Abstract: Damping members for turbocharger assemblies, methods for providing turbocharger assemblies, and turbocharger assemblies are described herein. The damping members include bodies having shapes to fit between a recess extending into a rotor disk of a turbocharger and laterally protruding shoulders of platforms in neighboring blades of the turbocharger. The bodies dampen vibrations of the blades during rotation of the blades. The damping members may include a variety of shapes, such as a sheet, a wedge, a tapered pin, a cylindrical pin, a bent sheet, or another shape.

Abstract: Various methods and systems are provided for controlling a tip clearance between a shroud and blade of a turbocharger turbine. In one embodiment, a method for an engine including a turbocharger comprises, selectively adjusting a flow of coolant from one or more engine coolant sources through a shroud of a turbine based on a tip clearance between the shroud and a blade of the turbine.

Abstract: The method includes moving at least one of a first support and a second support to vary a position of the plurality of main blades and tandem blades relative to each other to control one or more flow control characteristics across the turbine. The turbine includes a nozzle having the plurality of main blades and tandem blades. The plurality of main blades are coupled to the first support and the plurality of tandem blades are coupled to the second support disposed spaced apart from the first support.

Abstract: Various methods and systems are provided for engine operation with a degraded turbocharger. In one embodiment, a method for an engine comprises reducing mass flow through a first turbocharger while continuing engine operation and adjusting operation of a second turbocharger in response to detected degradation of the first turbocharger.

Abstract: Various systems and apparatuses are provided for a fluid transfer system for an engine. In one example, a system includes a first turbine having an exit for discharging a main fluid flow and a second turbine having an inlet for receiving at least a portion of the main fluid flow. A main conduit fluidically couples the exit of the first turbine to the inlet of the second turbine. A transition conduit is coupled with the main conduit and includes a volute passageway curving around the main conduit. The volute passageway includes a slot that follows a route around the curving volute passageway and opens into an interior of the main conduit. The slot is defined at least in part by a lip and establishes a path for either a secondary fluid flow to enter the main conduit or a portion of a main fluid flow to exit the main conduit.

Abstract: Various methods and systems are provided for lowering exhaust gas temperature. In one embodiment, a method comprises increasing an air-to-fuel ratio of an engine in response to an exhaust gas temperature exceeding a threshold temperature value to lower the exhaust gas temperature to a temperature below the threshold temperature value.

Abstract: Various methods and systems are provided for a turbocharger comprising a turbine disc rotatable about a rotational axis of the turbocharger, a compressor wheel mechanically coupled to the turbine disc via a shaft, a compressor casing including an air inlet and a blower casing formed as one piece, the air inlet configured to admit air to the compressor wheel, and a turbine casing housing the turbine disc, the turbine casing including a shroud surrounding the turbine disc.

Abstract: Various methods and systems are provided for a system for a rotary machine, such as a compressor or turbocharger. In one example, the rotary machine includes a volute assembly and a bearing housing. The volute assembly has a first connector that is configured to interlock with a second connector of the bearing housing. The first and second connectors are configured to engage to a greater extent through relative rotation between the volute assembly and the bearing housing.

Abstract: A turbocharger includes a compressor, a turbine, a shaft coupling the compressor to the turbine, and a turbo casing configured to improve pressure recovery and reduce energy loss from exhaust flow. In one embodiment, the turbo casing may include a geometry configured to improve exhaust flow towards an exhaust outlet. The turbo casing may include a torus shaped chamber having a cross-sectional area that progressively increases in an annular direction of the flow towards the exhaust outlet.

Abstract: An exemplary turbocharger system for an internal combustion engine is provided. The turbocharger system includes a first turbine and a second turbine. The first turbine is in fluid communication with the internal combustion engine. The first turbine receives a first portion exhaust gas discharged from the internal combustion engine and provides a first turbine exhaust gas. The second turbine is in fluid communication with the first turbine via an inter-stage channel. The inter-stage channel transports the first turbine exhaust gas from the first turbine to the second turbine. The inter-stage channel is in thermal connection with an exhaust gas recirculation channel defined between an inlet and an outlet of the internal combustion engine. The first turbine exhaust gas flowing through the inter-stage channel is capable of being heated by a second portion exhaust gas discharged from the internal combustion engine and flowing through the exhaust gas recirculation channel.

Abstract: The method includes moving at least one of a first support and a second support to vary a position of the plurality of main blades and tandem blades relative to each other to control one or more flow control characteristics across the turbine. The turbine includes a nozzle having the plurality of main blades and tandem blades. The plurality of main blades are coupled to the first support and the plurality of tandem blades are coupled to the second support disposed spaced apart from the first support.

Abstract: Various systems and apparatuses are provided for a fluid transfer system for an engine. In one example, a system includes a first turbine having an exit for discharging a main fluid flow and a second turbine having an inlet for receiving at least a portion of the main fluid flow. A main conduit fluidically couples the exit of the first turbine to the inlet of the second turbine. A transition conduit is coupled with the main conduit and includes a volute passageway curving around the main conduit. The volute passageway includes a slot that follows a route around the curving volute passageway and opens into an interior of the main conduit. The slot is defined at least in part by a lip and establishes a path for either a secondary fluid flow to enter the main conduit or a portion of a main fluid flow to exit the main conduit.

Abstract: Various methods and systems are provided for lowering exhaust gas temperature. In one embodiment, a method comprises increasing an air-to-fuel ratio of an engine in response to an exhaust gas temperature exceeding a threshold temperature value to lower the exhaust gas temperature to a temperature below the threshold temperature value.

Abstract: Various methods and systems are provided for engine operation with a degraded turbocharger. In one embodiment, a method for an engine comprises reducing mass flow through a first turbocharger while continuing engine operation and adjusting operation of a second turbocharger in response to detected degradation of the first turbocharger.

Abstract: Various methods and systems are provided for controlling air flow in a two-stage turbocharger. In one example, an engine method comprises adjusting one or more exhaust gas recirculation valves to maintain a first turbocharger within a first air flow range, and adjusting a turbocharger bypass valve to maintain a second turbocharger within a second air flow range.

Abstract: An exemplary compressor is provided. The compressor includes a plurality of blades, a hub defining a front surface and a back surface, and a first flow restriction structure provided at the back surface of the hub. The plurality of blades are arranged in a predefined manner on the front surface for receiving input air flow at a first pressure and compressing the input air flow to provide an output air flow at a second pressure higher than the first pressure. The first flow restriction member is configured for preventing at least a portion of the output air flow at the second pressure from entering into the back surface of the hub to reduce an air pressure at the back surface of the hub.

Abstract: An exemplary turbocharger system for an internal combustion engine is provided. The turbocharger system includes a first turbine and a second turbine. The first turbine is in fluid communication with the internal combustion engine. The first turbine receives a first portion exhaust gas discharged from the internal combustion engine and provides a first turbine exhaust gas. The second turbine is in fluid communication with the first turbine via an inter-stage channel. The inter-stage channel transports the first turbine exhaust gas from the first turbine to the second turbine. The inter-stage channel is in thermal connection with an exhaust gas recirculation channel defined between an inlet and an outlet of the internal combustion engine. The first turbine exhaust gas flowing through the inter-stage channel is capable of being heated by a second portion exhaust gas discharged from the internal combustion engine and flowing through the exhaust gas recirculation channel.

Abstract: A turbocharger system, in certain embodiments, includes a compressor, a turbine, a shaft of common diameter coupling the compressor to the turbine, and a first fluid film bearing disposed about the shaft at a compressor end portion of the shaft. The system also includes a second fluid film fixed pad bearing disposed about the shaft at a turbine end portion of the shaft, wherein the first and second fluid film fixed pad bearings have different clearance ratios, effective lengths, or both, relative to one another. The system, in some embodiments, includes a compressor fluid film fixed pad bearing and a turbine fluid film fixed pad bearing, wherein the compressor and turbine fluid film fixed pad bearings have different clearance ratios and effective lengths, relative to one another.