Garrett Transportation I Inc.

Honeywell International Inc.

Ashraf Mohamed

Wagner Magalhaes

Stephane Pees

William Joseph Smith

Filip Eckl

Scott MacKenzie

Derek Cooper

Denis Tisserant

Shakeel Nasir

Mark Eldo Groskreutz

Petr Pribyl

Petr Skara

Matthew S Oakes

Pavel Foucek

Kevin Zhang

Chris Meade

Radu C Florea

David Strott

Frederic Nicolle

Radu Florea

William Joseph Smyth

Scott Mackenzie

Turbochargers for use in an engine having an internal combustion engine. The design includes, in examples, a shaft having a rotation axis, a turbine housing, a compressor housing, a center housing extending from the turbine housing to the compressor housing with the shaft therethrough, a turbine wheel disposed in the turbine housing and operatively connected to the shaft, and a compressor wheel disposed in the compressor housing and operatively connected to the shaft. A turbine backplate structure is provided having one or more grooves adjacent a back side of the turbine wheel. The turbine backplate structure may be formed on the central housing, or may be a separate backplate installed in the central housing.

Spiral grooved thrust generator on turbine wheel back plate

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 (Θ) 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.

Turbocharger turbine wheel

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.

Turbocharger turbine assembly

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.

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.

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.

Turbocharger having a meridionally divided turbine housing and a variable turbine nozzle

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.

Turbocharger with ported turbine shroud

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.

Turbine housing for turbocharger with linear A/R distribution and nonlinear area distribution

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.

Turbine wheel with reduced inertia

A vane for a turbine assembly of a turbocharger includes an airfoil that has a pair of flow surfaces disposed between a hub end and a shroud end and a leading edge and a trailing edge where the airfoil further includes a non-zero sweep angle, a non-zero lean angle, a non-zero twist angle or any two or more combinations thereof. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

Vanes for directing exhaust to a turbine wheel

A vane for a turbine assembly of a turbocharger includes a first airfoil that includes a length between a leading edge and a trailing edge, a second airfoil that includes a length between a leading edge and a trailing edge where the length of the first airfoil optionally differs from the length of the second airfoil, and one or more intra-vane throats defined at least in part by the first airfoil and the second airfoil. Various other examples of devices, assemblies, systems, methods, etc., are also disclosed.

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Torrance, CA, United States of America

Ashraf Mohamed