An exhaust gas liner for a gas turbine includes an annular inner shell and an annular outer shell, which are arranged concentrically around a machine axis of the gas turbine to define an annular exhaust gas channel in between. The inner shell and/or said outer shell are composed of a plurality of liner segments, which are attached to a support structure. To compensate thermal expansion and achieving resistance against dynamic loads, the liner segments are fixed to the support structure at certain fixation spots, which are distributed over the area of said liner segments, such that said liner segments are clamped to said support structure through a whole engine thermal cycle without hindering thermal expansion.

A cooled flange connection of a gas-turbine engine is annular and includes a first flange of a first component, at least a second and central flange of a second component, and a third flange of a third component. At the contact area between the first and the second flange a first circumferential duct is provided that extends over at least part of the circumference. At the contact area between the second and the third flange a second circumferential duct is provided that extends over at least part of the circumference. The first and second circumferential ducts are connected to one another by axial connecting recesses. The first flange is provided with at least one inflow recess connected to the first circumferential duct. The third flange is provided with at least one outflow recess connected to the circumferential duct.

A cooled flange connection of a gas-turbine engine is annular and includes a first flange of a first component, at least a second and central flange of a second component, and a third flange of a third component. At the contact area between the first and the second flange a first circumferential duct is provided that extends over at least part of the circumference. At the contact area between the second and the third flange a second circumferential duct is provided that extends over at least part of the circumference. The first and second circumferential ducts are connected to one another by axial connecting recesses. The first flange is provided with at least one inflow recess connected to the first circumferential duct. The third flange is provided with at least one outflow recess connected to the circumferential duct.

There is disclosed a method of manufacturing a semi-annular component 60 for a casing arrangement of a gas turbine by additive manufacture, the component having a lattice structure 84 and extending circumferentially about a central axis 11 so that a radial direction extends towards the central axis 11. The method comprises: fusing material at successive build locations along a build direction 98 to progressively form the component 60 so that members 86 of the lattice structure 84 have an elongate direction having a circumferential component; wherein the build direction 98 lies in a plane substantially normal to the central axis; and wherein the build direction 98 is inclined with respect to the radial direction at each build location so that members 86 of the lattice structure 84 are progressively formed along their elongate direction. A semi-annular component including a seal carrier is also disclosed.

Systems and methods for cooling a core flow-path of a compressor section of a gas turbine engine are provided. In various embodiments, a cooling system for a gas turbine engine may comprise a valve system located radially outward from an engine case, the valve system being coupled between an air duct and the engine case, the valve system having an actuation device configured to at least one of open or close a valve in response to a command from an electronic engine controller, wherein cooling air from the air duct can pass through the valve system and enter the engine case into a high pressure compressor plenum when the valve system is in an open position.

Partition damper seal configurations for segmented internal cooling hardware apparatus are disclosed. An example apparatus includes an inner wall and an outer wall, the outer wall spaced apart from the inner wall in a radial direction, a space between the inner and outer walls defining a flow passage, and a body positioned between the inner and outer walls, the body traversing the inner and outer walls in an axial direction and attached to an inner surface of the outer wall and an outer surface of the inner wall, the body to detach from the inner and outer surfaces and to at least partially seal the flow passage in response to the outer wall moving relative to the inner wall.

Partition damper seal configurations for segmented internal cooling hardware apparatus are disclosed. An example apparatus includes an inner wall and an outer wall, the outer wall spaced apart from the inner wall in a radial direction, a space between the inner and outer walls defining a flow passage, and a body positioned between the inner and outer walls, the body traversing the inner and outer walls in an axial direction and attached to an inner surface of the outer wall and an outer surface of the inner wall, the body to detach from the inner and outer surfaces and to at least partially seal the flow passage in response to the outer wall moving relative to the inner wall.

A turbine shroud assembly for a gas turbine engine includes a shroud wall extending circumferentially partway around a central reference axis to define a gas path of the gas turbine engine. An attachment feature extends radially from the shroud wall. A foam is located at least on the shroud wall.

Aspects of the disclosure regard a fan case assembly for a gas turbine engine, the fan case assembly comprising a fan case having an inner surface, a fan case liner having an outer surface, and a reclosable fastening system attaching the fan case liner to the fan case, the reclosable fastening system comprising two components, a first component being attached to the fan case inner surface and a second component being attached to the fan case liner outer surface.

A turbine housing (1) of an exhaust-gas turbocharger (15) having a turbine volute (7) which is delimited by a metallic outer shell (8) and which has an inner wall (9); and a heat insulation layer (10) which is arranged on the inner wall (9) and which has a heat insulation core (6A, 6B) which, on its surface (12A, 12B) facing into a volute interior space (11), is covered by a first sheet-metal shell (3A, 3B). The heat insulation core (6A, 6B) is covered, on a surface (13A, 13B, 13′B) facing toward the inner wall (9), by a second sheet-metal shell (4A and 4B respectively).