Turbo Systems Switzerland Ltd.

Abb Turbo Systems Ag

Abb Schweiz Ag

Accelleron Switzerland Ltd.

Daniel Bernhard Rusch

Bent Phillipsen

Gerd Mundinger

Christian Kreienkamp

Jean-Francois Tissot

Armin Reichl

Rene Hunziker

Andrea Vacca

Ansgar Weickgenannt

Alessandro Sofia

Matthias Schleer

Jürg Weber

The invention relates to a stabilizer of a compressor, in particular of a radial compressor or diagonal compressor. The stabilizer comprises a first annular stabilizer chamber which encloses a main flow channel in the intake region of a compressor wheel. The stabilizer further comprises a second annular stabilizer chamber which encloses the first annular stabilizer chamber. The invention further relates to a compressor, in particular a radial compressor or diagonal compressor, comprising the stabilizer according to the invention, and to a turbomachine, in particular a turbocharger, comprising the compressor.

Stabilizer of a compressor

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.

Secondary-fluid supply for the diffuser of a compressor stage

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.

Stabilizer channel of a compressor

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.

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.

Outflow region of a compressor, compressor having an outflow region of said type, and turbocharger having the compressor

The invention relates to a diffuser for a radial compressor, comprising a flow channel defined by a first side wall and a second side wall, a diffuser vane ring with a plurality of diffuser vanes that are at least partially arranged in the flow channel, each of the diffuser vanes having a pressure side and a suction side, a plurality of diffuser passages, said diffuser passages being formed between every two adjacent diffuser vanes of the plurality of diffuser vanes, and circulation openings, each circulation opening connecting the flow channel to a diffuser cavity, at least two circulation openings being associated with one diffuser passage, and a circulation opening associated with a diffuser passage being fluidically connected to another circulation opening associated with the same diffuser passage or to a circulation opening associated with another diffuser passage, via the diffuser cavity.

Diffuser for a radial compressor

The present invention relates to a compressor assembly for a turbocharger. The compressor assembly may comprise a spiral housing with a flow channel which is designed to convey a fluid which can be sucked up from outside the compressor assembly, a compressor outlet flange which is fluidically connected to the spiral housing via the flow channel, and an injection device designed to introduce a fluid from outside the compressor assembly into the flow channel, wherein the injection device is arranged outside the flow channel of the spiral housing.

Compressor assembly for a turbocharger

The present disclosure relates to a diffuser for a radial compressor. The diffuser may comprise a diffusor duct portion formed by first and second side walls that are arranged so as to diverge at least partially from one another in a direction of flow, a blade ring having a number of blades arranged at least partially in the diffusor duct portion with each blade having a pressure side and a suction side delimited by a blade leading edge and by a blade trailing edge of the respective blade, a number of pressure equalizing openings incorporated into at least one of the first and second side walls of the diffuser duct portion in a region where the first and second side walls diverge from one another with each of the pressure equalizing openings being arranged between the pressure side of one blade and the suction side of an adjacent blade of the blade ring, and a first annular duct arranged behind the pressure equalizing openings and fluidically connected to the diffuser duct portion via at least two of the pressure equalizing openings, such that a number of regions between two adjacent blades of the blade ring in the diffuser duct portion are fluidically connectable together.

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Wettingen, Switzerland

Daniel Bernhard Rusch