A turbocharger assembly can include a center housing; a turbine housing; and an insert disposed between the center housing and the turbine housing where a surface of the turbine housing and a first surface of the insert define a volute and where a surface of the center housing and a second surface of the insert define a chamber.

A thermal panel having a high temperature side located nearest a source of heat and a low temperature side. The thermal panel includes a corrugated composite material core having hot side ridges and cold side ridges. A hot side skin is attached to the hot side ridges to form a plurality of first cells. A cold side skin is attached to the cold side ridges to form a plurality of second cells. The first cells and second cells are substantially filled with an insulating material that has a thermal conductivity which is lower than the thermal conductivity of the composite material.

A combustion section for a gas turbine engine including an inner casing comprising a first material defining an inner diameter of a pressure vessel and a first heat transfer coefficient. A second material is extended at least partially over an outer diameter of the first material. The second material is disposed radially between the first material and a combustor liner. The second material defines a second heat transfer coefficient less than the first heat transfer coefficient.

An airfoil adapted for use in a gas turbine engine is disclosed. The airfoil may include components made from ceramic materials. The airfoil may include insulating material to thermally isolate portions of the airfoil.

Engine components are provided for a gas turbine engines that generate a hot combustion gas flow. The engine component can include a substrate constructed from a CMC material and having a hot surface facing the hot combustion gas flow and a cooling surface facing a cooling fluid flow. The substrate generally defines a film hole extending through the substrate and having an inlet provided on the cooling surface, an outlet provided on the hot surface, and a passage connecting the inlet and the outlet. The engine component can also include a coating on at least a portion of the hot surface and on at least a portion of an inner surface defined within the passage.

The present disclosure relates to probe sheaths adapted for a probe housing positioned within a turbomachine fluid flow path. A probe sheath according to the disclosure can include: a non-metallic sheathing material having at least one opening shaped to enclose a first portion of a fluid probe therein, the non-metallic sheathing material being sized for placement within an interior cavity of the probe housing; and a metallic sheathing material mechanically coupled to a first end of the non-metallic sheathing material and sized for placement within the interior cavity of the probe housing. The metallic sheathing material may include at least one opening in fluid communication with the at least one opening of the non-metallic sheathing material, and may be shaped to enclose a second portion of the fluid probe therein.

A solid rocket propellant grain having rocket propellant and a membrane in contact with the rocket propellant. The membrane includes a highly heat conductive pattern which affects the propellant burning rate through localized conductive heat transfer from the combustion zone and into the uncombusted propellant. Different geometries for the thermally conductive pattern produce different combustion results.

A gas turbine and nozzle system is provided that includes a radial inflow turbine rotor and a volute providing a flow path to deliver a pressurized gas to a circumference of the radial turbine rotor. The volute incorporates a shape which substantially conforms to a radial turbine shroud contour. The volute includes at least first and second parts. A mating surface between the first and second parts is substantially aligned with a direction of pressurized gas flow in the volute.

A turbocharge includes: a compressor wheel; a turbine wheel configured to rotate with the compressor wheel; a turbine housing disposed so as to cover the turbine wheel; a bearing supporting a rotational shaft of the turbine wheel rotatably; and a bearing housing accommodating the bearing. One of the turbine housing or the bearing housing includes a fin portion protruding toward the other one of the turbine housing or the bearing housing so as to extend along an axial direction of the rotational shaft, and, between the turbine housing and the bearing housing, a cavity is formed on each side of the fin portion with respect to a radial direction of the rotational shaft.

A dual wall liner for a gas turbine engine may comprise a shell having a first side and a second side, a panel contacting the shell, the panel at least partially defining a hot gas path through which a hot gas flows, wherein the first side of the shell faces the panel, wherein the shell includes a thermal barrier coating (TBC) disposed on the first side of the shell. The TBC may thermally protect the shell from heat from a hot gas path.