Abstract: An exhaust system is provided for an automotive engine of vehicles with exhaust conduits having a textured surface. The system comprises a plurality of cylinder exhaust ports, and an exhaust manifold including a plurality of exhaust runners fluidly coupled to the plurality of cylinder exhaust ports, where at least one exhaust runner of the plurality of exhaust runners includes a plurality of steps or dimples protruding outward from the exhaust runner. In one example, the system promotes an effective mixing of oxygen and hydrocarbons in the exhaust stream to reduce engine emissions.

Abstract: An exhaust system is provided for an automotive engine of vehicles with exhaust conduits having a textured surface. The system comprises a plurality of cylinder exhaust ports, and an exhaust manifold including a plurality of exhaust runners fluidly coupled to the plurality of cylinder exhaust ports, where at least one exhaust runner of the plurality of exhaust runners includes a plurality of steps or dimples protruding outward from the exhaust runner. In one example, the system promotes an effective mixing of oxygen and hydrocarbons in the exhaust stream to reduce engine emissions.

Abstract: Methods and systems are provided for a turbocharger system to reduce and balance axial thrust load on the turbine shaft and the associated bearing system and sealing. In one example, a partial back plate compressor may be used in combination with an axial turbine to reduce axial thrust load and to improve turbocharger transient response time. In another example, a regenerative turbocharger system with back-to-back turbo pump may be used to reduce and balance axial thrust load.

Abstract: A method for operating an engine that includes a turbocharger with a wastegate is described. In one example, the method includes oscillating a position of the wastegate during cold engine starting as a function of a speed of an engine. The wastegate position may be adjusted to follow a square wave, sinusoidal wave, or triangle wave.

Abstract: A method for operating an engine that includes a turbocharger with a wastegate is described. In one example, the method includes oscillating a position of the wastegate during cold engine starting as a function of a speed of an engine. The wastegate position may be adjusted to follow a square wave, sinusoidal wave, or triangle wave.

Abstract: Compressors and methods for operating compressors are provided. In one example, a compressor is provided that comprises a ported shroud including a first port positioned upstream of a leading side of a rotor and a second port positioned downstream of the leading side of the rotor. The compressor also includes a muffler arranged in the ported shroud and comprising a plurality of projections, each of the plurality of projections radially extend from a base of the muffler and include an aperture extending through the base.

Abstract: Methods and systems are provided for cooling a compressor in an engine. In one example, a compressor with a liquid coolant passage extending through a section of a housing of the compressor adjacent to a bypass passage, is provide. The bypass passage enable airflow to be directed around a portion of a compressor impeller.

Abstract: Methods and systems are provided for a variable inlet device of a compressor. In one example, a compressor may include a casing forming a recirculation passage surrounding an intake passage, an active casing treatment surrounding a wall separating the intake passage and the recirculation passage and adapted to selectively control a flow of gas through a plurality of ports disposed in the wall, and an impeller. Additionally, a variable inlet device may be position in the intake passage, upstream of the impeller, the variable inlet device including a plurality of adjacently arranged blades forming a ring, each of the blades being pivotable, about an axis arranged tangent to the ring, between the open and closed position.

Abstract: Methods and systems are provided for a variable inlet device of a compressor. In one example, a compressor may include an impeller rotatable about a central axis and an inlet conduit including a variable inlet device (VID) positioned upstream of the impeller and adjustable between and open position and a closed position that restricts and generates pre-swirl flow to the impeller. The VID may include a plurality of adjacently arranged blades forming a ring around the central axis with inner surfaces of the blades forming a flow passage through the VID, each of the blades being pivotable, about an axis arranged tangent to the ring, between the open and closed position.

Abstract: Methods and systems are provided for a slidable sleeve valve actuation system for a turbocharger compressor. In one example, an actuator assembly for a slidable sleeve of a turbocharger compressor may comprise: a fork arm coupled to the slidable sleeve; a rotatable lever arm coupled to the fork arm via a rigid connecting shaft; a connector rod coupled between the lever arm and a rotatable element; and an actuator unit coupled to the rotatable element and attached to an attachment case, the attachment case coupled to the turbocharger compressor. The actuator assembly may be actuated to move the slidable sleeve from one position along a casing treatment to another position along the casing treatment, thereby adjusting the alignment of sleeve slots on the slidable sleeve relative to choke or surge slots on the casing treatment.

Abstract: Various systems and methods are described for a variable geometry turbine. In one example, a nozzle vane includes a stationary having a first cambered sliding surface and a sliding vane having a second cambered sliding surface where the second cambered sliding surface includes a flow disrupting feature in contact with the first sliding cambered surface. The sliding vane may be positioned to slide in a direction from substantially tangent along a curved path to an inner circumference of the turbine nozzle and selectively uncover the flow disrupting feature.

Abstract: Methods and systems are provided for adjusting an active casing treatment of a compressor responsive to a predicted engine condition. In one arrangement, a controller may actuate a sleeve of a variable geometry compressor casing to a position selected based on each of a compressor pressure ratio and a mass flow through the compressor, as well as driver behavior and predicted road conditions; and adjust each of an EGR actuator and a boost actuator based on the selected position to maintain the compressor pressure ratio during the actuating.

Abstract: Methods and systems are provided for a turbocharger system to reduce and balance axial thrust load on the turbine shaft and the associated bearing system and sealing. In one example, a partial back plate compressor may be used in combination with an axial turbine to reduce axial thrust load and to improve turbocharger transient response time. In another example, a regenerative turbocharger system with back-to-back turbo pump may be used to reduce and balance axial thrust load.

Abstract: Methods and systems are provided for a turbocharger system to reduce and balance axial thrust load on the turbine shaft and the associated bearing system and sealing. In one example, a partial back plate compressor may be used in combination with an axial turbine to reduce axial thrust load and to improve turbocharger transient response time. In another example, a regenerative turbocharger system with back-to-back turbo pump may be used to reduce and balance axial thrust load.

Abstract: Systems are provided for a nozzle blade for a variable nozzle turbine of a turbocharged engine. In one example, a nozzle blade for a turbine nozzle of a variable geometry turbine may include: a cambered outer surface that curves from an inlet end to an outlet end of the nozzle blade, relative to a chord of the nozzle blade, the chord having a chord length defined from the inlet end to the outlet end, the nozzle blade having an aspect ratio in a range of 1.54 to 2.95, a thickness that is greatest in a range of 47 to 61% of the chord length, and a camber line angle change ratio in a range of 0.94 to 1.16 from the inlet end to the outlet end of the nozzle blade.

Abstract: Methods and system are provided for a turbine nozzle adapted with variable geometry guide vanes. In one example, a turbine nozzle may include sliding and fixed vanes arranged between supporting plates. The sliding vanes are engaged by an actuating plate that adjusts a position of the sliding vanes to regulate gas flow to the turbine.

Abstract: Methods and systems are provided for cooling a compressor in an engine. In one example, a compressor with a liquid coolant passage extending through a section of a housing of the compressor adjacent to a bypass passage, is provide. The bypass passage enable airflow to be directed around a portion of a compressor impeller.

Abstract: Methods and systems are provided for a variable inlet device of a compressor. In one example, a compressor may include an impeller rotatable about a central axis and an inlet conduit including a variable inlet device (VID) positioned upstream of the impeller and adjustable between and open position and a closed position that restricts and generates pre-swirl flow to the impeller. The VID may include a plurality of adjacently arranged blades forming a ring around the central axis with inner surfaces of the blades forming a flow passage through the VID, each of the blades being pivotable, about an axis arranged tangent to the ring, between the open and closed position.

Abstract: Methods and systems are provided for a variable inlet device of a compressor. In one example, a compressor may include a casing forming a recirculation passage surrounding an intake passage, an active casing treatment surrounding a wall separating the intake passage and the recirculation passage and adapted to selectively control a flow of gas through a plurality of ports disposed in the wall, and an impeller. Additionally, a variable inlet device may be position in the intake passage, upstream of the impeller, the variable inlet device including a plurality of adjacently arranged blades forming a ring, each of the blades being pivotable, about an axis arranged tangent to the ring, between the open and closed position.

Abstract: Methods and systems are provided for a variable inlet device of a compressor. In one example, a compressor may include the variable inlet device arranged within an inlet conduit of the compressor. The variable inlet device may be adjustable to control the gas flow through the compressor, the variable inlet including a pair of semi-cylindrical shells that are pivotable, about a set of hinges, between an open and closed position.