The present invention is related to a multiple-inlet turbine casing (16) for a turbine rotor (60) which comprises a first fluid supply channel (70) configured to direct a first working fluid onto the turbine rotor (60) and a second fluid supply channel (74) configured to direct a second working fluid to impart torque on the turbine rotor (60) in the same direction as the direction in which torque is imparted on the turbine rotor (60) by the first working fluid. The first working fluid is an exhaust gas from an internal combustion engine and the second fluid may be steam and the turbine may be an inverted-Brayton-cycle turbine for recovery of waste energy from the exhaust gas of said internal combustion engine. Thus, the number of turbine rotors is reduced in comparison to a system comprising a single turbine for each distinct working fluid.

A turbine includes: a turbine blade wheel housed in a housing unit; two turbine scroll flow paths wound radially outward with respect to the turbine blade wheel and connected at positions different from each other in a circumferential direction in an outer circumferential portion of the housing unit; and two scroll outlets each communicating one of the two turbine scroll flow paths with the housing unit, the two scroll outlets formed along the circumferential direction, at least one of the two scroll outlets having a height distribution in which a height in an axial direction is lower than a surrounding height at at least one of an upstream end or a downstream end.

A cylinder head assembly for an internal combustion engine includes a cast cylinder head and a turbocharger housing integrally cast with the cylinder head and having an integrally cast wastegate housing. The turbocharger housing is configured to receive a turbocharger cartridge rotatably supporting a shaft coupled between a compressor wheel and a turbine wheel. The integrally cast wastegate housing defines a wastegate chamber configured to receive a wastegate valve, a flow of exhaust gas from the turbine wheel, and a flow of wastegate exhaust gas.

A turbine housing has a scroll passage. The scroll passage includes: an outer peripheral surface extending along an axial direction of the turbine housing; an inner peripheral surface disposed inward of the outer peripheral surface in a radial direction of the turbine housing; a one-side surface, which is a side surface on one side in the axial direction of the turbine housing, extending along the radial direction of the turbine housing; an other-side surface, which is a side surface on another side in the axial direction of the turbine housing, disposed closer to an outlet of the turbine housing than the one-side surface and extending along the radial direction of the turbine housing; a one-side outer peripheral R portion connecting an outer peripheral end of the one-side surface and a one-side end of the outer peripheral surface; an other-side outer peripheral R portion connecting an outer peripheral end of the other-side surface and an other-side end of the outer peripheral surface; and an other-side inner peripheral R portion connecting an inner peripheral end of the other-side surface and an other-side end of the inner peripheral surface. In a cross-sectional view of the scroll passage, when a ratio of a width dimension of the scroll passage along the axial direction to an R dimension of each of the one-side outer peripheral R portion, the other-side outer peripheral R portion, and the other-side inner peripheral R portion is defined as a one-side outer peripheral R ratio, an other-side outer peripheral R ratio, and an other-side inner peripheral R ratio, respectively, the scroll passage has an R ratio increasing region where at least one of the one-side outer peripheral R ratio, the other-side outer peripheral R ratio, and the other-side inner peripheral R ratio increases from upstream to downstream in the scroll passage.

An aircraft turbomachine having a centrifugal compressor, an annular combustion chamber, an annular casing extending around the chamber and delimiting an annular space (E) in which the chamber is situated, and a heat exchanger. The heat exchanger can include a first circuit supplied with exhaust gas from the turbomachine, and a second circuit connected by first and second volutes respectively to an outlet of the compressor and to the annular space. The first and second volutes can be positioned at an axial distance from one another, and the second volute is can be connected to the annular space by a straightener which is situated at least in part outside the casing and which is integrated into an annular connecting pipe which connects the second volute to this casing.

Aircraft turbomachine including a centrifugal compressor, a combustion chamber, the combustion chamber being supplied by the compressor via a diffuser and via a straightener, and a heat exchanger, the exchanger including a first circuit, supplied with exhaust gas from the turbomachine, and a second circuit, which are connected by volutes on the one hand to an outlet of the diffuser and on the other hand to an inlet of the straightener, the volutes having reversed winding directions such that their connection ports to the exchanger are independent of one another and are substantially diametrically opposed, and such that the minimum cross section of each duct is situated at a larger cross section of the other duct.

A turbocharger includes a turbine housing. The turbine housing includes a turbine inlet wall defining an inlet passage, an exducer shroud wall defining an exducer interior, a turbine outlet wall defining an outlet passage, a wastegate port wall defining a wastegate channel, and a bushing wall coupled to the wastegate port wall and defining a bushing boss extending along a bushing axis, and a valve seat disposed about the wastegate channel. The turbocharger also includes a wastegate assembly. The wastegate assembly includes a valve element engageable with the valve seat. The wastegate port wall is disposed outside of the exducer interior such that the wastegate port wall and the bushing wall are configured to be thermally decoupled from the turbine inlet wall and such that relative displacement between the valve seat and the bushing axis is reduced during operation of the turbocharger.

A turbine comprises a turbine wheel for rotation within a turbine housing, the turbine housing including at least one volute arranged to deliver a fluid to the turbine wheel via the turbine nozzle. A method for determining a width of a turbine nozzle for the turbine, comprises selecting from a relationship between a turbine stage efficiency and an effective nozzle area, at least one target effective nozzle area. As used here, the effective nozzle area is dependent on both the width of the turbine nozzle and a whirl angle induced by the at least one volute. The method further comprises determining, in dependence on the whirl angle, the width of the turbine nozzle as a width that will achieve the at least one target effective nozzle area.

A turbocharger arrangement includes a turbine housing with multiple individual cylinder exhaust delivery scrolls, each having an individual inlet to the turbine, formed therein. The turbine housing has one individual cylinder exhaust delivery scroll for each cylinder of an engine to which the turbocharger arrangement is attached. Individual runner exhaust manifolds each connect one exhaust port of one cylinder of the engine to one of the individual cylinder exhaust delivery scrolls. The individual runner exhaust manifolds may be pipes of approximately equal length and/or equal gas flow characteristics. Separating the exhaust pulses from each cylinder with individually runner exhaust manifolds and turbine scrolls allows for enthalpy in the exhaust flow to be harnessed to a greater extent, and allows the system to be tuned for optimum energy recovery from engine cylinder blowdown.

Disclosed is an austenitic stainless steel alloy that includes or consists of, by weight, about 20.0% to about 21.5% chromium, about 8.5% to about 10.0% nickel, about 4.0% to about 5.0% manganese, about 0.5% to about 2.0% silicon, about 0.4% to about 0.5% carbon, about 0.2% to about 0.3% nitrogen, and a balance of iron with inevitable/unavoidable impurities. The elements niobium, tungsten, and molybdenum are excluded beyond impurity levels. Turbocharger turbine housings made of the stainless steel alloy, and methods of making the same, are also disclosed. The stainless steel alloy is suitable for use in turbocharger turbine applications for temperatures up to about 1020° C.