Abstract: A turbine assembly includes a turbine casing, a turbine wheel, vanes, and link plates. The turbine casing defines a center chamber and a volute configured to transport exhaust gas to the center chamber. The turbine wheel is disposed within the center chamber and is rotatably coupled to the turbine casing. The driving ring extends around a periphery of the center chamber and is rotatably coupled to the turbine casing. The vanes are disposed within the center chamber and are configured to adjust a flow rate of exhaust gas from the volute to the turbine wheel. The link plates couple the vanes to the driving ring such that the vanes pivot when the driving ring rotates. When the ring is rotated to a given position, the link plates are configured to pivot one of the vanes to one position while pivoting another one of the vanes to another position.

Abstract: An adjustable trim system for a turbocharger compressor including a ported shroud for a vehicle propulsion system includes a compressor inlet adjustor positioned in a compressor air inlet and being continuously adjustable between a fully open configuration, a ported shroud closed configuration, and a partially-open ported shroud recirculation configuration between the fully open configuration and the ported shroud closed configuration, and a compressor inlet adjustor control module that adjusts the configuration of the compressor inlet adjustor to a configuration between the fully open configuration and the ported shroud closed configuration when the turbocharger pressure ratio is higher than a predetermined pressure ratio threshold and the compressor corrected air flow into the compressor housing inlet is less than a maximum compressor corrected air flow of a compressor flow map for the turbocharger compressor.

Abstract: An adjustable trim system for a turbocharger compressor including a ported shroud for a vehicle propulsion system includes a compressor inlet adjustor positioned in a compressor air inlet and being continuously adjustable between a fully open configuration, a ported shroud closed configuration, and a partially-open ported shroud recirculation configuration between the fully open configuration and the ported shroud closed configuration, and a compressor inlet adjustor control module that adjusts the configuration of the compressor inlet adjustor to a configuration between the fully open configuration and the ported shroud closed configuration when the turbocharger pressure ratio is higher than a predetermined pressure ratio threshold and the compressor corrected air flow into the compressor housing inlet is less than a maximum compressor corrected air flow of a compressor flow map for the turbocharger compressor.

Abstract: A turbine assembly includes a turbine casing, a turbine wheel, vanes, and link plates. The turbine casing defines a center chamber and a volute configured to transport exhaust gas to the center chamber. The turbine wheel is disposed within the center chamber and is rotatably coupled to the turbine casing. The driving ring extends around a periphery of the center chamber and is rotatably coupled to the turbine casing. The vanes are disposed within the center chamber and are configured to adjust a flow rate of exhaust gas from the volute to the turbine wheel. The link plates couple the vanes to the driving ring such that the vanes pivot when the driving ring rotates. When the ring is rotated to a given position, the link plates are configured to pivot one of the vanes to one position while pivoting another one of the vanes to another position.

Abstract: A variable inlet guide vane system for a turbocharger includes a casing that forms an intake passage along a longitudinal axis. A plurality of vanes extend along corresponding transverse axes that are perpendicular to the longitudinal axis, and each vane is movably disposed within the intake passage between a high-trim position where the intake passage defines a maximum cross-sectional area for supplying airflow at a high-trim velocity and a low-trim position where the vanes define a minimum cross-sectional area for supplying airflow at a low-trim velocity. The minimum cross-sectional area is smaller than the maximum cross-sectional area such that the low-trim velocity is higher than the high-trim velocity at a common flow rate. Each vane includes an outer section rotatably coupled to the casing and an inner section, which extends from the outer section along the transverse axis and is angularly spaced from the outer section about the transverse axis.