An assembly having an outer tubular portion delimiting an inner space, an inner tubular portion in the outer tubular portion, a fluid jacket in the inner tubular portion, a plurality of groups of at least four thermal flow sensors. For each group, the sensors of the group are disposed in the inner space and overall in one and the same plane perpendicular to a central line. In each group, the sensors of the group are distributed angularly about the central line. A control unit which, for each group, receives the data from each sensor of the group and which, on the basis of these data, determines a warning level. With such an arrangement, the monitoring of the values of the different thermal flow sensors makes it possible to monitor a potential problem at the fluid jacket.

A method includes drilling a first aperture in a panel that extends between a panel first surface and a panel second surface. The first aperture projects into the panel along a first centerline from the panel first surface. The first centerline is angularly offset from the panel first surface by a first angle. A first tool is arranged with the panel. The first tool includes a support structure, a locator and a drill guide. The locator is mounted to the support structure and projects into the first aperture. The drill guide is mounted to the support structure and is arranged adjacent the panel second surface. A second aperture is drilled in the panel using the drill guide. The second aperture projects into the panel along a second centerline from the panel second surface to the first aperture. The second centerline is coaxial with the first centerline.

A method of assembling a turbocharger having a vaned turbine nozzle includes first forming a sub-assembly of a center housing, shaft, bearings, compressor wheel, turbine wheel, and vane assembly. The vane assembly is held captive in attachment to the center housing by an annular heat shield that includes prongs or the like at its inner and outer peripheries for respectively engaging a first catch formed on the center housing and a second catch formed on the nozzle ring of the vane assembly. The heat shield forms a snap fit to the center housing and nozzle ring, thereby connecting the cartridge to the center housing. The whole sub-assembly is then joined to the turbine housing, in the process axially compressing the heat shield and a spring shroud for exerting an axial biasing force on the nozzle ring.

A turbo shield with a slit, wherein the slit is configured to allow an inner diameter across the turbo shield to increase and decrease without altering the properties of fibers associated with the turbo shield.

Embodiments of the present invention may include a turbocharger having a turbine, a turbine housing, a variable valve, a first plate, a second plate and a heat shield member. The turbine housing accommodates the turbine and has a flow path. The variable valve rotates about each pivot member provided thereon, thereby adjusting the flow velocity of fluid guided from the flow path to the turbine. The first plate supports one end of each pivot member, and defines the flow path. The second plate supports the other end of each pivot member or the variable valves, and defines the flow path. The heat shield member covers a wall surface of the turbine housing, and defines the flow path.

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.

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.

A thermal insulation blanket assembly having a thermal insulation blanket including an aerogel insulation material having a first surface and a second surface that is oppositely-disposed from the first surface, a backing covering the second surface of the aerogel insulation material, and a skin layer covering the first surface of the aerogel insulation material.

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.

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).