Abstract: An exemplary center housing rotating assembly includes a turbine wheel, a compressor wheel, a center housing with a through bore extending from a compressor end to a turbine end, a lubricant inlet and a lubricant outlet, a pair of bearings disposed at least partially in the through bore of the center housing, a bearing spacer and a shaft rotatably supported by the bearings and having a rotational axis coincident with a rotational axis of the turbine wheel and a rotational axis of the compressor wheel where the center housing includes bearing lubricant paths to direct lubricant from the lubricant inlet to the pair of bearings and a shaft lubricant path to direct lubricant from the lubricant inlet to the shaft in a manner dependent on rotational position of the bearing spacer in the through bore of the center housing. Various other exemplary devices, systems, methods, etc., are also disclosed.

Abstract: An exemplary flow path for an electrically assisted turbocharger (220) includes a first opening to an air intake path (114) of an engine (110), the first opening positioned downstream from a compressor (224) of the turbocharger (220); a second opening to an exhaust path (116) of an engine (110), the second opening positioned upstream from the turbine (226) of the turbocharger (220); and a valve (229) controllable by a controller (240, 150, 160) wherein the controller (240, 150, 160) includes control logic for controlling the valve (229) and for controlling an electric motor (228) of the electrically assisted turbocharger (220). Various other exemplary devices, methods, systems, etc., are also disclosed.

Abstract: An exemplary spring for positioning a turbocharger bearing in a housing includes a free standing inner diameter, a free standing outer diameter and a substantially sinusoidal shape to provide an inward radial bias and to provide an outward radial bias wherein the spring balances the inward radial bias with the outward radial bias to thereby position a turbocharger bearing in a housing. Various exemplary springs, bearings, housings, assemblies, etc., are also disclosed.

Abstract: An exemplary bearing and locating pin system for a turbocharger includes a locating pin including a shaft, a head and an aperture and a bearing having a central axis and including an internal bore to receive a shaft extending between a compressor wheel and a turbine wheel, the internal bore including a plurality of axial grooves, the bearing including a locating pin aperture substantially equidistant from axial ends of the bearing for engaging the locating pin to prevent rotation of the bearing within a bearing case bore, the bearing further including a plurality of lubricant inlets, each inlet extending between an outer surface of the bearing and one of the axial grooves at an angle non-orthogonal to the central axis. Other exemplary technologies are also disclosed.

Abstract: An exemplary mixer includes a cylindrical wall having a center axis, a substantially tubular wall defining a volute oriented about the center axis, an inlet to the volute, an exit to the volute provided by one or more openings in the cylindrical wall wherein the volute imparts a tangential velocity component to gas exiting the volute and a mount to mount the mixer to an inlet to a compressor wherein the tangential velocity component imparted by the orientation of the volute is in the intended direction of rotation of a compressor wheel of the compressor. Such a mixer can improve compressor stability, especially where the gas is exhaust gas for exhaust gas recirculation. Other methods, device, systems are also disclosed.

Abstract: An exemplary bearing assembly for a turbocharger includes a center housing with a bearing bore having a bearing bore turbine end radius and an inlet for lubricant and a unitary bearing disposed in the bearing bore and forming an outer lubricant film between the bearing and the bearing bore wherein the bearing includes a central axis, an internal bore to receive a shaft extending between a compressor end and a turbine end of the bearing and forming an inner lubricant film between the internal bore and the shaft, a locating mechanism between axial ends of the bearing to prevent rotation and translation of the bearing within the bearing bore and a turbine end protrusion wherein the protrusion comprises a radius that exceeds the bearing bore turbine end radius to thereby deflect lubricant from the outer lubricant film layer radially outward. Other exemplary technologies are also disclosed.

Abstract: An exemplary vane fronting surface for a variable geometry turbine includes a white layer that comprises nitrides. Such a layer may be formed using gas nitriding. As described, trials demonstrate that such nitriding reduces friction between a vane fronting surface and vanes of a variable geometry turbine. Consequently, nitriding can enhance longevity and controllability of a variable geometry turbine.

Abstract: The present invention provides an assembly comprising a compressor housing and EGR mixer, the assembly further comprising a ported shroud in the compressor housing and a noise suppressor in the EGR mixer.

Abstract: An exemplary controller for a variable geometry compressor includes one or more inputs for receiving engine operating information and for receiving a signal representative of geometry of a variable geometry compressor and control logic to call for actuation of an actuator based at least in part on the engine operating information received by the one or more inputs and to call for actuation of the actuator based at least in part on the signal received by the one or more inputs whereby actuation of actuator causes a change in geometry of a variable geometry compressor. Various other exemplary technologies are also disclosed.

Abstract: A turbomachinery apparatus. A turbine is provided with a retainer having a bore step element for turbine wheel retention, and with an aperture manifesting a tailored diameter less than the trim diameter of the turbine, thereby to permit customization of the turbine efficiency characteristic. Various configurations of turbine retainers, with tailored diameter apertures, are disclosed.

Abstract: A charge air condensation separation system for a turbocharged engine, especially suited for engines employing EGR, includes a turbocharger having a compressor providing charge air with a charge air cooler connected to the compressor to cool the charge air. A charge air delivery duct is connected to an outlet of the charge air cooler and a torroidal trap having an annular inlet is disposed in the charge air delivery duct with a sump for collecting condensation integral to the torroidal trap. A drain line for removing condensation from the sump for expulsion to the atmosphere is connected to the trap and a pump or other device for overcoming pressure differential in the drain line is employed in certain embodiments. For EGR systems employing a mixer, the condensation separator can be incorporated adjacent to or integral with the mixer to minimize additional volume requirements in the engine compartment.

Abstract: A turbocharger turbine housing of this invention comprises a generally circular-shaped body having an exhaust gas inlet flange at a radial housing end and an exhaust gas outlet at an axial end. The inlet flange is configured having openings to two volutes that are separated by a wall divider, thereby forming an X-shaped pattern. The inlet flange is additionally configured having rounded and uniform thickness walls. The volutes are configured having a nonuniform shape and size, and the wall divider is configured having a diminishing area between the volutes, moving through the housing away from the inlet flange. The volutes are configured having a nonuniform shape and size with respect to one another as well moving through the turbine housing. Configured in this manner, turbocharger turbine housings of this invention serve to minimize thermal stress effects caused from transient thermal loading, thereby minimizing and/or eliminating thermal stress relating damage such as cracking.

Abstract: Butterfly valves of this invention generally comprise a flapper element that is rotatably disposed within an annular bore of a valve housing. The valve may be configured to provide an improved degree of gas flow control sensitivity from a closed to a partially opened position through the use of projections that extend radially inwardly from the housing bore, are positioned at diametrically opposed positions within the bore, and that are specifically configured to provide a gradual increase in gas flow across the valve as the flapper is moved from a closed position to a partially opened position. The butterfly valve may be configured having further projections that extend radially inwardly a distance therein, that are positioned at diametrically opposed positions in the bore, and that include faces that are sized and shaped to cooperate with respective opposed surfaces of the flapper to seal off gas flow within the bore when the flapper is placed into a closed position.

Abstract: Exemplary methods, devices and/or system for enhancing engine performance through use of one or more compressors and/or one or more turbines. An exemplary system includes an electric compressor to boost intake charge pressure supplied to an internal combustion engine; an electric turbine to generate electrical power from exhaust received from the internal combustion engine; and an electric power control to provide electrical power from a power storage to the electric compressor upon a request for boost and to provide electrical power generated by the electric turbine to the electric compressor after a request for boost and upon a depletion of the power storage to a predetermined power storage level. Various other exemplary methods, devices and/or systems are also disclosed.