Abstract: A compressor wheel for an internal combustion engine may include a plurality of blades which in a circumferential direction of the wheel are spaced from one another. The plurality of blades may respectively include an inflow edge which during operation are subject to an inflow of a compressible fluid substantially axially to the wheel axis. The plurality of blades may include a surface layer of locally distinct materials to adapt to locally distinct loads during operation.

Abstract: A rotor for at least one of a turbine and a compressor of a supercharging device may include a shaft defining an axis of rotation and at least one impeller. The at least one impeller may have a thread which is arranged coaxially to the axis of rotation. The shaft may include a complementary thread which is arranged coaxially to the axis of rotation. The shaft and the at least one impeller may be secured together via the respective threads. The shaft and the at least one impeller may be fixed with respect to one another via at least one of a soldered connection, a welded connection, an adhesive bond, a clamped connection and a crystallization connection.

Abstract: A rotor for at least one of a turbine and a compressor of a supercharging device may include a shaft defining an axis of rotation and at least one impeller. The at least one impeller may have a thread which is arranged coaxially to the axis of rotation. The shaft may include a complementary thread which is arranged coaxially to the axis of rotation. The shaft and the at least one impeller may be secured together via the respective threads. The shaft and the at least one impeller may be fixed with respect to one another via at least one of a soldered connection, a welded connection, an adhesive bond, a clamped connection and a crystallization connection.

Abstract: A compressor wheel for an internal combustion engine may include a plurality of blades which in a circumferential direction of the wheel are spaced from one another. The plurality of blades may respectively include an inflow edge which during operation are subject to an inflow of a compressible fluid substantially axially to the wheel axis. The plurality of blades may include a surface layer of locally distinct materials to adapt to locally distinct loads during operation.

Abstract: The invention relates to a rotor (1) of a turbomachine, in particular of an exhaust gas turbocharger, with a rotor wheel (2) which has a wheel back (3), and with a rotor shaft (4) which has an intermediate piece (5), via which the rotor shaft (4) is connected rigidly to the rotor wheel (2), the intermediate piece (5) being provided with a disk-shaped balancing plate (5A), the outside diameter (DA) of which is larger than the largest diameter (D4C) of the rotor shaft (4) and which is fixed to the wheel back (3) of the rotor wheel (2).

Abstract: A charging device may include a turbine housing and a bearing housing. The bearing housing may have a bearing arrangement for a shaft carrying a turbine wheel and a compressor wheel. A gasket may be arranged by metal-to-metal connection between a radially orientated flat surface of the turbine housing and a radially orientated flat surface of the bearing housing. The gasket may be resilient.

Abstract: A bearing housing may have a bearing housing cover formed of metal. A first thread may be arranged on the bearing housing cover and a second thread may be arranged on the bearing housing and designed complementarily to the first thread so that the bearing housing cover may be screwed on and fixed on the bearing housing through a rotational movement.

Abstract: The invention refers to a turbocharger with a compressor (8) which has a compressor wheel (9) which is fixed on one end of a rotor shaft (6); with a turbine (2) which has a turbine rotor (10) which comprises a turbine wheel (5) which has a connecting journal (17) which can be connected to a connecting section (12) of the rotor shaft (6), and with at least one piston ring groove (11, 11?) which is provided on the turbine rotor (10); wherein the piston ring groove (11, 11?) is arranged on the connecting journal (17).

Abstract: A charging device may include a turbine housing and a bearing housing. The bearing housing may have a bearing arrangement for a shaft carrying a turbine wheel and a compressor wheel. A gasket may be arranged by metal-to-metal connection between a radially orientated flat surface of the turbine housing and a radially orientated flat surface of the bearing housing. The gasket may be resilient.

Abstract: The invention relates to a rotor (1) of a turbomachine, in particular of an exhaust gas turbocharger, with a rotor wheel (2) which has a wheel back (3), and with a rotor shaft (4) which has an intermediate piece (5), via which the rotor shaft (4) is connected rigidly to the rotor wheel (2), the intermediate piece (5) being provided with a disk-shaped balancing plate (5A), the outside diameter (DA) of which is larger than the largest diameter (D4C) of the rotor shaft (4) and which is fixed to the wheel back (3) of the rotor wheel (2).

Abstract: The invention concerns a method to create fusion-integrated joints of workpieces, in which a workpiece area formed on a workpiece made from a TiAl alloy and a workpiece area formed on another workpiece made from a TiAl alloy or a different high temperature material are joined in a joint area using a joining additive, where the joining additive contains at least one of the elements gallium and indium. The invention also concerns a method to create a material deposit on a workpiece, in which a deposit material is applied to a workpiece area made from a TiAl alloy, where a fusion-integrated joint is produced between the deposit material and the workpiece area, where the deposit material contains at least one of the elements gallium and indium and a filler material.

Abstract: The invention relates to a turbocharger (1), comprising a compressor (8), with a compressor wheel (9) fixed to one end of a rotor shaft (6) and a turbine (2), with a turbine rotor (10) which has a turbine wheel (5) with a fixing section (11) which may be connected to a connector part (12) of the rotor shaft (6) by means of a connector device (14, 15), said connector device (14, 15) being designed as a combination of a press connection and a positive-fit connection, the cross-section (Q1, Q1?, Q1?) of the connector part (12) being orbiform

Abstract: The invention refers to a turbocharger with a compressor (8) which has a compressor wheel (9) which is fixed on one end of a rotor shaft (6); with a turbine (2) which has a turbine rotor (10) which comprises a turbine wheel (5) which has a connecting journal (17) which can be connected to a connecting section (12) of the rotor shaft (6), and with at least one piston ring groove (11, 11?) which is provided on the turbine rotor (10); wherein the piston ring groove (11, 11?) is arranged on the connecting journal (17).

Abstract: A pre-whirl generating apparatus (26) is provided that employs deformable air deflecting vanes (46) adjacent the inlet (18) of a radial air compressor (12-22), which vanes (46) can be mechanically deformed to generate positive, neutral, or negative pre-whirl flow to the compressor. A minimum number of parts are used to position one or more thin, deformable vanes (46) in the intake channel (34) leading to the compressor inlet (18). In their undeformed position, the vanes (46) do not deflect the incoming air, thereby causing little or no flow restriction. To achieve the desired positive or negative pre-whirl of flow to the compressor (12-22), the trailing edge (62) of the vanes (46) are deflected transverse to the direction of flow in the channel (34) in either the positive or negative direction.

Abstract: A pre-whirl generating apparatus (26) is provided that employs deformable air deflecting vanes (46) adjacent the inlet (18) of a radial air compressor (12-22), which vanes (46) can be mechanically deformed to generate positive, neutral, or negative pre-whirl flow to the compressor. A minimum number of parts are used to position one or more thin, deformable vanes (46) in the intake channel (34) leading to the compressor inlet (18). In their undeformed position, the vanes (46) do not deflect the incoming air, thereby causing little or no flow restriction. To achieve the desired positive or negative pre-whirl of flow to the compressor (12-22), the trailing edge (62) of the vanes (46) are deflected transverse to the direction of flow in the channel (34) in either the positive or negative direction.