A heat shield assembly for an engine case of a gas turbine engine may include a heat shield and a support lock. The heat shield may have an annular shape and a groove formed circumferentially along an inner surface of the heat shield. The support lock may have a tab extending radially outward from a distal surface of the support lock. The groove in the heat shield may be configured to retain the tab of the support lock.

A heat shield assembly for an engine case of a gas turbine engine may include a heat shield and a support lock. The heat shield may have an annular shape. The heat shield may define an aperture extending through the heat shield. The support lock may have a tab extending radially outward from a distal surface of the support lock. The aperture in the heat shield may be configured to retain the tab of the support lock.

A thermal management system for a heat engine, the system including an forming at least in part a core flowpath and a cavity, wherein the core flowpath and the cavity are separated by a double wall structure formed by at least a portion of inner wall, and wherein the double wall structure includes a plenum. A first opening provides fluid communication between the cavity and the plenum, and a second opening provides fluid communication between the plenum and the core flowpath. The inner wall is configured to receive a first flow of fluid. An outer wall forms a passage extended at least partially around the core flowpath. The outer wall is configured to receive a second flow of fluid fluidly separated from the core flowpath.

A turbocharger includes a turbine housing adapted to be arranged in the middle of an engine exhaust passage, a bearing housing coupled to the turbine housing, a turbine wheel located inside the turbine housing, a rotary shaft that is connected to the turbine wheel and is rotationally supported by the bearing housing, and a cooling water passage that is provided inside the turbine housing. The cooling water passage is located around the turbine wheel. The turbine housing includes a first connection portion joined to the bearing housing, a second connection portion joined to a part of the engine exhaust passage located on a downstream side of the turbine housing, and a heat insulating portion located between the cooling water passage and at least one of the first connection portion and the second connection portion.

An internal combustion engine has a cylinder head with at least one cylinder and a cooled turbine. Each cylinder has at least one outlet opening adjoined by an exhaust line for discharging exhaust gases from the cylinder. The exhaust line issues into an inlet region transitioning into an exhaust gas-conducting flow duct of the turbine. The turbine has at least one rotor mounted on a rotatable shaft in a turbine housing. The turbine has at least one coolant duct which is integrated in the housing and which is delimited and formed by at least one wall of the housing to form a cooling arrangement. The at least one wall of the turbine housing that delimits the at least one coolant duct is provided, at least in regions, with a thermal insulation.

A flowpath apparatus for a gas turbine engine includes: a plurality of ducts arranged in an array, each duct including a peripheral wall structure having a closed perimeter that defines a flow channel from an upstream end to a downstream end thereof; and a support structure positioning a the plurality of ducts in an array configuration.

A carbon dioxide cycle power generation system includes storage collectively storing portions of carbon dioxide liquid and gas and a transfer connection selectively directing flow of the carbon dioxide through a turbine. The system cycles between different seawater depths in order to employ at least one of seawater pressure and seawater temperature in creating the carbon dioxide flow. Inlet/outlet control valves on variable volume tanks, positioned below movable pistons within the respective tank, selectively allow seawater into or out of a lower portion of the respective tank below the piston to pressurize the carbon dioxide therein relative to the carbon dioxide within the other tank when at depth rather than near the surface. Inhibited versus uninhibited heat transfer between storage portions and the seawater allows different seawater temperatures at depth and near the surface to create the carbon dioxide flow. Acoustic communications may be driven concurrent with the turbine.

A heat shield provided with a gas turbine engine includes a heat shield body extending between a first heat shield end and a second heat shield end. The heat shield body has an exterior surface disposed proximate an inner surface of a first case and an interior surface disposed opposite the exterior surface. The interior surface defines a rib that extends towards a combustor vane support lock.

An internal casing ferrule for a turbomachine, centered on a longitudinal central axis, which includes: a main body centered on this axis, with two ends, delimited by surfaces that are radially inner and outer relative to this axis; a thermal porous-structure insulation envelope having a volumetric porosity ≥50%, which includes: a lateral portion entirely covering the two ends; when viewed in section transversely to this axis, exterior and interior portions entirely covering, respectively, the radially outer and inner surfaces of the main body; and a protective envelope which at least partially covers the envelope and which includes, when viewed in section transversely to this axis, radially outer and inner protective portions, respectively covering, at least in part, the exterior and interior portions.

A turbine frame cooling system for use with a gas turbine engine includes an outer ring defining a cavity and a hub positioned radially inward of the outer ring. The turbine frame cooling system also includes a plurality of circumferentially-spaced first fairings coupled between the outer ring and the hub and a plurality of circumferentially-spaced second fairings coupled between the outer ring and the hub, wherein the first and second fairings are alternatingly positioned about the hub. The turbine frame cooling system also includes a plurality of circumferentially-spaced air scoops coupled to the outer ring. The plurality of air scoops extend into a bypass stream and are configured to channel a bypass air cooling flow into the cavity of the outer ring.