A pneumatic motor for pneumatic tools includes a cylinder provided therein with a vane wheel. A rotating shaft inserted in the vane wheel is provided with a withstanding member and a tightening member, which can push the withstanding member to move toward the vane wheel and tighten the vane wheel with the rotating shaft for avoiding gap between the vane wheel and the rotating shaft. Thus, when outside driving air pushes the vane wheel to rotate, the vane wheel can synchronously drive the rotating shaft to rotate immediately and truly. By so designing, this invention can solve the problems of the conventional pneumatic motor that is likely to cause starting delay, untrue in power transmission and easy to wear.

Turbine housing assemblies and related turbocharger systems are provided. One exemplary turbine housing assembly includes a core structure having a voided inner region defining an axial outlet and an outer surface defining an inner contour of a volute and an inner sheet metal shell having an inner base portion defining an inlet in fluid communication with the volute and a volute portion defining an outer contour of the volute, wherein at least a portion of the core structure defining the axial outlet extends in an axial direction through an opening in the inner sheet metal shell defined by the volute portion. The turbine housing assembly also includes an outer sheet metal shell surrounding the volute portion and including an outer base portion circumscribing the inner base portion.

The invention relates to a device (1) for separating an air/oil mixture comprising an air/oil mixture inlet (8), an oil receiving chamber (9), an air circulation duct (11), at least one filter element (21) rotatably coupled to a rotating drive shaft (12), the device (1) being designed so that the mixture from the above-mentioned inlet (8) opens into the chamber (9) and is driven through the rotatably driven filter element (21), so that the oil contained in the mixture is centrifuged radially outside the filter element (21) and fed into the oil receiving chamber (9), the filtered air opening into the air flow line (11), characterized in that the rotating drive shaft (12) is coupled to a turbine (26) capable of being driven in rotation by at least part of the filtered air flow, the turbine (26) comprising an outlet (29) of the filtered flow which opens to the outside.

The centrifugal impeller can have a hub and a plurality of blades, each of the blades having a span extending from the hub to a tip edge, camber lines extending from an inlet edge to an outlet edge between two opposite faces, including a tip camber line extending along the tip edge and a 50% span camber line extending at 50% of the span, a thickness extending between opposite faces of each blade, the tip edge having, at a location corresponding to 5% of the tip camber line, less than 15% of the maximum thickness, each of the blades having, along the 50% span camber line, a thickness reaching at least 58% of the maximum thickness and then reducing by at least 5% of the maximum thickness within 10% of the length of the 50% span camber line.

A turbine rotor blade according to at least one embodiment of the present invention is to be connected to a rotational shaft so as to be rotatable around an axis and includes: a hub having a hub surface inclined with respect to the axis in a cross-section along the axis; at least one rotor blade disposed on the hub surface; and a connection passage disposed inside the turbine rotor blade and connecting a first opening disposed in the at least one rotor blade and a second opening disposed downstream of the first opening in the turbine rotor blade.

An exhaust gas turbine is provided. The exhaust gas turbine includes a first turbine housing part having insulating material extending along an interior surface and a second turbine housing part having insulating material extending along an interior surface, the second turbine housing part coupled to the first turbine housing part to form a volute directing exhaust gas to a turbine wheel.

The centrifugal impeller can have a hub and a plurality of blades, each of the blades having a span extending from the hub to a tip edge, camber lines extending from an inlet edge to an outlet edge between two opposite faces, including a tip camber line extending along the tip edge and a 50% span camber line extending at 50% of the span, a thickness extending between opposite faces of each blade, the tip edge having, at a location corresponding to 5% of the tip camber line, less than 15% of the maximum thickness, each of the blades having, along the 50% span camber line, a thickness reaching at least 58% of the maximum thickness and then reducing by at least 5% of the maximum thickness within 10% of the length of the 50% span camber line.

A multi-stage turboexpander and a method for generating mechanical power therewith are disclosed. The multi-stage turboexpander includes a casing and a shaft, arranged for rotation in the casing. The shaft is supported by a first bearing at a first shaft end portion and a second bearing at a second shaft end portion. A first radial impeller and a second radial impeller are arranged between the first bearing and the second bearing on the shaft for co-rotation therewith around a rotation axis.

An impeller for a centrifugal compressor, the impeller comprising: a hub defining a rotation axis about which the impeller is rotatable; and a vane extending from the hub, the vane having a leading edge, a trailing edge, and a chord defined therebetween, a pressure side of the vane and a suction side of the vane opposite the pressure side, a vane thickness defined transversely between the pressure side and the suction side, the vane thickness reducing over at least a downstream 40% of the chord, the vane thickness having a trailing edge thickness value at the trailing edge of between 40% and 80% of a maximum thickness value of the vane thickness.

A turbocharger turbine rotor includes a rotor basic body, and moving blades configured without an outer shroud. The moving blades, forming a defined curvature region, merge into the rotor basic body with a defined, constant or variable curvature radius r.sub.f. On a first group of first moving blades, the following relationship applies to the curvature radius of the curvature region of the first moving blades: 2.5%r.sub.f1*100/l10%, wherein r.sub.f1 is the constant or variable curvature radius of the curvature region of the first moving blades and l the length of the first moving blades on a flow trailing edge. On a second group of second moving blades, the curvature radius r.sub.f2 of the curvature region of the second moving blades deviates from the curvature radius rf1 of the curvature region of the first moving blades on the damping side in a defined manner.