Abstract: Disclosed is an installation/removal device for translationally moving one or more rotor blocks in a housing of a single- or multi-stage turbocharger assembly. The device comprises a support element having first and second guide rails. Furthermore, the device comprises a movement device having a first slide, which is movably arranged on the first guide rails, and a second slide which is movably arranged on the second guide rails. The movement device comprises a spindle, which is rotatably mounted in the support element, and a connection element which is connected to the spindle, to the first slide and/or to the second slide. The device comprises a fastening device having a first fastening structure for fastening a first rotor block and a second fastening structure for fastening a second rotor block. The first fastening structure is connected to the first slide, and the second fastening structure is connected to the second slide.

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: 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 turbocharging assembly is described. The turbocharging assembly includes a housing having a first housing part for enclosing a first stage, particularly a low-pressure stage, comprising a first turbine coupled with a first compressor, particularly a low-pressure turbine coupled with a low-pressure compressor, and a second housing part for enclosing a second stage, particularly a high-pressure stage. The second housing part encases an exhaust gas passage unit replacing a second turbine, particularly a high-pressure turbine, the exhaust gas passage unit being an insert configured for providing a gas passage from an exhaust gas inlet provided in the second housing part to the first turbine. Further, a method of operating a multi-stage turbocharging assembly as single-stage turbocharger is described.

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.

Abstract: The invention relates to an exhaust gas turbocharger with a silencer. The silencer comprises a multiplicity of damping elements which are arranged concentrically about a central axis of the silencer and are spaced apart concentrically from one another, with the result that a flow duct is formed in each case between adjacent damping elements. The flow duct has an inlet which is at a greater radial spacing from the central axis than an outlet of the flow duct.

Abstract: A multi-stage turbocharging assembly (100) is described. The multi-stage turbocharging assembly (100) includes a high-pressure stage (110) including a high-pressure turbine (113) coupled with a high-pressure compressor (114). Additionally, the multi-stage turbocharging assembly (100) includes a low-pressure stage (120) including a low-pressure turbine (123) coupled with a low-pressure compressor (124): Further, the multi-stage turbocharging assembly (100) includes a casing (130) enclosing the high-pressure stage (110) and the low-pressure stage (120), wherein the casing (130) is a single unit.

Abstract: Described herein is an air feed system for an internal combustion engine. The air feed system includes a charge air receiver for receiving charge air and a starting air system. The starting air system is designed to feed starting air, in particular from a starting air feed, to the cylinder of the internal combustion engine intermittently during a starting process of the internal combustion engine. The charge air receiver is connected to the starting air system via a charge air shut-off valve in order to feed charge air from the charge air receiver to the starting air system during partial-load operation of the internal combustion engine, such that the starting air system feeds charge air to the cylinder intermittently during partial-load operation of the internal combustion engine. Also described herein are an internal combustion engine and a method for operating an internal combustion engine.

Abstract: The disclosure relates to a valve train for an internal combustion engine and to an internal combustion engine. The valve train has an inlet valve actuation mechanism for the periodic actuation of an inlet valve of the internal combustion engine. The valve train also has a delay element, which is in contact with the inlet valve actuation mechanism and which has a hydraulic chamber for delaying a closing movement of the inlet valve by means of a hydraulic medium. The valve train has a hydraulic feed for feeding the hydraulic medium into the hydraulic chamber, the hydraulic feed having a control shaft, and the control shaft being mechanically driven by the internal combustion engine. The control shaft has an axially extended cavity for the hydraulic medium, and at least one opening for intermittently feeding the hydraulic medium from the cavity to the hydraulic chamber.

Abstract: The disclosure relates to a compressor housing of a radial compressor. The compressor housing includes a radially inner housing region which forms an axial inflow channel in an intake region of the radial compressor. The compressor housing also includes a diffusor region which adjoins the radially inner housing region. The diffusor region is designed to deflect a radial flow downstream of a compressor impeller into an axial direction counter to an inflow direction of the inflow channel. The compressor housing also includes a radially outer housing region which adjoins the diffusor region, extends axially counter to the inflow direction and provides one or more charge air manifolds.

Abstract: The invention relates to an exhaust gas turbine, comprising a turbine rotor (12) having a plurality of turbine rotor blades (2) with a turbine rotor blade height H. The exhaust gas turbine further comprises a diffuser arrangement (20) having a transverse diffuser (1) and an exhaust gas collection chamber (9). The transverse diffuser (1) is arranged downstream of the turbine rotor blades (2). The transverse diffuser (1) has a curved diffuser channel (13) which opens into the exhaust gas collection chamber (9) at a diffuser channel outlet (17). A M/H ratio between an axial extension M of the exhaust gas collection chamber (9) and the turbine rotor blade height H has a value of 1.0?M/H?4.6 and a P/H ratio between a radial extension P of the diffuser arrangement (20) and the turbine rotor blade height H has a value of 2.7?P/H?4.9. A D/H ratio between a radial expansion D of the diffuser channel section (13) and the turbine rotor blade height H has a value of 2.5?D/H?3.

Abstract: The invention relates to an exhaust gas turbine, comprising a turbine wheel (7) with a multiplicity of moving blades (8) and an exhaust-gas outlet duct (15), which is arranged downstream of the moving blades of the turbine wheel. The exhaust-gas outlet duct (15) is delimited radially on the outside by an axial turbine diffuser (1) and radially on the inside, at least partially, by a spinner (2). The axial turbine diffuser (1) is formed by a number N>1 of successive conical diffuser segments. An axial diffuser opening angle A between successive diffuser segments is A>1.0°. A ratio L/H between an axial diffuser segment length L and an entry height H of the exhaust-gas outlet duct (15) is L/H>0.01. A ratio H/S between the entry height H of the exhaust-gas outlet duct and a maximum radius S of the spinner (2) is H/S>1.0. The spinner (2) is formed by a number P>1 of successive conical spinner segments. An axial spinner opening angle B between successive spinner segments is B>1.0°.

Abstract: The invention relates to an exhaust gas turbine, comprising a turbine rotor (12) having a plurality of turbine rotor blades (2) with a turbine rotor blade height H. The exhaust gas turbine further comprises a diffuser arrangement (20) having a transverse diffuser (1) and an exhaust gas collection chamber (9). The transverse diffuser (1) is arranged downstream of the turbine rotor blades (2). The transverse diffuser (1) has a curved diffuser channel (13) which opens into the exhaust gas collection chamber (9) at a diffuser channel outlet (17). A M/H ratio between an axial extension M of the exhaust gas collection chamber (9) and the turbine rotor blade height H has a value of 1.0?M/H?4.6 and a P/H ratio between a radial extension P of the diffuser arrangement (20) and the turbine rotor blade height H has a value of 2.7?P/H?4.9. A D/H ratio between a radial expansion D of the diffuser channel section (13) and the turbine rotor blade height H has a value of 2.5?D/H?3.

Abstract: The invention relates to an exhaust gas turbine, comprising a turbine wheel (7) with a multiplicity of moving blades (8) and an exhaust-gas outlet duct (15), which is arranged downstream of the moving blades of the turbine wheel. The exhaust-gas outlet duct (15) is delimited radially on the outside by an axial turbine diffuser (1) and radially on the inside, at least partially, by a spinner (2). The axial turbine diffuser (1) is formed by a number N>1 of successive conical diffuser segments. An axial diffuser opening angle A between successive diffuser segments is A>1.0°. A ratio L/H between an axial diffuser segment length L and an entry height H of the exhaust-gas outlet duct (15) is L/H>0.01. A ratio H/S between the entry height H of the exhaust-gas outlet duct and a maximum radius S of the spinner (2) is H/S>1.0. The spinner (2) is formed by a number P>1 of successive conical spinner segments. An axial spinner opening angle B between successive spinner segments is B>1.0°.

Abstract: Exemplary embodiments of the present disclosure are directed to a 2-stage supercharging unit having a housing unit which integrates within it a high-pressure charger and a low-pressure charger. The rotor axes of the two chargers are vertical with respect to the housing unit, which can be screwed directly via the housing base to the side of an internal combustion engine. As a result, increased flexibility is made possible with regard to the connection of the supercharging unit to the cooler and to the internal combustion engine, whereby the structural volume of the supercharging assembly can be additionally reduced.

Abstract: Exemplary embodiments of the present disclosure are directed to a 2-stage supercharging unit having a housing unit which integrates within it a high-pressure charger and a low-pressure charger. The rotor axes of the two chargers are vertical with respect to the housing unit, which can be screwed directly via the housing base to the side of an internal combustion engine. As a result, increased flexibility is made possible with regard to the connection of the supercharging unit to the cooler and to the internal combustion engine, whereby the structural volume of the supercharging assembly can be additionally reduced.

Abstract: In a fuel injection system and method for a diesel engine with compression induced ignition, NOx emissions are reduced by providing a supplemental fuel injection from a supplemental injection nozzle, in addition to the primary fuel injection through a primary injection nozzle. The supplemental injection nozzle injects a supplemental quantity of fuel onto a vaporization surface such as an exhaust valve, a flame ring area, or a top surface of the piston, in the combustion chamber, whereupon the supplemental fuel vaporizes and forms a lean air/fuel mixture. Thereafter, the primary injection nozzle injects the main fuel charge into the combustion chamber, to produce a rich air/fuel combustion mixture, which is then ignited and combusts.

Abstract: A vibration suppressor and a vibration damper are configured in a system including an internal combustion engine and an exhaust-gas turbo charger. The vibration suppressor and vibration damper are secured to an exposed place on the system which is subjected to strong vibrations. As the vibrations are the strongest in said area, the vibration reducer can be used to a maximum. The system including the internal combustion engine and the exhaust-gas charger is enhanced in such a manner that the internal combustion engine can be operated in all of the rotational speed ranges without reducing the service life of individual components or the entire system.

Abstract: Depending on the actual operating situation and the composition of the fuels used for driving the internal combustion engine, contamination of the moving blades, of the guide device and of the turbine casing parts occurs sooner or later in the exhaust gas turbine. According to the invention, a small quantity of cleaning fluid is fed continuously or cyclically into the exhaust gas flow of an exhaust gas turbine and is directed onto the components to be cleaned. The small quantity of cleaning fluid can be fed in with unchanged operation of the internal combustion engine, such that the exhaust gas turbine can be cleaned or kept clean within the entire operating range of the internal combustion engine. Fluctuations in the power output of the internal combustion engine on account of requisite cleaning of the exhaust gas turbine therefore do not occur. Furthermore, the formation of thermostress cracks in the critical turbine casing parts is largely avoided.

Abstract: Depending on the actual operating situation and the composition of the fuels used for driving the internal combustion engine, contamination of the moving blades, of the guide device and of the turbine casing parts occurs sooner or later in the exhaust gas turbine. According to the invention, a small quantity of cleaning fluid is fed continuously or cyclically into the exhaust gas flow of an exhaust gas turbine and is directed onto the components to be cleaned. The small quantity of cleaning fluid can be fed in with unchanged operation of the internal combustion engine, such that the exhaust gas turbine can be cleaned or kept clean within the entire operating range of the internal combustion engine. Fluctuations in the power output of the internal combustion engine on account of requisite cleaning of the exhaust gas turbine therefore do not occur. Furthermore, the formation of thermostress cracks in the critical turbine casing parts is largely avoided.