Abstract: The present invention relates to an actuation device for a compressor inlet adjustment mechanism. The actuation device comprises a housing part and a lever assembly. The lever assembly comprises a bearing section, an input section and an output section. The output section is configured to be coupled to an adjustment ring of the adjustment mechanism on a first side of the housing part. The input section can be coupled to an actuator rod on a second side of the housing part. The lever assembly is rotatably mounted in the housing part via the bearing section on the compressor inlet side here.

Abstract: A compressor with a compressor housing in which a compressor wheel is arranged. The compressor additionally includes a cartridge which is arranged in the compressor housing in the area of a compressor inlet. The cartridge is designed to variably change the cross section of the compressor inlet.

Abstract: The invention relates to a turbine comprising a turbine housing defining a volute having a substantially annular outlet opening, a turbine wheel, and an adjusting ring, rotatable about the turbine axis, which is arranged in the turbine housing radially between the volute and the turbine wheel, wherein the adjusting ring comprises a flow channel between a radially outer first peripheral opening and a radially inner second peripheral opening, and wherein the outlet opening is fluidically coupled to the turbine wheel by the flow channel. The outlet opening and the first peripheral opening have a path, variable in the axial direction, so that during a rotation of the adjusting ring, the outlet opening and the first peripheral opening are adjusted relative to each other in such a way that an overflow cross section between the outlet opening and the first peripheral opening is variably changeable.

Abstract: A cartridge for use in a pulse energy enhanced turbine of a turbocharger. At least first and second fixed separating blades (12) are provided between a nozzle ring (6) and a disk (29), the separating blades (12) maintaining separation of exhaust gas flows through a guide grid between a divided volute and a turbine wheel (11).

Abstract: A turbocharger with at least one axial turbine stage. Separate circumferential sections of the turbine are fed by separate exhaust system runners. The turbine is designed to harness pulse energy. Corresponding engine having cylinders comprising such a turbocharger.

Abstract: A number of variations may include a product including a mixing device comprising a housing including a first fluid intake port, a fluid output port, a fluid flow conduit transversely connecting the first fluid intake port to the fluid output port, a second fluid intake port radially distal from the fluid flow conduit, and an at least partially annular second fluid flow compartment radially connecting the second fluid intake port to the fluid flow conduit, wherein the second fluid flow compartment is oriented to at least partially surround a portion of the fluid flow conduit and wherein the second fluid flow compartment is constructed and arranged to facilitate the mixing of incoming first fluid flow and incoming second fluid flow to create a fluid mixture that flows through the fluid flow conduit.

Abstract: A multi-flow exhaust gas turbocharger (101) comprising a turbine (105), a turbine wheel, a first flow (1) and a second flow (2), a bypass line (6) for bypassing the turbine wheel, a bypass valve unit (107) for adjusting the size of a bypass exhaust gas flow through the bypass line (6), and comprising a flow connection unit (108) for adjusting an extent of the connection of exhaust gas flows into the flows (1, 2), characterized in that the bypass valve unit (107) and the flow connection unit (108) can be actuated in a mechanically coupled way by means of a coupling unit (109).

Abstract: A number of variations may include a method of optimizing inlet guide vane performance comprising: modifying an inlet guide vane to include at least one of a twist, a curve, a surface texture, a sealing feature, a tip leakage reduction feature, an airfoil having at least one component, or at least one channel.