment to the outer radial end of the intermediate structure segment; and attaching the main body segment to the inner radial end of the intermediate structure segment. At least one of the flange outer structure segment, the intermediate structure segment, or the main body segment is produced using an additive manufacturing process.

Abstract: A rotor assembly comprises an internal snap ring seated in a groove defined in an inner diameter surface of a rotor component. The snap ring has centrifugal weights to centrifugally expand enough to compensate for a difference in thermal growth between the rotor component and the snap ring.

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: A rotor assembly comprises an internal snap ring seated in a groove defined in an inner diameter surface of a rotor component. The snap ring has centrifugal weights to centrifugally expand enough to compensate for a difference in thermal growth between the rotor component and the snap ring.

Abstract: A turbine shroud segment has a shroud body including a platform having forward and aft hooks extending from a radially outer surface of the platform for engagement with a shroud support structure of a turbine support case. A pin receiving hole is defined in the shroud body. An anti-rotation pin is engaged in the pin receiving hole. The anti-rotation pin projects outwardly from the pin receiving hole for engagement with a corresponding anti-rotation abutment on the shroud support structure.

Abstract: A turbine shroud segment has a shroud body including a platform having forward and aft hooks extending from a radially outer surface of the platform for engagement with a shroud support structure of a turbine support case. A pin receiving hole is defined in the shroud body. An anti-rotation pin is engaged in the pin receiving hole. The anti-rotation pin projects outwardly from the pin receiving hole for engagement with a corresponding anti-rotation abutment on the shroud support structure.