A turbine shaft used for a turbocharger including a turbine and a compressor includes a turbine impeller, and a rotor shaft joined on one end side to the turbine impeller. The rotor shaft includes a fitting region configured to fit with a compressor impeller of the compressor by inserting the other end side of the rotor shaft into a through hole formed in the compressor impeller, a fastening region formed between the fitting region and the other end side of the rotor shaft, and configured to allow fastening by a fastening part, and a tapered part having a maximum outer diameter at a position closest to the turbine impeller in the fitting region and formed such that an outer diameter of the rotor shaft decreases from the position closest to the turbine impeller toward a tip side of the compressor impeller.

A compressor housing for a turbocharger may include an outer volute having an outer volute inner surface with a clamp groove defined therein, and an inner volute having an inner volute outer surface and an axially facing surface. The inner volute is inserted into the outer volute through the outer volute inner surface with the inner volute outer surface facing the outer volute inner surface. The inner volute is positioned with the axially facing surface disposed axially inward of the clamp groove. A clamp plate includes a radially outward portion inserted into the clamp groove and a radially inward portion extending downward past the inner volute outer surface. The clamp groove and the axially facing surface engage the clamp plate to retain the inner volute within the outer volute when an axial load is applied to the inner volute.

Provided is a turbine housing (10) having: a housing part (11) that forms a spiral space (S5) extending around a rotating shaft (40); a heat-shielding core (12) which is disposed in the spiral space (S5) and forms a spiral exhaust gas flow passage (S6) in which exhaust gas introduced from an exhaust gas introduction port flows; and a variable nozzle mechanism (13) that guides the exhaust gas to a turbine wheel, wherein heat-shielding spaces (S1, S2, S3) are formed between the inner circumferential surface of the housing part (11) and the outer circumferential surface of the heat-shielding core (12), and wherein the heat-shielding core (12) has a first flange part (12d) and a second flange part (12e) and is fixed between the variable nozzle mechanism (13) and the housing part (11) while a first sealing (14) is interposed between the first flange part (12d) and the variable nozzle mechanism (13).

A turbine includes: an inner diameter side exhaust flow path; an outer diameter side exhaust flow path having a flow path cross-sectional area smaller than a flow path cross-sectional area of the inner diameter side exhaust flow path; an inner diameter side bypass flow path connecting the inner diameter side exhaust flow path and a discharge flow path; and an outer diameter side bypass flow path connecting the outer diameter side exhaust flow path and the discharge flow path, the outer diameter side bypass flow path having a flow path cross-sectional area larger than a flow path cross-sectional area of the inner diameter side bypass flow path.

A cylinder head assembly for an internal combustion engine includes a cast cylinder head, a turbocharger housing including a compressor housing and turbine housing integrally cast with the cylinder head, and a turbocharger cartridge assembly configured to be inserted into the turbocharger housing and including a shaft coupled between a compressor wheel and a turbine wheel. A compressor cover is configured to couple to the compressor housing and define a compressor inlet and at least partially define a compressor diffuser passage. The cartridge assembly includes a housing having a diffuser flange extending outwardly therefrom, the diffuser flange including a front surface and an opposite contoured volute surface. The compressor diffuser passage is at least partially defined by the compressor cover and the diffuser flange front surface. A compressor volute is at least partially defined by the diffuser flange contoured volute surface and a contoured inner surface of the compressor housing.

The present invention relates to a valve arrangement (100) for a multi-channel turbine (10), having a housing section (300) with a first volute (320), with a second volute (340) and with a connecting region (360) between the first volute (320) and the second volute (340), and having a valve body (110) for closing off the connecting region (360) in a closed position of the valve body (110). A wall region (370) of the housing section (300), which wall region is arranged in the connecting region (360) and is situated opposite the valve body (110) in the closed position, is configured to be optimized in terms of flow to increase, during operation of the valve arrangement (100), a rate of flow transfer of exhaust gas between the first volute (320) and the second volute (340) in an open position of the valve body (110).

There is provided a compact turbine-compressor assembly 25. The turbine-compressor assembly 25 includes a turbine wheel 39 with one or more turbine blades 41 and a compressor wheel 47 that includes one or more compressor blades 49. The compressor wheel 47 is concentric with the turbine wheel 39. Furthermore, the compressor wheel 47 and the turbine wheel 39 are not located at opposite ends of a common axle with a medial portion of the axle distancing them apart, as is the case with prior art turbine-compressor assemblies that are known. In contrast, the turbine wheel 39 and the compressor wheel 47 are located adjacent to each other and in one embodiment they axially overlap each other so that one nests within the other to thereby provide a compact arrangement. The turbine-compressor assembly 25 includes a first fluid path 67 which is configured to convey fluid, which will typically be air, through the turbine blades 41. The turbine-compressor assembly 25 also includes a second fluid path 77 which is configured to convey fluid, which will typically be air, through the compressor blades. The turbine-compressor assembly 25 is arranged so that the first fluid path 67 is distinct from the second fluid path 77 and vice-versa.

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.

A variable geometry turbine comprising: a wheel supported for rotation about an axis; a housing comprising a first volute for receiving gas from a first source and a second volute for receiving gas from a second source; the first and second volutes being separated by a dividing wall; and an inlet passageway surrounding the wheel and fluidly connected to the volutes; the inlet passageway at least partially defined between a first wall and an opposite second wall, the first wall being moveable along the axis to vary the size of the inlet passageway; wherein a tip of the dividing wall defines a first radius relative to the axis, and a radially outermost part of the first wall positioned within the inlet passageway defines a second radius relative to the axis, and wherein the first radius is at least around 1% larger than the second radius.

An impeller for a centrifugal compressor, the impeller rotatable about a central axis, has: an outer hub body including a first material and extending around the central axis, the outer hub body defining a gaspath face extending from an inlet to an outlet, the gaspath face extending radially away from the central axis from the inlet to the outlet; blades protruding from the gaspath face and circumferentially distributed around the central axis; and an inner hub body extending around the central axis, the inner hub body secured to the outer hub body, the outer hub body axially overlapping and extending around the inner hub body, the inner hub body made of a second material being more cold dwell resistant than the first material.