Abstract: A distance adjustment apparatus and a control method of the distance adjustment apparatus are provided. The distance adjustment apparatus includes a connection component, and the connection component includes a first component and a second component. The first component is connected to the second component, and a memory alloy component is disposed in a connection region between the first component and the second component. The memory alloy component is controlled by a current to drive the first component and the second component to move closer to and/or away from each other.

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: 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 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 system for increasing temperature in an exhaust aftertreatment system upstream of an exhaust aftertreatment device, such as a selective catalyst reduction (SCR) device, is provided. In one form, the system includes a component within an exhaust stream being exposed to exhaust flow and temperatures of at least 200° C. At least one surface of the component includes an adhered ceramic coating that functions as a catalyst to accelerate heating of the exhaust flow. In another form, a secondary catalyst is adhered to the ceramic coating. The component may be a part or parts of a turbocharger, such as nozzles, vanes, runners, and blades.

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 and methods are provided for a turbocharger compressor, where the system may comprise: an actuatable annular disk comprising choke slots therein; an outer annular disk comprising choke slots therein; and an actuator to rotate the actuatable annular disk relative to the outer annular disk to vary alignment of the choke slots of the actuatable annular disk and the outer annular disk. The actuator may be controlled by an engine controller responsive to operating conditions of the compressor and actuated to align choke slots. Alignment of the choke slots allows air to be drawn into the impeller effectively expanding the compressor flow capacity to prevent compressor choke.

Abstract: A system for increasing temperature in an exhaust aftertreatment system upstream of an exhaust aftertreatment device, such as a selective catalyst reduction (SCR) device, is provided. In one form, the system includes a component within an exhaust stream being exposed to exhaust flow and temperatures of at least 200° C. At least one surface of the component includes an adhered ceramic coating that functions as a catalyst to accelerate heating of the exhaust flow. In another form, a secondary catalyst is adhered to the ceramic coating. The component may be a part or parts of a turbocharger, such as nozzles, vanes, runners, and blades.

Abstract: Systems are provided for a reinforcement element coupled to a sheet metal turbine housing that imparts desirable thermal-protective and structurally strengthening characteristics to the housing layers. In one example, a system may include a turbine comprising a housing surrounding a turbine rotor, the housing having an outer layer surrounding an inner layer at a distance to form an intermediate space between the inner and outer layers. Moreover, disposed in the intermediate space is a reinforcement element coupled to the inner and outer layers, providing strength and consistent rigidity without a significant increase in weight to the housing.

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: 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 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: 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: Systems are provided for a reinforcement element coupled to a sheet metal turbine housing that imparts desirable thermal-protective and structurally strengthening characteristics to the housing layers. In one example, a system may include a turbine comprising a housing surrounding a turbine rotor, the housing having an outer layer surrounding an inner layer at a distance to form an intermediate space between the inner and outer layers. Moreover, disposed in the intermediate space is a reinforcement element coupled to the inner and outer layers, providing strength and consistent rigidity without a significant increase in weight to the housing.

Abstract: Embodiments may provide variable geometry turbine, a nozzle vane for a variable geometry turbine, and a method. The variable geometry turbine that may include a turbine wheel and a plurality of adjustable vanes radially positioned around the turbine wheel. The turbine may also include a flow disrupting feature on one or more outside surfaces of one or more of the plurality of adjustable vanes.

Abstract: A method for operation of an engine including a turbocharger system is provided. The method includes adjusting turbocharger rotational acceleration or deceleration in response to one or more resonant frequencies. Additionally in some examples, the method may further include increasing turbocharger rotation in response to one or more resonant frequencies during a first condition, and increasing turbocharger deceleration in response to one or more resonant frequencies during a second condition, the second condition different from the first condition. In this way, it is possible to enhance the useful life cycle of the turbocharger and associated engine by limiting the operating time in a resonant frequency band.

Abstract: A vehicle system operation method is provided. The method comprises, during a first operating condition, increasing back pressure in a first exhaust conduit positioned upstream of a turbine and downstream of a first emission control device and during a second operating condition, reducing back pressure in the first exhaust conduit and flowing boosted air from downstream of a compressor into a second exhaust conduit positioned upstream of a second emission control device and downstream of the turbine.