Abstract: The cleaning device for the exhaust gas turbine comprises openings, which open out into the flow duct upstream of the nozzle ring, for injecting a cleaning liquid from the radially inner side into the annular flow duct, a cavity, which is connected to the openings, for distributing the cleaning liquid to the openings, and a supply line for supplying the cleaning liquid to the cavity. The cleaning device according to the invention provides a uniform distribution of water to nozzle ring or to the rotor blades of the turbine rotor wheel.

Abstract: A device for fastening a turbocharger to a base, with a fastening foot (12) which is integrally formed in one piece on a gas outlet casing (10) of the turbocharger and which has long holes (16) spaced from one another and preferably arranged in a star-shaped manner in relation to one another. In order to fasten the turbocharger, sliding shoes (26) are capable of being inserted into the long holes (16) and have continuous orifices, through which can be led fastening elements (30, 30?) capable of being fixed in the base.

Abstract: An exhaust-gas turbocharger with a compressor casing, turbine housing and bearing housing is supported on a base in the area of the bearing housing by means of a first support and in the area of the turbine housing by means of a second support. The second support is made in at least two parts, whereby the two parts can be moved relative to one another in the support direction. As a result, the length of the supports can be varied and counterbalance a temperature-related raising or lowering of the exhaust-gas turbocharger housing.

Abstract: The use of spring clamping clips (1) between two adjacent guide vane shafts (21, 22) leads to a defined force on the bearing points of the guide vane in the guide bush. The seating force, resulting from the clamping force and the flow-related lift/drift forces, of the guide vane in the guide bush is therefore always positive and the guide vane rests constantly in the guide bush.

Abstract: The exhaust-gas turbine comprises a turbine wheel arranged on a shaft, a bearing casing for the bearing arrangement of the rotatable shaft, a gas-inlet casing supported on the bearing casing and concentrically surrounding the bearing casing in the supporting region, and a centering ring for centering the gas-inlet casing relative to the shaft mounted in the bearing casing. The centering ring and either the bearing casing or the gas-inlet casing comprise grooves and either radially or axially unidirectional centering lugs for engaging in the grooves. Due to the radially or axially unidirectional centering lugs with corresponding grooves, at least one of the connections between the bearing casing and the centering ring and the centering ring and the gas-inlet casing is not positive-locking, as a result of which any desired positioning of the gas-inlet casing relative to the bearing casing is made possible.

Abstract: A method of clamping a rotationally symmetrical body (10) for the purpose of machining, in which method the body (10), with its first side (12), is pulled by means of a tensile force (F1), which acts in extension of the rotation axis (19, 19?) of the body (10) on the first side (12) of the body (10), against a supporting element (72) having a centering effect. A device for clamping a rotationally symmetrical body (10) for the purpose of machining, which device comprises a supporting element (72), against which the body (10) can be pulled, and a tie rod (64) which can act on and pull the body (10), to be clamped, axially and concentrically to the rotation axis (19, 19?) of the latter. The mounting of the tie rod (64) is designed in such a way that the tie rod (64) is axially guided with radial clearance (66) for the axial pulling movement. The tensile force (F1) of the tie rod (64) is preferably adjustable.

Abstract: The fastening arrangement (26) for an impeller (22) on a shaft (14), in particular for an impeller (22) of a turbocharger on a turbocharger shaft (14), comprises a bush (34), which can be screwed onto a shaft journal (20) of the shaft (14), and a shaft-side hub extension (30) of the impeller (22) having a central recess (32), into which the bush (34) can be inserted in a frictional manner. The hub extension (30), at least in the region of its shaft-side end, is designed approximately in the form of a hollow cylinder. The fastening arrangement (26) also comprises a press sleeve (36) which can be frictionally connected radially on the outside to the hub extension (30).

Abstract: In a turbocharger (1), comprising a turbine (2) and a compressor (3) connected to the turbine (2), the turbine (2) contains a turbine wheel (4) and the compressor (3) contains a compressor wheel (7) which are connected to one another by means of a shaft (10) and are arranged in a housing (5, 9, 16). During operation, if the compressor wheel (7) separates from the shaft (10), an axial force acts on the turbine wheel (4) and the shaft (10) connected thereto. A means (22, 25) for axially locking the shaft and the turbine wheel connected thereto in the housing (5, 9, 16) is arranged on the shaft (10) connected to the turbine wheel (4).

Abstract: The shaft is connected to the shaft attachment by a thread. A bore with an internal thread is incorporated in the shaft attachment and the shaft has a corresponding stem which can be introduced into the threaded bore and has an external thread. An axial stop is arranged on the shaft and on the shaft attachment. The internal and external threads have torque-transmitting flanks which are flat toward the axis and which can be connected to one another frictionally by radial pressure by mutual rotation of shaft and shaft attachment with interaction between the axial stops. Owing to the small angle between the load-bearing flanks and the axis, the radial pressure decisive for the torque transmission is correspondingly greater than in conventional threaded connections. As a result, the axial prestressing force between the two parts to be connected can be correspondingly reduced.

Abstract: The exhaust-gas turbine comprises a turbine wheel arranged on a shaft, a bearing casing for the bearing arrangement of the rotatable shaft, a gas-inlet casing supported on the bearing casing and concentrically surrounding the bearing casing in the supporting region, and a centering ring for centering the gas-inlet casing relative to the shaft mounted in the bearing casing. The centering ring and either the bearing casing or the gas-inlet casing comprise grooves and either radially or axially unidirectional centering lugs for engaging in the grooves. Due to the radially or axially unidirectional centering lugs with corresponding grooves, at least one of the connections between the bearing casing and the centering ring and the centering ring and the gas-inlet casing is not positive-locking, as a result of which any desired positioning of the gas-inlet casing relative to the bearing casing is made possible.

Abstract: The shaft (1) is connected to the shaft attachment (2) by means of a thread. A bore (20) with an internal thread is incorporated in the shaft attachment and the shaft has a corresponding stem (10) which can be introduced into the threaded bore and has an external thread. An axial stop (11, 21) is arranged in each case on the shaft and on the shaft attachment. The internal and external threads have torque-transmitting flanks which are flat toward the axis and which can be connected to one another frictionally by means of radial pressure by mutual rotation of shaft and shaft attachment with interaction between the axial stops.

Abstract: The guide-vane system serves to change the position of the guide vanes of an axial-flow exhaust-gas turbine of a turbocharger. The guide vanes are arranged axially symmetrically to the turbine axis in a flow passage carrying exhaust gas and can be pivoted by a pivoting device in each case about a radially directed axis. A vane shank led radially outward from the flow passage through a casing wall is attached to each of the guide vanes. With its part directed outward, the vane shank is mounted so as to be rotatable about the pivot axis. The pivoting device contains an adjusting ring, arranged outside the flow passage and rotatable about the turbine axis, and also an adjusting lever which transmits a torque from the adjusting ring to the vane shank of each guide vane. The adjusting ring is mounted with its outside on rolling elements which are each designed as one-armed levers and are mounted so as to be pivotable on a component of a casing wall, this component being designed as a supporting ring.

Abstract: The exhaust-gas turbine comprises a turbine casing (1), a shaft (3) rotatably mounted in a bearing housing (4), a turbine wheel (5) arranged on the shaft, and a heat-protection wall (2), the heat-protection wall defining with the turbine casing an inflow passage (6) leading to the turbine wheel. The heat-protection wall has two seatings, the first seating resting on the bearing housing (4) and the second seating resting on the turbine casing (1).

Abstract: The exhaust turbocharger includes an exhaust gas turbine and a turbine casing, in which is formed the volute inlet flow duct which starts with an inlet connection. An exhaust gas flow is carried to the exhaust gas turbine in this duct. The turbocharger also includes a flow straightener, which is arranged in the inlet connection and guides the exhaust gas flow in the volute direction of the inlet flow duct.

Abstract: A method for operating an exhaust gas turbocharger serving for charging an internal combustion engine, in which a main flow of a gas is supplied to a compressor (14) of the exhaust gas turbocharger via an intake line (26), is compressed in the compressor (14) and is led into an intake duct of the internal combustion engine via a compressor line. The gas quantity transferred to the combustion chambers of the internal combustion engine via the intake duct is regulated by means of a throttle valve (36) arranged between the compressor (14) and the combustion chambers.

Abstract: A Helmholtz resonator (24, 24′, 24″, 24a), which is screened in an acoustically transparent manner from the flow (S) by means of an absorption noise suppressor (36) is located on the flow duct (16) in order to suppress the low frequencies in an exhaust gas system (10) for industrial gas turbines with an exhaust gas conduit (12) and a chimney (14) which is connected to it, which together form a continuous flow duct (16).

Abstract: In a hydrodynamic axial bearing (10), a rotating body (13) is mounted radially in a radial bearing (17) of a bearing body (18). The rotating body (13) comprises a shaft (16), with its shaft journal (14) mounted in the radial bearing (17), and a bearing collar (20) which is connected fixedly to the shaft (16) and corotates with the shaft (16). A floating disk (12) is arranged in an annular-groove-shaped space (28) between a wall (26) of the fixed bearing body (18) and a projection (22) of the corotating bearing collar (20). The floating disk (12) has a central circular orifice (30) which is designed as an integrated hydrodynamic radial bearing (32). By means of this radial bearing (32), the floating disk (12) is mounted radially on a fixed bearing element (38) concentrically surrounding the rotating body (13) on a portion (29).

Abstract: So that sufficient combustion air is available in all the cylinders of a diesel internal combustion engine both under part load and in transient operating states, oxygen-containing gas or additional gas or compressed air from a gas distributor is additionally supplied under pressure to the combustion space of the cylinder, even after the diesel internal engine has been started, through at least one separate additional-gas inlet by means of at least one separate additional-gas valve (V1a). The supply of this additional gas can commence after closing of an air inlet valve (VE) or of an air outlet valve (VA) of the diesel internal combustion engine. The method is suitable for both 4-stroke and 2-stroke diesel internal combustion engines.

Abstract: A turbine blade is provided with a bracket arranged in the tip region of the blade and projecting beyond the blade profile. The bracket is formed merely in a section of a surface region of the pressure side, the surface region being enclosed by an imaginary chord bearing against the pressure side of the blade body both in the region of the leading edge and in the region of the trailing edge.

Abstract: The object of the invention is to improve the efficiency of a turbomachine blade provided with a reinforced hole for accommodating a damping element. To this end, the raised end faces (12, 13) of the marginal region (11), reinforced toward the hole (10), of the blade body (4) are formed with an acute angle (&agr;) open toward the leading edge (5) of the blade body (4) and/or with an acute angle (&bgr;) open toward the blade tip (9).