Abstract: A turbocharger for a powered machine including a turbine is disclosed. The turbocharger may include a turbine wheel including a disk section, the disk section including a disk body, the disk body including a length extending between a longitudinal axis and a blade platform. The disk section may further include a shoulder section positioned radially outward the longitudinal axis, a neck section positioned radially outward the shoulder section and a throat section positioned radially outward the neck section, an upstream axial plane coextensive with an upstream side of the blade platform, a downstream axial plane coextensive with a downstream side of the blade platform. Further, the turbine burst shield section may have a geometry that peaks in depth in the burst plane which prevents ejection of secondary mass in the event of a turbine burst.

Abstract: This document discloses an exhaust gas turbocharger, which includes a turbine disk connected to a turbine disk hub. The turbine disk hub extends distally away from the turbine disk and towards a shaft that connects the turbine disk to a compressor. The shaft includes a proximal end that includes a shaft hub that extends proximally away from the shaft and towards the turbine disk hub. The turbine disk hub is coaxially connected to the shaft hub at a joint. The turbine disk hub and the shaft hub form a cavity between the turbine disk and the proximal end of the shaft. The turbocharger also includes a sleeve having an inner surface that surrounds and engages at least part of the turbine disk hub, at least part of the shaft hub and that further surrounds the joint and partially surrounds the cavity. The sleeve provides structural reinforcement for the joint and additional cooling functions beyond the cooling function provided by the cavity.

Abstract: This document discloses an exhaust gas turbocharger, which includes a turbine disk connected to a turbine disk hub. The turbine disk hub extends distally away from the turbine disk and towards a shaft that connects the turbine disk to a compressor. The shaft includes a proximal end that includes a shaft hub that extends proximally away from the shaft and towards the turbine disk hub. The turbine disk. hub is coaxially connected to the shaft hub at a joint. The turbine disk hub and the shaft hub form a cavity between the turbine disk and the proximal end of the shaft. The turbocharger also includes a sleeve having an inner surface that surrounds and engages at least part of the turbine disk hub, at least part of the shaft hub and that further surrounds the joint and partially surrounds the cavity. The sleeve provides structural reinforcement for the joint and additional cooling functions beyond the cooling function provided by the cavity.

Abstract: A turbocharger for a powered machine including a turbine is disclosed. The turbocharger may include a turbine wheel including a disk section, the disk section including a disk body, the disk body including a length extending between a longitudinal axis and a blade platform. The disk section may further include a shoulder section positioned radially outward the longitudinal axis, a neck section positioned radially outward the shoulder section and a throat section positioned radially outward the neck section, an upstream axial plane coextensive with an upstream side of the blade platform, a downstream axial plane coextensive with a downstream side of the blade platform. Further, the turbine burst shield section may have a geometry that peaks in depth in the burst plane which prevents ejection of secondary mass in the event of a turbine burst.

Abstract: An exhaust gas recirculation system may include a header located at an end of a cooler, and a mixer for mixing exhaust gases and intake air within the header. The mixer may include a passage for receiving exhaust gases and an inlet for receiving intake air. The exhaust gases and intake air may collide at a substantially perpendicular angle within the mixer, and the mixer may further include an outlet for emitting mixed exhaust gases and intake air.

Abstract: A centrifugal compressor includes an annular inlet air recirculation channel having a smoothly variable cross section extending from a first slot at a forward end of the channel adjacent an inlet member to a second slot at a rearward end of the channel beyond an inlet end of a vaned compressor impeller. The channel is formed between an aerodynamic channel ring supported in a smooth annular recess formed in a compressor housing and the separate inlet member. The ring may be mounted by radial struts connected with the housing and located in an area of low momentum air flow. The channel ring and the channel recess may be machined or otherwise formed with smoothly variable surfaces prior to assembly of the ring into the housing. The channel may have a smoothly diminishing annular cross section for aerodynamically efficient air flow.