Abstract: Embodiments of a process for estimating a rotational speed of a rotating component and a process for estimating an acceptable rotor imbalance of a rotating component are provided herein. The process for estimating the rotational speed of a rotating component for a charging system comprises measuring a vibration signal of the rotating component by means of a sensor; and identifying harmonic train members from a plurality of peaked components of the vibration signal. Further, the process comprises determining a candidate fundamental frequency from the harmonic train members; and determining a derived vibration amplitude value from the vibration signal. This determination involves a filtering of the vibration signal, removing periodic contributions having a high amplitude. A scalar value is then derived from the filtered signal as a derived vibration amplitude value, representing the integrated total vibration amplitude of the filtered signal at the current speed.

Abstract: A turbine housing clamping connection for a turbine, and a turbine having a turbine housing clamping connection are described herein. The turbine housing clamping connection has a bearing housing, a turbine housing and a clamping component comprising a clamping flange clamped between a bearing housing clamping portion of the bearing housing and a turbine housing clamping portion of the turbine housing. The clamping flange has a bearing-housing-side clamping surface comprising a convexly curved clamping surface region. Furthermore, the convexly curved clamping surface region defines a minimum radius of curvature. A ratio of the minimum radius of curvature to an inner radius of the clamping surface is at least 0.1 and/or at most 10, and preferably at least 0.5 and/or at most 2.0, and more preferably at least 1.0 and/or at most 1.4.

Abstract: Embodiments of a compressor stage, in particular for a turbocharging system and/or a turbocompound, and a process for operating a compressor stage are provided herein. The compressor stage comprises an impeller, and a vaned diffuser arranged downstream of the impeller. The vaned diffuser is in fluid connection with an outlet of the impeller and comprises an injection device configured to inject a secondary fluid into the vaned diffuser. The injection device comprises a displaceable port at least partially arranged between an adjacent pair of vanes of the diffuser.

Abstract: A centering device (10) for centering a turbine housing (40) with respect to a central axis (33) of a radial turbine of a turbo system is described. The centering device (10) includes a ring-shaped body (11) having an outer diameter D1 and an inner diameter D2, wherein a ratio of D1/D2 is ?2. Additionally, the centering device (10) includes two or more centering elements (16) provided on a side surface (12) of the ring-shaped body (11) for engaging with respective complementary centering elements (21) provided on a bearing housing (20). The two or more centering elements (16) are configured for allowing a radial thermal expansion of the ring-shaped body (11) during engagement of the two or more centering elements (16) with the respective complementary centering elements (21). Further, a turbo system, including such a centering device as well as a method of centering a turbine housing are described.

Abstract: A mixture supply system with quantitative mixture control comprises a charging system connectable to an internal combustion engine, comprising a bypass and a bypass valve, and a valve train for periodically actuating an intake valve of the internal combustion engine. A valve control time of the intake valve is controllable by the valve train. The system is configured to at least partially close the bypass valve and change the valve control time for extending the valve opening duration upon increase of an engine load, to at least partially open the bypass valve during and/or after expiration of a valve train latency time, and/or to at least partially open the bypass valve and change the valve control time for decreasing the valve opening duration upon an decrease of an engine load, and to at least partially close the bypass valve during and/or after expiration of a valve train latency time.

Abstract: A turbocharging assembly is described. The turbocharging assembly includes a compressor having a compressor wheel and a turbine having a turbine wheel. The turbine wheel and the compressor wheel are mounted back-to-back on a shaft. The shaft is coupled to a power converter provided in front of the compressor wheel. Additionally, the turbocharging assembly includes a housing extension encasing the power converter. The housing extension is connected with a compressor housing. The power converter includes a rotor and a stator. The stator is mounted to the housing extension. Further, the turbocharging assembly includes a filter silencer arranged between the compressor and the power converter. Yet further, the turbocharging assembly includes a blower mounted to the shaft. The blower is arranged at a side of the power converter facing away from the compressor.

Abstract: The invention relates to a stabilizer channel having an annular stabilizer chamber which encloses a main flow channel in the intake region of a compressor wheel and is delimited from the main flow channel by an annular bridge. The annular stabilizer channel is connected to the main flow channel via a downstream flow inlet and an upstream flow outlet. At least one separating element (T) is arranged in at least one of the flow inlet and the flow outlet, with the result that an inflow into the annular stabilizer chamber and/or an outflow out of the annular stabilizer chamber are/is split transversely with respect to the main flow direction of the main flow channel. At least one flow guiding element is arranged in at least one of the flow inlet and the flow outlet.

Abstract: The invention relates to a turbocharger which contains a bearing device which is arranged between a compressor and a turbine and which is designed to support a shaft. This bearing device has a bearing housing, in which an oil-lubricated bearing for supporting the shaft is arranged. The shaft has a slinger element extending in the circumferential direction for centrifugally dispersing lubricating oil. The bearing housing has an oil drainage channel for discharging the lubricating oil from the bearing housing. The inner region of the bearing housing forms an oil delimitation chamber, which is sealed off by seals arranged between the shaft and the bearing housing. The oil delimitation chamber has a deflection means which is formed in such a way that, during operation of the turbocharger, lubricating oil that is centrifugally dispersed by the slinger element is deflected by the deflection means and is conducted in the opposite direction to the seals.

Abstract: The invention relates to a stabilizer channel, in particular of a radial compressor or diagonal compressor, having an annular stabilizer chamber which encloses a main flow channel in the intake region of a compressor wheel and is delimited from the main flow channel by an annular bridge. The annular stabilizer chamber is bladeless and is connected to the main flow channel via a downstream inlet channel and an upstream outlet channel. A plurality of flow directing elements are arranged in the downstream inlet channel. The downstream inlet channel is arranged between an upstream part of the annular bridge and a downstream part of the annular bridge. The invention furthermore relates to a compressor, in particular a radial compressor or diagonal compressor, comprising the stabilizer channel according to the invention and to a turbocharger comprising the compressor.

Abstract: A shaft bearing assembly having a shaft supported in a bearing housing is described. The shaft bearing assembly includes a pressure reduction device for generating an underpressure inside the bearing housing. The pressure reduction device is operated by employing an incompressible fluid. Further, a method of reducing a pressure inside a bearing housing supporting a shaft is described. The method includes using an incompressible fluid for operating a pressure reduction device for generating an underpressure inside the bearing housing.

Abstract: An exhaust turbocharger including a modular bearing designed for bearing a shaft and arranged between a compressor and a turbine is provided herein. The bearing has a bearing housing having a receptacle chamber, wherein a bearing assembly module can be or is installed in the receptacle chamber and can be non-destructively removed. The receptacle chamber is sized such that either a bearing assembly module having a rolling bearing or a bearing assembly module having a slide bearing can be installed. The receptacle chamber has an interface, designed to contact the bearing flange of a bearing assembly module inserted into the receptacle chamber. The interface is designed to connect an oil gallery passing through the bearing housing to one or more oil galleries passing through a bearing flange of the bearing assembly module.

Abstract: An outflow region of a compressor. The outflow region comprises a flow channel delimited by a side wall at a shroud side and a side wall at a hub side. The side wall at the hub side has, in a region of the compressor wheel outlet, a contour configured such that, in a flow direction, the cross-sectional areas of the flow channel decrease, pass through a minimum and increase again. In the region of the compressor wheel outlet, the flow channel has a length L which extends from a compressor wheel outlet edge to a diffuser blade inlet edge of a diffuser region. The diffuser region adjoins the region of the compressor wheel outlet and has multiple diffuser blades. A compressor with the outflow region according to the invention, and to a turbocharger having the compressor.

Abstract: An exhaust turbine includes a turbine wheel having a plurality of rotor blades, an exhaust outlet where the exhaust outlet is arranged downstream of the rotor blades and is delimited radial to the outside by an axial turbine diffusor. An exhaust mass flow can be output in an axial flow direction by the exhaust outlet duct and the axial turbine diffusor opens downstream, radially to the outside at a non-constant diffusor-opening angle, such that at a first diffusor-opening angle deviates from a second diffusor-opening angle by at least 1°. The exhaust turbine further includes a waste gate duct, the outlet region of which opens into the diffusor or directly downstream of the diffusor into the exhaust outlet duct. The waste gate duct is designed to generate a substantially axial flow direction of a waste gate mass flow at the outlet region of the waste gate duct.

Abstract: A turbine casing for an exhaust-gas turbine is provided herein. The turbine casing has a connection flange for bearing-casing-side attachment to a bearing casing in which casing-connection holes that are mutually spaced in the circumferential direction are provided, wherein, between adjacent casing-connection holes, material recesses that are open radially inwards towards a central longitudinal axis of the turbine casing are provided in the connection flange. Further provided herein is an exhaust-gas turbine that is equipped with the turbine casing.

Abstract: Embodiments of bladed rotors and methods for manufacturing bladed rotors are provided herein. The method for manufacturing bladed rotors includes providing a workpiece including a first rotor blade segment. The first rotor blade segment includes a first platform portion on a radially outward end portion of the first rotor blade segment. Further, the method includes forming a second rotor blade segment, by additive manufacturing, removing a side portion of the first platform portion, and removing a side portion of the second rotor blade segment, whereby a second platform portion remains on a radially outward end portion of the second rotor blade segment.

Abstract: A nozzle ring for a radial turbine includes a disc-shaped main body having a central opening for passing a shaft therethrough. Additionally, the nozzle ring includes guide vanes disposed circumferentially in a radially outer portion on a first surface of the main body. Two or more bores are provided in a radially inner portion of the main body. Further, a groove is provided in the first surface of the main body, the groove connecting at least two of the two or more bores.

Abstract: A multi-stage turbocharging assembly is described. The multi-stage turbocharging assembly includes a high-pressure stage including a high-pressure turbine coupled with a high-pressure compressor. Additionally, the multi-stage turbocharging assembly includes a low-pressure stage including a low-pressure turbine coupled with a low-pressure compressor: Further, the multi-stage turbocharging assembly includes a casing enclosing the high-pressure stage and the low-pressure stage, wherein the casing is a single unit.