Various systems are provided for an axially split turbocharger case housing each of a turbine of a turbocharger, a compressor of the turbocharger, and a bearing of the turbocharger. In one example, an apparatus for an engine includes a first monolithic component and a second monolithic component that, when coupled together, form a turbocharger case configured to house each of a turbine, a compressor, and a bearing, the first and second monolithic components, when coupled together, also forming a compressor shroud and a turbine shroud. In further examples of the system, portions of the turbocharger case are formed of a lattice structure.

A bearing housing for a two-wheel air cycle machine includes a first housing portion, a second housing portion, a third housing portion, and a journal bearing bore. The first housing portion is centered around an axis and has a first side and a second side. The second side is positioned axially away from the first side. The second housing portion is centered around the axis and has a first side and a second side. The second side is positioned axially away from the first side. The first side of the second housing portion connects to the second side of the first housing portion. The third housing portion is centered around the axis and has a first side and a second side. The second side is positioned axially away from the first side. The first side of the third housing portion connects to the second side of the second housing portion. The journal bearing bore is centered axially with in the bearing housing and has a diameter of D.sub.1.

A bearing structure includes a rotating shaft, a thrust collar, and a first thrust bearing. The rotating shaft has a central axis. The thrust collar is mounted on the rotating shaft. The first thrust bearing includes a first dynamic pressure generating mechanism. The first dynamic pressure generating mechanism faces the thrust collar. The relation Rt>Rf1 is satisfied, where Rt represents a length from the central axis to the outer circumferential edge of the thrust collar, and Rf1 represents a length from the central axis to the outer circumferential edge of the first dynamic pressure generating mechanism.

A compact heat and electricity co-generation device comprised by: a) a heat generating system connected to a steam generator, a condenser and an internal working fluid, wherein said steam is obtained by external combustion of a suitable fuel in a boiler and/or by conduction of external hot gases to a boiler; y b) an electricity generator system comprised by: i) one or more radial and/or axial turbines; ii) an electric axial flow generator; and iii) an electronic control inverter. The fuel can be a solid, liquid or gaseous fuel. Both the turbine and the electric generator have passive magnetic bearings and electrodynamic bearings. The equipment does not use mechanical seals as all moving parts are housed within working fluid the pressure containment of the working fluid.

A thrust supporting apparatus includes: a thrust runner configured to rotate integrally with a shaft; and a foil thrust bearing supporting an axial load of the shaft, the axial load being transmitted from the thrust runner. The foil thrust bearing includes a top foil facing a first surface of the thrust runner, and the thrust runner comprises first one or more grooves formed on the first surface.

The present disclosure relates to a bearing supporting assembly and a machining method thereof, and a centrifugal compressor. The bearing supporting assembly includes: bearing supports, provided with through holes for mounting radial bearings; and a fixing plate, detachably mounted at one end of each of the bearing supports along an axial direction, sides, away from the bearing supports, of the fixing plates being configured to mount first thrust bearings.

A propulsion system includes a drive shaft movable in rotation about an axis of rotation, a low-pressure compressor driven in rotation by the drive shaft, the low-pressure compressor having a mean radius, a fan shaft, a fan driven in rotation by the fan shaft, a reduction mechanism coupling the drive shaft and the fan shaft, having a reduction ratio, and an inlet channel which extends between the fan and the low-pressure compressor, the inlet channel having an inlet adjacent to the fan and an outlet opposite the inlet and adjacent to the low-pressure compressor, the inlet having a mean radius. A first ratio between a ratio of a mean radius of the inlet channel and the mean radius of the low-pressure compressor, and the reduction ratio of the reduction mechanism, is strictly less than 0.35.

A rocket engine propulsion system having improved engine performance is described herein. The rocket engine propulsion system includes an axial counterbalance to reduce or eliminate axial thrust exerted on components of a turbopump. The axial counterbalance can allow for a larger range of axial thrust forces while coupling this ability to a rotational speed (e.g., rotations per minute, or RPM) of a shaft. The axial counterbalance includes a protrusion on that extends circumferentially around a shaft that mates with a protrusion on a swing arm. The swing arm is rotatably attached to a bracket which is constrained by a static support.

A bearing, a gas turbine unit having such a bearing, and a method for operating and for increasing the efficiency a gas turbine unit, wherein the bearing has an annular bearing body, on the axially opposing end faces of which are provided two thrust bearings, each having a plurality of bearing elements which are distributed over the circumference, project and are movable in the axial direction, and have a bearing surface. The bearing elements of each thrust bearing are hydraulically displaceable axially outwards in two stages by predetermined amounts of movement.

An electric turbocharger includes: a thrust collar having a disk shape and provided to protrude in a flange shape around a rotation shaft between a compressor impeller and an electric motor; a thrust air bearing facing a compressor impeller-side surface of the thrust collar, and supporting the rotation shaft in a thrust direction; a thrust air bearing facing an electric motor-side surface of the thrust collar, and supporting the rotation shaft in the thrust direction; a bearing space which is interposed between the thrust air bearings and in which the thrust collar is accommodated; and a labyrinth seal portion provided along an outer peripheral surface of the thrust collar, and partitioning the bearing space into a first region on a compressor impeller side and a second region on an electric motor side.