Abstract: Aspects relate to a three-dimensional (3D) printing device including a gantry system configured to move a build platform between the different stages of the printing process. The stages may include, for example, printing, washing, and post curing. The gantry system includes a gantry rail and a gantry carriage. The gantry carriage can be removably attached to a build platform on which a printed object is printed and the gantry rail can then move the build platform between at least the printing and washing stages.

Abstract: A turbocharger turbine wheel can include a hub that includes a rotational axis, a backdisk and a nose, where the rotational axis defines an axial coordinate (z) in a cylindrical coordinate system that includes a radial coordinate (r) and an azimuthal coordinate (?) in a direction of intended rotation about the rotational axis; and blades that extend outwardly from the hub, where each of the blades includes a hub profile, a shroud edge, a leading edge, a trailing edge, a pressure side, and a suction side, where the hub profile includes a global maximum radius and a global minimum radius, and where, between the global maximum radius and the global minimum radius, in an axial direction from the backdisk to the nose, the hub profile includes a local minimum radius at a first axial coordinate position and a local maximum radius at a second axial coordinate position.

Abstract: A turbine housing assembly can include a turbine housing that defines a rotational axis for a turbine wheel; and a cartridge receivable by the turbine housing, where the cartridge includes a nozzle wall component with an upper nozzle surface and a plate component with a lower nozzle surface, where the upper nozzle surface and the lower nozzle surface define a nozzle space, and vanes positioned in the nozzle space, where the vanes are pivotable between a closed vanes position of 0 percent open and a fully open vanes position of 100 percent open, and where, for a vanes position of at least 50 percent open and less than 75 percent open, an axial dimension of the nozzle space increases with respect to decreasing radius as measured from the rotational axis.

Abstract: A turbine housing assembly can include a turbine housing that defines a rotational axis for a turbine wheel; and a cartridge receivable by the turbine housing, where the cartridge includes a nozzle wall component with an upper nozzle surface and a plate component with a lower nozzle surface, where the upper nozzle surface and the lower nozzle surface define a nozzle space, and vanes positioned in the nozzle space, where the vanes are pivotable between a closed vanes position of 0 percent open and a fully open vanes position of 100 percent open, and where, for a vanes position of at least 50 percent open and less than 75 percent open, an axial dimension of the nozzle space increases with respect to decreasing radius as measured from the rotational axis.

Abstract: A turbocharger turbine wheel can include a hub that includes a rotational axis, a backdisk and a nose, where the rotational axis defines an axial coordinate (z) in a cylindrical coordinate system that includes a radial coordinate (r) and an azimuthal coordinate (0) in a direction of intended rotation about the rotational axis; and blades that extend outwardly from the hub, where each of the blades includes a hub profile, a shroud edge, a leading edge, a trailing edge, a pressure side, and a suction side, where the hub profile includes a global maximum radius and a global minimum radius, and where, between the global maximum radius and the global minimum radius, in an axial direction from the backdisk to the nose, the hub profile includes a local minimum radius at a first axial coordinate position and a local maximum radius at a second axial coordinate position.

Abstract: Systems and methods for multi-sensor mapping are provided for a multi-sensor device having a range sensor, a location sensor and an orientation sensor that provide range data, location data and orientation data, respectively. The device may be operated in a stationary mode, a mobile ground mode or an airborne mode. The range data, the location data and the orientation data are combined to generate three-dimensional geo-referenced point cloud data.

Abstract: A turbocharger turbine wheel includes a hub; and blades that extend outwardly from the hub, where each of the blades includes a shroud edge, a leading edge, a trailing edge, a pressure side, and a suction side, where the shroud edge includes a minimum axial coordinate position where the shroud edge meets the leading edge, and a maximum axial coordinate position where the shroud edge meets the trailing edge, and where, between the minimum axial coordinate position and the maximum axial coordinate position, each of the blades includes a first lean angle at a first axial coordinate position defined with respect to a first radial line, a second lean angle at a second axial coordinate position defined with respect to a second radial line, and a lean angle inflection region at an inflection axial coordinate position that is between the first axial coordinate position and the second axial coordinate position.

Abstract: A turbocharger turbine assembly can include a turbine housing that includes a longitudinal axis, an exhaust inlet, a shroud portion, and an exhaust outlet; and a turbine wheel that includes a hub that includes a rotational axis aligned with the longitudinal axis of the turbine housing, a backdisk and a nose, where the rotational axis defines an axial coordinate (z) in a cylindrical coordinate system; and blades that extend outwardly from the hub, where each of the blades includes a shroud edge, a leading edge, a trailing edge, a pressure side, and a suction side, where the shroud edge includes a minimum axial coordinate position where the shroud edge meets the leading edge, and a maximum axial coordinate position where the shroud edge meets the trailing edge, and where, from the minimum axial coordinate position to the maximum axial coordinate position, the shroud edge has a decreasing radial coordinate position.

Abstract: A turbocharger turbine assembly can include a turbine housing that includes a longitudinal axis, an exhaust inlet, a shroud portion, and an exhaust outlet; and a turbine wheel that includes a hub that includes a rotational axis aligned with the longitudinal axis of the turbine housing, a backdisk and a nose, where the rotational axis defines an axial coordinate (z) in a cylindrical coordinate system; and blades that extend outwardly from the hub, where each of the blades includes a shroud edge, a leading edge, a trailing edge, a pressure side, and a suction side, where the shroud edge includes a minimum axial coordinate position where the shroud edge meets the leading edge, and a maximum axial coordinate position where the shroud edge meets the trailing edge, and where, from the minimum axial coordinate position to the maximum axial coordinate position, the shroud edge has a decreasing radial coordinate position.

Abstract: A turbocharger turbine wheel includes a hub; and blades that extend outwardly from the hub, where each of the blades includes a shroud edge, a leading edge, a trailing edge, a pressure side, and a suction side, where the shroud edge includes a minimum axial coordinate position where the shroud edge meets the leading edge, and a maximum axial coordinate position where the shroud edge meets the trailing edge, and where, between the minimum axial coordinate position and the maximum axial coordinate position, each of the blades includes a first lean angle at a first axial coordinate position defined with respect to a first radial line, a second lean angle at a second axial coordinate position defined with respect to a second radial line, and a lean angle inflection region at an inflection axial coordinate position that is between the first axial coordinate position and the second axial coordinate position.

Abstract: A turbocharger has a meridionally divided turbine housing defining a first scroll and a first nozzle, and a second scroll and a second nozzle. The first and second nozzles are divided from each other by a shroud plate mounted within the nozzle, for isolating the exhaust gas streams flowing through the two nozzles from each other. A plurality of circumferentially spaced vanes are rotatably mounted at a radially inner side of the nozzles. Leading-edge portions of the vanes are slotted to receive the shroud plate when the vanes are pivoted open. Trailing-edge portions of the vanes are unslotted. A radially inner periphery of the shroud plate includes cutouts for abutting the trailing-edge portions of the vanes in the closed position, and includes contour portions for influencing a flow separation ratio of the turbine.

Abstract: A turbocharger includes a turbine housing that defines a flow passage for a fluid. The turbine housing includes a turbine shroud member. The turbocharger also includes a turbine wheel supported for rotation within the turbine housing relative to the turbine shroud member. The turbine wheel is configured to rotate as the fluid flows through the flow passage. Moreover, the turbocharger includes a port extending through the turbine shroud member. The port is configured to receive a portion of the fluid flowing through the flow passage.

Abstract: Aspects of the disclosed technology relate to techniques for protocol analysis during a circuit design verification process. A protocol-specific message capture unit captures messages while or after being transmitted over one or more communication channels between a circuit design model and one or more target devices. A protocol-independent interface unit receives signals carrying the messages and information for processing the messages from the protocol-specific message capture unit. After processing the messages, the protocol-independent interface unit sends the messages to an analysis unit for analyzing the messages based on a protocol file. The analysis unit may then output the messages for displaying.

Abstract: A turbine housing includes a volute flow passage with an inlet and an end that are spaced apart along a flow axis in a circumferential direction about an axis of rotation. The volute flow passage defines a plurality of cross sections arranged in series along the flow axis from the inlet to the end. The plurality of cross sections are taken normal to the flow axis. The plurality of cross sections have an area (A) and a centroid, and the centroid is spaced at a radial distance (R) from the axis of rotation. The volute flow passage has a sidewall angle distribution from the inlet to the end that is at least partly nonlinear. The volute flow passage has an A/R-distribution from the inlet to the end that is substantially linear. The volute flow passage has an A-distribution from the inlet to the end that is at least partly nonlinear.

Abstract: A turbine wheel for a turbocharger is provided. The turbine wheel includes a plurality of blades and a mid-plane is defined between a pressure side and a suction side of adjacent blades. Each of the blades has a leading edge, and is coupled to the wheel hub along a respective blade hub camber line. The wall has a first radii at the leading edge that extends for a first circumferential distance adjacent to the suction side. The first circumferential distance is at least 12% of a circumferential distance that extends between adjacent blades. The wheel hub includes a plurality of scallops defined through the wall. Each of the scallops is asymmetrical about the mid-plane. For each of the scallops, the wall has a second minimum radii defined offset from the mid-plane toward the suction side and a third minimum radii defined offset from the mid-plane toward the pressure side.

Abstract: A turbine housing includes a volute flow passage with an inlet and an end that are spaced apart along a flow axis in a circumferential direction about an axis of rotation. The volute flow passage defines a plurality of cross sections arranged in series along the flow axis from the inlet to the end. The plurality of cross sections are taken normal to the flow axis. The plurality of cross sections have an area (A) and a centroid, and the centroid is spaced at a radial distance (R) from the axis of rotation. The volute flow passage has a sidewall angle distribution from the inlet to the end that is at least partly nonlinear. The volute flow passage has an A/R-distribution from the inlet to the end that is substantially linear. The volute flow passage has an A-distribution from the inlet to the end that is at least partly nonlinear.

Abstract: A turbine wheel for a turbocharger is provided. The turbine wheel includes a plurality of blades and a mid-plane is defined between a pressure side and a suction side of adjacent blades. Each of the blades has a leading edge, and is coupled to the wheel hub along a respective blade hub camber line. The wall has a first radii at the leading edge that extends for a first circumferential distance adjacent to the suction side. The first circumferential distance is at least 12% of a circumferential distance that extends between adjacent blades. The wheel hub includes a plurality of scallops defined through the wall. Each of the scallops is asymmetrical about the mid-plane. For each of the scallops, the wall has a second minimum radii defined offset from the mid-plane toward the suction side and a third minimum radii defined offset from the mid-plane toward the pressure side.

Abstract: A turbocharger has a meridionally divided turbine housing defining a first scroll and a first nozzle, and a second scroll and a second nozzle. The first and second nozzles are divided from each other by a shroud plate mounted within the nozzle, for isolating the exhaust gas streams flowing through the two nozzles from each other. A plurality of circumferentially spaced vanes are rotatably mounted at a radially inner side of the nozzles. Leading-edge portions of the vanes are slotted to receive the shroud plate when the vanes are pivoted open. Trailing-edge portions of the vanes are unslotted. A radially inner periphery of the shroud plate includes cutouts for abutting the trailing-edge portions of the vanes in the closed position, and includes contour portions for influencing a flow separation ratio of the turbine.

Abstract: Aspects of the disclosed technology relate to techniques for protocol analysis during a circuit design verification process. A protocol-specific message capture unit captures messages while or after being transmitted over one or more communication channels between a circuit design model and one or more target devices. A protocol-independent interface unit receives signals carrying the messages and information for processing the messages from the protocol-specific message capture unit. After processing the messages, the protocol-independent interface unit sends the messages to an analysis unit for analyzing the messages based on a protocol file. The analysis unit may then output the messages for displaying.

Abstract: A turbocharger includes a turbine housing that defines a flow passage for a fluid. The turbine housing includes a turbine shroud member. The turbocharger also includes a turbine wheel supported for rotation within the turbine housing relative to the turbine shroud member. The turbine wheel is configured to rotate as the fluid flows through the flow passage. Moreover, the turbocharger includes a port extending through the turbine shroud member. The port is configured to receive a portion of the fluid flowing through the flow passage.