A hydrogen fueled powerplant including an internal combustion engine that drives a motor-generator, and has a two-stage turbocharger, for an aircraft. A control system controls the operation of the motor-generator to maintain the engine at a speed selected based on controlling the engine equivalence ratio. The control system controls an afterburner, an intercooler and an aftercooler to maximize powerplant efficiency. The afterburner also adds power to the turbochargers during high-altitude restarts. The turbochargers also include motor-generators that extract excess power from the exhaust.

A number of variations may include a product comprising a bearing housing comprising a body having an internal cavity defined by an inner surface of the body, wherein a first end of the body includes an end face and a second end of the body opposite of the end face is open, wherein the end face further comprises a through hole defined by an inner surface of the end face; and an end plate constructed and arranged to attach to the second end of the body of the bearing housing, wherein the end plate further comprise a first face and a second face, and an opening defined by an inner surface of the end plate.

A number of variations may include a product comprising a bearing housing comprising a body having an internal cavity defined by an inner surface of the body, wherein a first end of the body includes an end face and a second end of the body opposite of the end face is open, wherein the end face further comprises a through hole defined by an inner surface of the end face; and an end plate constructed and arranged to attach to the second end of the body of the bearing housing, wherein the end plate further comprise a first face and a second face, and an opening defined by an inner surface of the end plate.

A rotary unit is rotatably accommodated within a supercharger casing of a supercharger for pressurizing an intake air of an engine. The rotary unit includes a supercharger rotary shaft, an impeller fixed to a tip end portion of the supercharger rotary shaft, a rotating component rotatable together with the supercharger rotary shaft independently of the impeller, and a nut member for pressing the impeller and the rotating component in a direction axially of the supercharger rotary shaft to thereby fix them to the supercharger rotary shaft. The nut member is formed with an adjustment portion for the rotational balance adjustment.

A rotary unit is rotatably accommodated within a supercharger casing of a supercharger for pressurizing an intake air of an engine. The rotary unit includes a supercharger rotary shaft, an impeller fixed to a tip end portion of the supercharger rotary shaft, a rotating component rotatable together with the supercharger rotary shaft independently of the impeller, and a nut member for pressing the impeller and the rotating component in a direction axially of the supercharger rotary shaft to thereby fix them to the supercharger rotary shaft. The nut member is formed with an adjustment portion for the rotational balance adjustment.

A turbocharger includes a variable-nozzle turbine having a variable vane assembly formed as a cartridge. A pipe-shaped insert of the cartridge fits into an axial bore in the turbine housing. The variable vane assembly includes a nozzle ring to which the variable vanes are mounted. A composite heat shroud is disposed between and axially compressed between the turbocharger's center housing and the nozzle ring. The heat shroud is constructed such that heating of the shroud causes the shroud to deform so as to increase the axial preload exerted by the shroud. In one embodiment the heat shroud is a two-layer structure in which the two layers are formed of different materials having different coefficients of thermal expansion.

A turbocharger includes a variable-nozzle turbine having a variable vane assembly formed as a cartridge. A pipe-shaped insert of the cartridge fits into an axial bore in the turbine housing. The variable vane assembly includes a nozzle ring to which the variable vanes are mounted. A composite heat shroud is disposed between and axially compressed between the turbocharger's center housing and the nozzle ring. The heat shroud is constructed such that heating of the shroud causes the shroud to deform so as to increase the axial preload exerted by the shroud. In one embodiment the heat shroud is a two-layer structure in which the two layers are formed of different materials having different coefficients of thermal expansion.

A turbocharger includes a variable turbine nozzle defined between a nozzle ring and a pipe flange, and having a plurality of circumferentially spaced vanes rotatably mounted on the nozzle ring such that the vanes are pivotable. Each vane includes an airfoil section and a disk section rigidly affixed to an end of the airfoil section, the disk section being disposed against a face of the pipe flange, each disk section having a plurality of perforations extending axially therethrough. The pipe flange has a corresponding number of holes for each disk section of the vanes, the holes being positioned such that as each vane is rotated the perforations in the disk sections and the holes in the pipe flange of the insert become aligned in some positions of the vanes, allowing exhaust gas to pass between the nozzle and a space on an opposite side of the pipe flange from the nozzle.

A turbocharger includes a variable turbine nozzle defined between a nozzle ring and a pipe flange, and having a plurality of circumferentially spaced vanes rotatably mounted on the nozzle ring such that the vanes are pivotable. Each vane includes an airfoil section and a disk section rigidly affixed to an end of the airfoil section, the disk section being disposed against a face of the pipe flange, each disk section having a plurality of perforations extending axially therethrough. The pipe flange has a corresponding number of holes for each disk section of the vanes, the holes being positioned such that as each vane is rotated the perforations in the disk sections and the holes in the pipe flange of the insert become aligned in some positions of the vanes, allowing exhaust gas to pass between the nozzle and a space on an opposite side of the pipe flange from the nozzle.

A thrust bearing, particularly for a turbocharger, having unique configurations on the thrust pad faces, including free-form curvatures or non-linear configurations defined by a geometric equation. The thrust pad faces can be configured by a programmed linear actuator system and cutting tool.