An internal combustion engine (20) has two exhaust valves (24, 25) for each combustion chamber, to permit separation of blow-down and expulsion phases of an exhaust stroke. The separate exhaust streams are directed to different geometries of an exhaust turbocharger (30), so as to make best use thereof. Variable exhaust valve timing, and bypass passage for the exhaust streams are disclosed.

An exhaust passage including a protrusion which is less likely to receive heat from a gas and hence has high heat-resistance reliability is provided. An exhaust passage includes an exhaust pipe, and a protrusion continuously formed over a range of a part of an inner surface of the exhaust pipe in a circumferential direction thereof, the protrusion being inclined toward a direction in which the exhaust pipe extends, and being configured in such a manner that a cross-sectional area of the exhaust pipe becomes smaller toward a downstream side thereof, in which the exhaust passage further includes a convex part on an inner surface of the protrusion.

A turbine with multiple gas inlets is designed by a process of, for a given engine, obtaining time series data characterizing the power bias of the engine, obtaining an isentropic power associated with each data point of the time series, and using the isentropic powers to obtain a design point. The turbine is then designed based on the design point, such as by optimising one or more design parameters of the turbine based on the design point.

An internal combustion engine has first and second combustion chambers, first and second exhaust gas line elements, and an exhaust gas turbocharger which has a first flood, a second flood, and a third flood. A bypass device has a bypass line that can be flowed through by exhaust gas from the first and second exhaust gas line elements and via the bypass line a turbine wheel is bypassed by a first part of the exhaust gas from the first and second exhaust gas line elements. A valve device includes a first valve element, via which an amount of the exhaust gas flowing through the bypass line and bypassing the turbine wheel from the first and second exhaust gas line elements is settable. A third exhaust gas line element opens out into the third flood.

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.

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).

A turbine bypass valve comprising: a casing defining first and second casing ports; and a valve cartridge mounted to the casing; wherein the valve cartridge comprises: first and second valve ports; and a valve member, the valve member being movable between a first position in which there is a flow path between the first and second valve ports, and a second position in which the valve member substantially blocks said flow path between the first and second valve ports; and wherein the valve cartridge is mounted to the casing such that the first valve port is aligned with the first casing port, and the second valve port is aligned with the second casing port.

An exhaust passage structure of an internal combustion includes a first merging passage, a second merging passage, and a third merging passage connecting a third gathering portion in which the exhaust gas flowing through the first merging passage and the exhaust gas flowing through the second merging passage gather and a turbine of a turbocharger. The first merging passage and the second merging passage have respective narrowed portions in which passage cross-sectional areas are minimized. When a total value of passage cross-sectional areas of inlets of exhaust ports in one cylinder is set as a reference passage cross-sectional area A, and the passage cross-sectional areas of the narrowed portions of the first merging passage and the second merging passage are set as narrowed cross-sectional areas B, the exhaust passage structure is configured such that the relationship of 0.5≤(B/A)≤1 is established.

A turbine connector in an engine exhaust manifold includes a turbine foot attached to incoming exhaust conduits. The turbine foot has an outer perimetric edge defining a trapezoidal shape, and inner perimetric edges forming exhaust outlets from the incoming exhaust conduits. The inner perimetric edges have varied perimetric curvatures largest in finite curvature size upon a web extending between the exhaust outlets, and together forming an hourglass web profile in a turbine-mounting plane defined by the turbine foot.

This turbocharger includes: an impeller which includes a hub provided to be rotatable around a center axis and a plurality of turbine blades arranged on the outside of the hub in a radial direction at intervals in a circumferential direction around the center axis; and a turbine housing which is disposed on the outside of the impeller in the radial direction and forms a scroll flow path guiding an exhaust gas toward the impeller on the inside of the radial direction while turning the exhaust gas in the circumferential direction, wherein a flow path width in the circumferential direction of at least one of a plurality of inter-blade flow path portions formed between the plurality of turbine blades is different from a flow path width of the another of the plurality of inter-blade flow path portions.