DE202015100965U1 - turbine - Google Patents

Abstract

Turbine (1) with a turbine housing (2), in which at least one on a rotatable shaft (4a) mounted impeller (4) is arranged, in which
- The turbine housing (2) has an inlet region (6) for supplying exhaust gas and an outlet region (7) for discharging the exhaust gas, wherein the inlet region (6) upstream of the at least one impeller (4) and belonging to a Abgasabführsystem (8) Outlet region (7) is arranged downstream of the at least one impeller (4) and adjoins the at least one impeller (4),
- At least one exhaust gas leading flow channel (5) is provided, which connects the inlet region (6) via the impeller (4) with the outlet region (7),
characterized in that
At least one overpressure line (2b, 2c) is provided, which branches off upstream of the outlet region (7) from the at least one exhaust gas flow channel (5) and flows downstream of the at least one impeller (4) into the Abgasabführsystem (8), wherein in the Pressure relief line (2b, 2c) an automatically controlling pressure valve (3) is arranged.

Description

• – das Turbinengehäuse einen Eintrittsbereich zum Zuführen von Abgas und einen Austrittsbereich zum Abführen des Abgases aufweist, wobei der Eintrittsbereich stromaufwärts des mindestens einen Laufrades und der zu einem Abgasabführsystem gehörende Austrittsbereich stromabwärts des mindestens einen Laufrades angeordnet ist und sich an das mindestens eine Laufrad anschließt,
• – mindestens ein Abgas führender Strömungskanal vorgesehen ist, der den Eintrittsbereich via Laufrad mit dem Austrittsbereich verbindet.

The invention relates to a turbine with a turbine housing, in which at least one impeller mounted on a rotatable shaft is arranged, in which

• The turbine housing has an inlet region for supplying exhaust gas and an outlet region for discharging the exhaust gas, wherein the inlet region upstream of the at least one impeller and the outlet region belonging to an exhaust gas removal system is arranged downstream of the at least one impeller and adjoins the at least one impeller,
• - At least one exhaust gas leading flow channel is provided, which connects the inlet area via the impeller with the outlet region.

Internal combustion engines have a cylinder block and at least one cylinder head, which are interconnected to form the cylinder. As part of the charge exchange, the exhaust of the combustion gases via the outlet openings and the filling of the cylinder via the inlet openings takes place. In order to control the charge exchange, an internal combustion engine requires control devices, for example globe valves, and actuators for actuating the control members. The required for the movement of the valves valve actuating mechanism including the valves themselves is referred to as a valve train.

The exhaust pipes, which connect to the outlet openings of the cylinder, are at least partially integrated in the cylinder head according to the prior art and are combined into a single overall exhaust gas line or a plurality of total exhaust gas lines. The combination of exhaust pipes to an overall exhaust line is referred to as exhaust manifold.

Downstream of the at least one manifold, the exhaust gases are then frequently fed to a turbine, for example, the turbine of an exhaust gas turbocharger, and optionally passed through one or more exhaust aftertreatment systems.

According to the state of the art, turbines are dimensioned with a certain degree of certainty in order to avoid excessively high pressures in the inlet area.

Based on a maximum expected exhaust gas mass flow at a certain pressure and a certain temperature, the turbine is equipped with an approximately 10 to 15% larger flow cross-section than is theoretically required for the exhaust gas mass flow to be managed or would be necessary. The background of this measure is that the pressure in the inlet region of the turbine should not exceed a predefinable permissible pressure, for example, if the actual exhaust gas mass flow in the individual case exceeds the maximum expected exhaust gas mass flow and / or the exhaust gas pressure is temporarily and unplanned higher than the maximum expected exhaust gas pressure.

The exhaust pressure upstream of the at least one impeller may not be arbitrarily large, otherwise an exhaust valve could be opened against the spring force of the valve spring of the valve train, which forces the valve towards the valve closing position. To eliminate this danger by a stronger valve spring, is not effective, since it increases the friction of the valve train.

The provision of safety in the context of sizing brings a variety of disadvantages. The larger turbine used has a higher weight and is voluminous, which is why a higher space requirement. The at least one impeller is dimensioned correspondingly larger and has a greater inertia. This is another reason why the turbine has a poorer response. The main disadvantage, however, is the inferior efficiency of the larger turbine, which in operation is predominantly exposed to exhaust gas mass flows that are smaller than the exhaust gas mass flows that could actually be handled. Such a turbine has a very unsatisfactory operating behavior with small exhaust gas mass flows. Especially here the safety-related large design of the turbine makes adversely noticeable.

The above applies not only to turbines having a fixed fixed geometry, but also to turbines with variable turbine geometry. In turbines of the latter type, the provision of safety is taken into account by the fact that the maximum exhaust gas mass flow to be expected is managed at a certain pressure and a certain temperature with a flow cross section that is open to about 85 to 90%. In order to be able to counteract higher exhaust pressures than expected or to be able to cope with larger exhaust masses than expected, the variable turbine geometry can then be further adjusted, ie. H. the flow cross-section be opened even further. Against the background of the above, it is the object of the present invention to provide a turbine according to the preamble of claim 1, which is optimized with regard to the problem of excessive pressure in the inlet region of the turbine.

• – das Turbinengehäuse einen Eintrittsbereich zum Zuführen von Abgas und einen Austrittsbereich zum Abführen des Abgases aufweist, wobei der Eintrittsbereich stromaufwärts des mindestens einen Laufrades und der zu einem Abgasabführsystem gehörende Austrittsbereich stromabwärts des mindestens einen Laufrades angeordnet ist und sich an das mindestens eine Laufrad anschließt,
• – mindestens ein Abgas führender Strömungskanal vorgesehen ist, der den Eintrittsbereich via Laufrad mit dem Austrittsbereich verbindet, und die dadurch gekennzeichnet ist, dass
• – mindestens eine Überdruckleitung vorgesehen ist, die stromaufwärts des Austrittsbereichs von dem mindestens einen Abgas führenden Strömungskanal abzweigt und stromabwärts des mindestens einen Laufrades in das Abgasabführsystem mündet, wobei in der Überdruckleitung ein selbsttätig steuerndes Druckventil angeordnet ist.

This object is achieved by a turbine with a turbine housing in which at least one impeller mounted on a rotatable shaft is arranged, in which

• The turbine housing has an inlet region for supplying exhaust gas and an outlet region for discharging the exhaust gas, wherein the inlet region upstream of the at least one impeller and the outlet region belonging to an exhaust gas removal system is arranged downstream of the at least one impeller and adjoins the at least one impeller,
• - At least one exhaust gas leading flow channel is provided, which connects the inlet area via the impeller with the outlet region, and which is characterized in that
• - At least one pressure relief line is provided, which branches off upstream of the outlet region of the at least one exhaust gas flow channel leading downstream of the at least one impeller into the Abgasabführsystem, wherein in the overpressure line, an automatically controlling pressure valve is arranged.

According to the invention, at least one overpressure line is provided in the turbine housing. Each pressure relief line is equipped with an automatically controlled pressure valve, which opens without further action as soon as the pressure in the inlet area of the turbine exceeds a predeterminable pressure. This serves to avoid too high pressures in the inlet area.

As a result, the turbine no longer needs to be protected with certainty, i. H. no longer be designed larger than this is required for the exhaust gas mass flow to be handled. The elimination of this safety-related oversizing leads to a smaller turbine, which has a lower weight and is less bulky. The response also improves due to the lower inertia of the power tool. The efficiency of this smaller turbine is higher and in particular the performance at smaller exhaust gas mass flows is significantly improved.

In turbines with variable turbine geometry, the maximum expected exhaust gas mass flow of a certain pressure and a certain temperature is overcome when the flow cross section is completely open. At higher exhaust pressures, the geometry that is already fully opened will not be further opened. Rather, the pressure relief valve opens automatically as soon as the pressure in the inlet region of the turbine exceeds a predeterminable pressure.

Thus, the object underlying the invention is achieved, namely a turbine according to the preamble of claim 1 is provided, which is optimized in terms of the problem of excessive pressure in the inlet region of the turbine.

The pressure relief line according to the invention is not comparable in diameter to the bypass line of a waste gate turbine and the rapidly controlling pressure valve, which is almost or completely leak-free, is not comparable to the bypass valve, which is usually designed as a pivotable flap and mechanically operated becomes. The flap allows a not inconsiderable leakage flow even in the closed position.

In this context, embodiments are advantageous in which the at least one overpressure line has a maximum diameter d _max with d _max ≦ 5 mm, d _max ≦ 3 mm or with d _max ≦ 2 mm.

Embodiments may be advantageous in which the turbine is a double-flow turbine having an inlet region with two exhaust gas inlet openings and two flow channels carrying exhaust gas. The exhaust pipes of the internal combustion engine can be connected in groups with the twin-flow turbine in such a way that the merging of the exhaust gas streams - if any - takes place in the impeller or downstream of the turbine. If the exhaust pipes are grouped in such a way that the high pressures, in particular the Vorlassstöße, can be obtained, a double-flow turbine is particularly suitable for a burst charge, which also high turbine pressure ratios can be achieved at low speeds. The turbine can also have more than two floods and thus more than two exhaust-carrying flow channels.

Further advantageous embodiments of the turbine according to the subclaims are discussed below.

Embodiments of the turbine in which the at least one overpressure line opens downstream of the at least one impeller into the outlet region are advantageous. In the present case, the at least one overpressure line does not open at any point in the exhaust gas discharge system, but opens into the region which immediately adjoins the at least one impeller, namely the downstream exit region. This shortens the length of the overpressure line as far as possible.

Embodiments of the turbine in which at least one overpressure line branches off in the inlet region upstream of the at least one impeller from the flow channel carrying at least one exhaust gas are advantageous. In the entrance area, d. H. at the entrance to the at least one impeller, the highest exhaust pressures are expected. In this respect, it may be useful to pressurize the at least one pressure line or the associated pressure relief valve with the pressure present in the inlet region.

Embodiments of the turbine in which at least one overpressure line branches off in the at least one impeller from the flow channel leading at least one exhaust gas are also advantageous. In the present case, the overpressure line or the associated pressure valve opens when the pressure in the impeller region exceeds a presettable pressure. By opening the line, the pressure in the impeller breaks down, whereby the pressure in the inlet area is reduced.

Embodiments of the turbine are advantageous in which the pressure valve is arranged on the inlet side in the overpressure line. The provision of the valve at the inlet into the overpressure line has the advantage that the valve is placed at the point in the turbine housing at which an excessively high pressure is to be reliably prevented. The valve is directly pressurized with the pressure to be limited. In addition, the overpressure line is open on the inlet side only if too high a pressure is released. Otherwise, the inlet side is closed, so that no components of the exhaust gas can be deposited in order to clog the line.

But can also be advantageous embodiments of the turbine, in which the pressure valve is arranged on the outlet side in the overpressure line. This is suitable, for example, in cases in which there is insufficient space available for the valve on the inlet side, for example, in embodiments in which a pressure relief line in the impeller region branches off from a flow channel carrying exhaust gas.

In addition, embodiments of the turbine may be advantageous in which the pressure relief valve is arranged between the inlet in the overpressure line and the outlet from the overpressure line. This embodiment lends itself to built-modular housings in which the valve then in a designated pocket, d. H. Recess, is arranged.

Embodiments of the turbine in which the turbine housing has at least one coolant channel arranged in the turbine housing are advantageous, wherein this at least one coolant channel extends annularly around the shaft in the housing at least in sections.

The production costs of an uncooled turbine are comparatively high, since the material used for the thermally heavily loaded turbine housing - often nickel-containing material - is expensive, in particular in comparison to the material preferably used for the cylinder head; for example aluminum. Not only the material costs per se are comparatively high, but also the costs for the processing of these materials used for the turbine housing.

In order to use more cost-effective materials for the production of the turbine, it is advantageous to equip the turbine with a cooling, in particular with a liquid cooling, which greatly reduces the thermal load on the turbine or the turbine housing by the hot exhaust gases and thus the use of thermal less resilient materials possible.

If the housing is a casting, the at least one coolant channel can be formed as part of the casting process as an integrated coolant channel of a monolithic housing. In a modular housing, a cavity can be formed as part of the assembly, which serves as a coolant channel.

In the structural design of a cooled turbine, a compromise between cooling capacity and material is required, which is basically aimed at cooling the turbine only to the extent that actually requires the material used in order in this way the exhaust gas enthalpy of the hot exhaust gases, which significantly the exhaust gas temperature is determined to be able to use optimally.

Advantageous may be embodiments, therefore, in which the at least one coolant channel has a maximum diameter d _max where d _max ≤ 12mm, d _max ≤ 10mm, d _max ≤ 8mm, or with d _max ≤ 6 mm.

The smaller the maximum diameter of a coolant channel, the more difficult it becomes to form this coolant channel as part of a casting process as a channel integrated in the housing, which is completely surrounded by housing material, so that such coolant channels are preferably constructed. The coolant channel can be arranged in an existing joint, for example in a mounting flange surface receiving and forming a flange on the bearing housing facing side of the turbine housing, wherein the coolant channel is open to the mounting flange surface and is capped closed by the bearing housing in the assembled state.

A minimalistic cooling of the turbine housing is preferred in which the at least one coolant channel in a section along the shaft sweeps or covers a flow channel leading to exhaust gas only in a limited angular range α, for example with α ≦ 45 °, α ≦ 35 ° or α ≤ 25 °, and not coat-like as large as possible. The cooling capacity is deliberately limited by making the at least one coolant channel smaller. By this measure, the dissipated amount of heat advantageously reduced or limited.

Corresponding to the moderate cooling capacity is to choose a corresponding material for the production of the turbine, namely gray cast iron or steel casting or the like.

Embodiments of the turbine are advantageous in which the at least one overpressure line is formed as part of a casting process of the housing as an integrated channel of a monolithic housing. Such an integrated overpressure line is surrounded and shaped by the housing material and is therefore generally free of leakage, d. H. exhaust tight. The number of components is reduced by the integration of the pressure line into the housing and the installation of the turbine is simplified.

Embodiments of the turbine in which the at least one overpressure line is formed by drilling or another machining operation are advantageous. Such a positive pressure line is surrounded and molded by the housing material and is usually leak-free. The number of components is reduced by the integration of the pressure line into the housing and the installation of the turbine is simplified.

An integration of the overpressure line according to an above type also shortens the length of the overpressure line, whereby a pressure reduction in the inlet region is supported with open pressure line.

Embodiments of the turbine in which the at least one overpressure line is rectilinear are advantageous, as a result of which production, for example by means of drilling, is facilitated.

Embodiments of the turbine in which the at least one overpressure line is constructed from at least two rectilinear sections are also advantageous. Advantages arise with regard to production by means of drilling.

Advantageous embodiments of the turbine, in which at least two pressure lines are provided. The overpressure lines are comparatively small in size and can not be compared with the bypass line of a waste gate turbine, which is designed from the outset regularly for medium exhaust gas flows. If the pressure in the inlet region of the turbine clearly exceeds a predefinable pressure, more than one overpressure line may be required or advantageous for rapidly reducing the overpressure.

Embodiments of the turbine in which the turbine housing is a monolithically cast housing are advantageous. By casting and using appropriate cores, the complex structure of the housing can be formed in one operation, so that subsequently only a post-processing of the housing and the assembly are required to form the turbine.

But can also be advantageous embodiments of the turbine, in which the turbine housing is modular. Such an embodiment lends itself, for example, to liquid-cooled turbines with built-up coolant channels, in which a coolant channel can also be arranged in a joint or separation surface, for example in the mounting flange surface between the bearing housing and the turbine housing. A modular turbine housing is also suitable for building the at least one overpressure line.

Advantageous embodiments of the turbine, in which the turbine is equipped with a variable turbine geometry, which includes arranged in the inlet region of the turbine and adjustable vanes for influencing the flow direction.

The turbine is presently equipped with a variable turbine geometry, which allows a further adaptation to the respective operating point of an internal combustion engine by adjusting the turbine geometry or the effective turbine cross-section. In this case, adjustable guide vanes for influencing the flow direction are arranged in the inlet region of the turbine. Unlike the vanes of the rotating impeller, the vanes do not rotate with the shaft of the turbine.

If the turbine has a fixed invariable geometry, the vanes are not only stationary, but also completely immovable in the entry area, i. H. rigidly fixed. With a variable geometry, however, the vanes are indeed arranged stationary, but not completely immobile, but rotatable about its axis, so that the flow of the blades can be influenced. The turbine can in principle be executed without any guide.

The inventive provision of at least one positive pressure line proves to be particularly advantageous in turbines with variable turbine geometry, since these costly turbines are used with the intention of gaining energy efficiency-optimized energy under as many different operating conditions using variable geometry, so that a safety-related oversizing of the turbine due to their efficiency-detrimental effect is considered to be particularly counterproductive.

Advantageous are embodiments in which the turbine is a radial turbine, d. H. the flow of the blades takes place substantially radially. In this case, essentially radial means that the velocity component in the radial direction is greater than the axial velocity component. The velocity vector of the flow intersects the shaft of the turbine at a right angle if the flow is exactly radial. In this respect, the radial turbine can also be designed in the mixed-flow design, as long as the velocity component in the radial direction is greater than the velocity component in the axial direction.

In order to be able to flow radially to the rotor blades, the inlet region for supplying the exhaust gas is preferably designed as a spiral or worm casing running all around, so that the inflow of the exhaust gas to the turbine takes place essentially radially.

The turbine can also be designed as an axial turbine, in which the velocity component in the axial direction is greater than the velocity component in the radial direction.

Therefore, embodiments in which the turbine is an axial turbine are also advantageous.

Embodiments in which the turbine is the turbine of an exhaust-gas turbocharger are advantageous.

The charge is used primarily to increase the performance of the internal combustion engine. The air required for the combustion process is compressed, which allows each cylinder per working cycle, a larger air mass can be supplied. As a result, the fuel mass and thus the medium pressure can be increased.

The charge is a suitable means to increase the capacity of an internal combustion engine with unchanged displacement, or to reduce the displacement at the same power. In any case, the charging leads to an increase in space performance and a lower power mass. At the same vehicle boundary conditions, the load collective can thus be shifted to higher loads in which the specific fuel consumption is lower. Charging therefore supports the constant effort in the development of internal combustion engines to minimize fuel consumption, d. H. to improve the efficiency of the internal combustion engine.

Compared to a mechanical supercharger, the advantage of an exhaust gas turbocharger is that no mechanical connection is required for transmitting power between the supercharger and the internal combustion engine. While a mechanical supercharger obtains the energy required for its drive directly from the internal combustion engine, the exhaust gas turbocharger uses the exhaust gas energy of the hot exhaust gases.

For a turbocharger turbocharger in which the at least one turbine is subject to particularly high thermal loads due to the high exhaust gas temperatures, a liquid-cooled turbine according to the invention is particularly suitable.

A cylinder head of a supercharged internal combustion engine is thermally more heavily loaded than a conventional cylinder head and therefore places increased demands on the cooling, which is why it is advantageous to provide the cylinder head with at least one coolant jacket integrated in the cylinder head to form a liquid cooling.

In the following the invention is based on two embodiments according to the 1 and 2 described in more detail. Hereby shows:

1 a first embodiment of the turbine, partially cut along the shaft of the turbine runner, and

2 a second embodiment of the turbine, partially cut along the shaft of the turbine runner.

1 shows a first embodiment of the turbine 1 , partly along the shaft 4a of the turbine runner 4 cut.

The turbine 1 is a radial turbine 1a which is a turbine housing 2 and one in this turbine housing 2 arranged and on a rotatable shaft 4a stored impeller 4 includes. So that the exhaust the blades of the impeller 4 can flow radially, is the turbine housing 2 as around the wheel 4 running spiral housing formed, in which an exhaust gas leading flow channel 5 spiral around the wheel 4 extends.

The turbine housing 2 has an entrance area 6 for supplying exhaust gas and an exit area 7 for discharging the exhaust gas, wherein the inlet area 6 upstream of the impeller 4 is arranged. The to an exhaust gas removal system 8th belonging exit area 7 is downstream of the impeller 4 arranged and closes immediately to the impeller 4 at.

In the present case, it is a single-flow turbine 1 , wherein an exhaust gas leading flow channel 5 the entrance area 6 via impeller 4 with the exit area 7 combines.

There are two pressure lines 2 B . 2c provided, each in the entry area 6 upstream of the impeller 4 from the exhaust gas leading flow channel 5 branch off, downstream of the impeller 4 in the exit area 7 open and on the inlet side with an automatically controlling pressure valve 3 are equipped. The pressure lines 2 B . 2c are straight and drilled.

2 shows a second embodiment of the turbine 1 , partly along the shaft 4a of the turbine runner 4 cut. It should only the differences to the in 1 Otherwise, reference will be made to FIG 1 and the corresponding description. The same reference numerals have been used for the same components.

Unlike the in 1 illustrated embodiment branches the pressure lines 2 B . 2c at the in 2 illustrated turbine 1 in the wheel 4 from the exhaust gas leading flow channel 5 from. The pressure valves 3 are on the outlet side in the overpressure lines 2 B . 2c arranged, as inlet side of the impeller 4 not enough space for the valves 3 is available. By opening the lines 2 B . 2c the pressure builds up in the impeller 4 which also reduces the pressure in the inlet area 6 is reduced.

The pressure lines 2 B . 2c are composed of two rectilinear sections and also drilled. While the pressure lines 2 B . 2c according to 1 in the turbine housing 2 are arranged, the lines run 2 B . 2c corresponding 2 by the cassette-shaped receiving the variable turbine geometry and thus by the extended turbine housing so to speak 2 ,

LIST OF REFERENCE NUMBERS

1

 turbine

1a

 radial turbine

2

 turbine housing

2 B

 first overpressure line

2c

 second overpressure line

3

 automatically controlling pressure valve

4

 Wheel

4a

 wave

5

 Exhaust gas leading flow channel

6

 entry area

7

 exit area

8th

 Abgasabführsystem

Claims (14)

Turbine ( 1 ) with a turbine housing ( 2 ), in which at least one on a rotatable shaft ( 4a ) stored impeller ( 4 ) is arranged, in which - the turbine housing ( 2 ) an entrance area ( 6 ) for supplying exhaust gas and an exit region ( 7 ) for discharging the exhaust gas, wherein the entry area ( 6 ) upstream of the at least one impeller ( 4 ) and to an exhaust gas removal system ( 8th ) belonging exit area ( 7 ) downstream of the at least one impeller ( 4 ) is arranged and to the at least one impeller ( 4 ), - at least one exhaust gas leading flow channel ( 5 ) is provided, the the entry area ( 6 ) via impeller ( 4 ) with the exit area ( 7 ), characterized in that - at least one overpressure line ( 2 B . 2c ) is provided upstream of the exit region ( 7 ) of the at least one exhaust gas leading flow channel ( 5 ) branches off and downstream of the at least one impeller ( 4 ) into the exhaust gas removal system ( 8th ), wherein in the overpressure line ( 2 B . 2c ) an automatically controlling pressure valve ( 3 ) is arranged. Turbine ( 1 ) according to claim 1, characterized in that the at least one overpressure line ( 2 B . 2c ) downstream of the at least one impeller ( 4 ) in the exit area ( 7 ) opens. Turbine ( 1 ) according to claim 1 or 2, characterized in that at least one overpressure line ( 2 B . 2c ) in the entry area ( 6 ) upstream of the at least one impeller ( 4 ) of the at least one exhaust gas leading flow channel ( 5 ) branches off. Turbine ( 1 ) according to claim 1 or 2, characterized in that at least one overpressure line ( 2 B . 2c ) in the at least one impeller ( 4 ) of the at least one exhaust gas leading flow channel ( 5 ) branches off. Turbine ( 1 ) according to one of the preceding claims, characterized in that the pressure valve ( 3 ) on the inlet side in the overpressure line ( 2 B . 2c ) is arranged. Turbine ( 1 ) according to one of claims 1 to 4, characterized in that the pressure valve ( 3 ) on the outlet side in the overpressure line ( 2 B . 2c ) is arranged. Turbine ( 1 ) according to one of the preceding claims, characterized in that the turbine housing ( 2 ) for forming a cooling at least one in the turbine housing ( 2 ) arranged coolant channel, wherein this at least one coolant channel in the housing ( 2 ) at least in sections annularly around the shaft ( 4a ). Turbine ( 1 ) according to one of the preceding claims, characterized in that at least two overpressure lines ( 2 B . 2c ) are provided. Turbine ( 1 ) according to one of the preceding claims, characterized in that the turbine housing ( 2 ) a monolithically cast housing ( 2 ). Turbine ( 1 ) according to one of claims 1 to 8, characterized in that the turbine housing ( 2 ) is modular. Turbine ( 1 ) according to one of the preceding claims, characterized in that the turbine ( 1 ) is equipped with a variable turbine geometry, which in the inlet area ( 6 ) of the turbine ( 1 ) and adjustable guide vanes for influencing the flow direction comprises. Turbine ( 1 ) according to one of the preceding claims, characterized in that the turbine ( 1 ) a radial turbine ( 1a ). Turbine ( 1 ) according to one of claims 1 to 11, characterized in that the turbine ( 1 ) is an axial turbine. Turbine ( 1 ) according to one of the preceding claims, characterized in that the turbine ( 1 ) the turbine ( 1 ) is an exhaust gas turbocharger.

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