Embodiments of the present invention may include a turbocharger having a turbine, a turbine housing, a variable valve, a first plate, a second plate and a heat shield member. The turbine housing accommodates the turbine and has a flow path. The variable valve rotates about each pivot member provided thereon, thereby adjusting the flow velocity of fluid guided from the flow path to the turbine. The first plate supports one end of each pivot member, and defines the flow path. The second plate supports the other end of each pivot member or the variable valves, and defines the flow path. The heat shield member covers a wall surface of the turbine housing, and defines the flow path.

A variable-capacity turbocharger includes a nozzle flow passage in which a gas is capable of flowing therethrough from a scroll flow passage toward a turbine impeller, a connecting pin connecting flow passage wall surfaces forming the nozzle flow passage, and nozzle vanes arranged in a rotation direction of the turbine impeller. At least one of the flow passage wall surfaces includes an inner peripheral side wall surface extending radially inward of a first reference line extending in the rotation direction, an outer peripheral side wall surface which is a plane extending radially outward from a second reference line extending in the rotation direction and parallel to a plane orthogonal to rotation axes of the nozzle vanes, and an intermediate wall surface which is a plane extending from the first reference line to the second reference line and parallel to the plane extending orthogonal to the rotation axes of the nozzle vanes.

An asymmetric double-entry turbine is provided with a turbine housing that includes a first volute, a second volute and a turbine receiving bore. The first volute has a first exhaust gas inlet and a first exhaust gas outlet. The second volute has a second exhaust gas inlet and a second exhaust gas outlet. The turbine receiving bore is in fluid communication with the first exhaust gas outlet and the second exhaust gas outlet for conducting a flow of exhaust gas from the first exhaust gas outlet and the second exhaust gas outlet out in an axial direction. The first exhaust gas outlet has an angular opening amount of more than 180 degrees around the turbine receiving bore. The second exhaust gas outlet has an angular opening amount of less than 180 degrees around the turbine receiving bore.

A radial turbine for a charging device with a turbine casing, a turbine wheel, a VTG guide grid, and a plurality of spacing elements. The spacing elements are arranged on the vane bearing ring and define an axial distance of the vane bearing ring from the turbine casing or from a counter-element arranged in the turbine casing. At least one spacing element is arranged adjacent to a guide vane and is configured such that a minimum distance between the at least one spacing element and the associated adjacent guide vane is achieved in a specific operating position of the guide vane in which the minimum distance is formed by a difference between an axial distance and an inflow distance.

A variable geometry assembly for modulating a fluid flow in a turbomachine is disclosed. The assembly comprises: a first ring having a plurality of first wedge-shaped elements and having an axis; a second ring having a plurality of second wedge-shaped elements and having an axis. The second ring is substantially coaxial to the first ring. The second wedge-shaped elements co-act with the first wedge-shaped elements Flow passages are defined between pairs of sequentially arranged first wedge-shaped elements and second wedge-shaped elements. The first ring and the second ring are angularly displaceable one with respect to the other. Moreover, the first ring and the second ring are configured to move axially with respect to one another when the first ring and the second ring are angularly displaced one with respect to the other.

Actuator devices useable to change orientation of one or more vanes, including an actuator rod and an actuator device body configured to allow the actuator rod to move along the axis inside the actuator device body, and having an inlet flange configured to allow a third fluid to enter a space between the actuator device body and the actuator rod, and an outlet flange configured to allow the third fluid to exit the actuator device body. Besides providing a fluid seal between the first fluid and the second fluid, the third fluid may also heat the actuator rod thereby preventing ice formation.

An exhaust gas turbocharger may include a turbine housing and a turbine wheel. The turbine wheel may include a first quantity of a plurality of moving blades. The turbine wheel may be rotatable relative to the turbine housing about a turbine wheel center of rotation and have a turbine wheel radius. A variable turbine geometry may include a blade bearing ring on which a second quantity of a plurality of guide blades are rotatably mounted in each case about a guide blade center of rotation. The plurality of guide blades may be adjustable between a closed position, in which a flow cross section between the guide blades for an exhaust gas to flow through is at a minimum, and an opened position, in which the flow cross section is at a maximum.

Various methods and systems are provided for a fluidic variable turbine. In one example, a system for an engine comprises a turbocharger turbine including a nozzle ring, the nozzle ring including a plurality of stationary vanes, each vane of the plurality of stationary vanes including a plurality of injection ports arranged at an outer surface of the vane, and a gas supply system to supply variable gas flow to and out of the plurality of injection ports.

A method of assembling a turbocharger having a vaned turbine nozzle includes first forming a sub-assembly of a center housing, shaft, bearings, compressor wheel, turbine wheel, and vane assembly. The vane assembly is held captive in attachment to the center housing by an annular heat shield that includes prongs or the like at its inner and outer peripheries for respectively engaging a first catch formed on the center housing and a second catch formed on the nozzle ring of the vane assembly. The heat shield forms a snap fit to the center housing and nozzle ring, thereby connecting the cartridge to the center housing. The whole sub-assembly is then joined to the turbine housing, in the process axially compressing the heat shield and a spring shroud for exerting an axial biasing force on the nozzle ring.

A system for controlling an angular position of a component of an aircraft includes a component having a shaft that includes at least one magnet. The system also includes a housing configured to receive the shaft and including at least one coil configured to generate a magnetic field based on a current through the at least one coil.