JP2013542372A - Insert parts for turbines for exhaust gas turbocharger, exhaust gas turbocharger, exhaust gas turbocharger - Google Patents

Abstract

The present invention relates to an insert (36, 36 ^I , 36 ^II ) for the turbine (12) of an exhaust gas turbocharger (10, 10 ^I , 10 ^II , 10 ^III , 10 ^IV , 10 ^V , 10 ^VI , 10 ^VI ). 36 ^III , 36 ^IV , 36 ^V , 36 ^VI ), which can be inserted at least partly into the housing (14) of the turbine (12) and circumferentially at least partly in the circumferential direction of the insert part. Expanded in the direction (48) and provided with at least one helical passage (38, 40, 42, 44) through which exhaust gas flowing through the turbine (12) can flow and the insert (36 , 36 ^I , 36 ^II , 36 ^III , 36 ^IV , 36 ^V , 36 ^VI ) at least partially open in the axial direction (49) on at least one end face (82, 84) .
[Selection] Figure 1

Description

  The invention relates to an insert for an exhaust gas turbocharger according to claim 1, an exhaust gas turbocharger for an internal combustion engine according to claim 4, an exhaust gas of the type specified in the preceding paragraph of claim 7. A turbine for a turbocharger, an exhaust gas turbocharger according to claim 8, and an exhaust gas turbocharger of the type specified in the preceding paragraph of claim 9.

  Patent document 1 discloses a spiral housing for a turbomachine, specifically an exhaust gas turbocharger having an at least partially adjustable cross section, which is slidably guided to the radial inner wall of the spiral housing. It has at least one tongue that can be moved circumferentially relative to this wall.

  Patent Document 2 is known for the disclosure of an internal combustion engine for a vehicle composed of a gas turbocharger. The exhaust gas turbocharger includes a compressor in an intake system of an internal combustion engine and a turbine in an exhaust gas device of the internal combustion engine, and the turbine includes a turbine housing and a turbine wheel including a spiral passage connected to an exhaust gas line of the exhaust gas device. have. The turbine wheel is arranged in the turbine wheel housing space and is connected to the helical passage for the purpose of driving the compressor wheel of a compressor connected via a shaft in a manner fixed to the turbine wheel. Can be moved by engine engine exhaust gas. The turbine comprises an actuating device in which the spiral inlet cross section of the spiral passage and the nozzle cross section of the spiral passage can be adjusted together in the receiving space.

West German Patent No. 2539711 German Patent Application No. 102008039085A1

  There is a further possibility of reducing the production costs of known exhaust gas turbochargers.

Accordingly, it is an object of the present invention to provide an exhaust gas turbocharger turbine, an exhaust gas turbocharger of an internal combustion engine, and a turbine insert for an exhaust gas turbocharger, resulting in the manufacturing cost of the exhaust gas turbocharger. Is reduced.

  This object is achieved by using an exhaust gas turbocharger turbine insert with the features of claim 1 and using an exhaust gas turbocharger for an internal combustion engine with the features of claim 4. Using an exhaust gas turbocharger turbine having the characteristics of claim 8, and using an exhaust gas turbocharger turbine having the characteristics of claim 9. . Advantageous embodiments including preferred significant improvements of the invention are specified in the claims.

  The first aspect of the present invention relates to an insert for an exhaust gas turbocharger, which is at least partially, in particular completely, insertable into a turbine housing, at least one helical passage. Is provided, which allows the exhaust gas to flow through the turbine through at least a portion of the circumference in the circumferential direction of the insert. In the axial direction of the insert part and the turbine, the spiral passage is designed to be opened at least partly on at least one end face of the insert part.

  The insert can be produced particularly quickly and inexpensively, in particular by the open design of the spiral passage. For example, the insert part is manufactured as a turning part and / or a milled part. That is, it is produced by turning and / or milling or by other production processes, in particular by cutting. The insert part can also be designed as an investment casting part using an investment casting process. The insert part can also be manufactured through a manufacturing process, which will be described later, by a combination of manufacturing processes. The open design of the spiral passage eliminates the need for expensive and costly casting processes such as a lost core. This makes it possible to keep the production costs of the insert parts and thus the turbine low, and thus advantageously achieve a particularly low production cost of the exhaust gas turbocharger.

  One advantageous embodiment of the invention is that the spiral passage is designed to open completely in the circumferential direction on at least one end face of the insert part and thus in the circumferential direction of the turbine. This enables a particularly quick and inexpensive production of the insert part, so that the production costs of the exhaust gas turbocharger can be kept low. In the production of automobile series, the exhaust gas turbocharger needs to produce a particularly large number of parts. Low manufacturing costs are made possible by the insert according to the invention, with the economic effect of reducing the cost of the vehicle being particularly advantageous.

  The insert according to the invention is also capable of a particularly advantageous induction of the exhaust gas flowing through the turbine, which is designed at the turbine wheel of the turbine, for example as a radial turbine, at least essentially in the assembled state of the exhaust gas turbocharger. In the radial direction of the circular insert, it is guided inside the insert. The spiral passage has an outlet opening through which the spiral passage opens in the radial direction of the insert inside the insert and the turbine wheel is actuated by exhaust gas flowing through the spiral passage. That is, the spiral passage guides the exhaust gas to flow toward the turbine wheel at least essentially in the radial direction of the insert or turbine wheel, thus allowing the latter to be driven.

One advantageous embodiment of the first aspect of the present invention is that the insert has at least one further spiral passage, which extends in the circumferential direction of the insert over at least a portion of the periphery and is therefore a turbine. In which the exhaust gas flowing therethrough is possible, and the further helical passage is designed to open partially in the axial direction of at least one end face of the insert. This means that the insert can be manufactured particularly quickly and inexpensively, even if it has many helical passages, provided with at least two, or more than three. An insert with a number of helical passages allows a favorable flow to the turbine wheel, whereby the turbine can be operated particularly effectively. Due to the favorable flow conditions as far as the turbine wheel is concerned, the effective operation of the turbine has a very beneficial effect in that it increases the overall efficiency of the exhaust gas turbocharger and is loaded using the exhaust gas turbocharger. The fuel consumption and CO ₂ emission of the internal combustion engine allocated to the exhaust gas turbocharger to be controlled are suppressed.

  It should be noted at this point that the insert can also be used as an exhaust gas turbocharger for other fluid energy machines, specifically an internal combustion engine for a supercharger. According to the invention, the insert can be used as a supercharger, for example as a turbocharger for turbo engines or a supercharger for fuel cells. In this case, the exhaust gas exiting the fuel cell flows through the turbine, and the exhaust gas exiting the fuel cell is directed to the turbine wheel by a particularly preferred method using inserts according to the present invention.

  According to the invention, if the insert part has many helical passages, they are arranged, for example, on the back side of each other in the circumferential direction of the insert part and / or in the axial direction of the same height. It is also possible for the helical passages to be arranged side by side in the axial direction of the insert part and / or circumferentially at the same height. The corresponding arrangement of the spiral passages is here adapted to the use of the turbine and the corresponding conditions selected accordingly.

  A second aspect of the present invention relates to an exhaust gas turbocharger for an internal combustion engine, which comprises a turbine and at least one insert, in particular according to the invention, at least partially within the turbine housing of the turbine. Including the inserted parts. The insert has at least one spiral passage that extends in at least a portion of the circumference in the circumferential direction of the insert and allows exhaust gas flowing through the turbine to flow therethrough, the spiral passage of the insert being At least one end face portion is designed to be at least partially opened in the axial direction of the exhaust gas turbocharger. Advantageous embodiments of the first aspect of the invention are regarded as advantageous embodiments of the second aspect of the invention and vice versa. As already mentioned in connection with the first aspect of the present invention, in particular, the open design of the spiral passage allows the insert part to be manufactured particularly inexpensively, which means that the entire turbine, ie the exhaust gas turbocharger, can be manufactured. It has a positive effect in terms of reducing manufacturing costs.

  In an advantageous embodiment of the second aspect of the invention, the spiral passage is at least partly in the axial direction of the exhaust gas turbocharger at one end face of the insert part, facing the outlet of the exhaust gas turbocharger. The exhaust gas turbocharger has a bearing housing that supports the rotor of the exhaust gas turbocharger, and the spiral passage faces the bearing housing at one end face of the insert. The exhaust gas turbocharger is designed to be at least partially opened in the axial direction. Through the at least one helical passage, the insert part here allows a particularly favorable induction of the exhaust gas to the turbine wheel of the turbine of the exhaust gas turbocharger, whereby the entire exhaust gas turbocharger operates particularly efficiently. At the same time, the insert parts are manufactured particularly inexpensively.

  The insert part in the second aspect of the invention is, for example, a turning part and / or a milling part, i.e. by turning and / or milling, or by other, in particular a manufacturing process with cutting, and / or It is also designed as a part manufactured through the investment casting process. The insert in the second aspect of the invention can be manufactured by a combination of the described manufacturing processes or by a combination of other manufacturing processes.

  The inserts in both the first and second aspects of the present invention can both be designed as sheet metal parts consisting of many parts of sheet metal that are otherwise welded and / or connected or joined together.

  In order to be able to cover at least one spiral passage or a number of spiral passages and thus to direct the exhaust gas to the turbine wheel in a preferred way, the insert part in the second aspect of the invention is for example an exhaust gas Arranged against a further part of the turbocharger. The insert part abuts the part and the part covers the open designed area of the spiral passage, for example using a wall. The component is, for example, a turbine housing.

  In order to avoid leaks that reduce efficiency, it is advantageous to apply force to keep the insert part abutting and thus in contact with the part covering the opening of the spiral passage. For this purpose, the insert part is supported indirectly, for example on a bearing housing, so that the insert part is held against the part by applying a force or the part applies a force. Thus, it is held in contact with the inserted part.

  A spring element, in particular a disc spring, is advantageously provided by the insertion part being supported on the bearing housing. Here, the bearing housing can be supported at least partly, at least indirectly, on the insert part or part of the turbine housing and / or part thereof.

  In a further embodiment of the invention, at least one lid element is provided to at least partially cover the area of the spiral passage that is designed to open the spiral passage. The region of the spiral passage that is designed to open is advantageously completely covered by the lid element, so that the exhaust gas can be directed to the turbine wheel in a particularly preferred manner.

  The lid element is advantageous in that it can have a simple and at least overwhelmingly flat structure for partially covering the helical passage, in particular when compared to the turbine housing and the insert part. With this simple construction, especially when the lid element is designed at least partially flat, the lid will at least essentially change its shape under the possibility of temperature stress changes during operation of the exhaust gas turbocharger. Loss uniformly. As a result, leaks that reduce the efficiency with which exhaust gases can flow out of the spiral passage are at least essentially avoided or similar leaks are very small. Here, it is advantageous if the lid element is held on the insertion part at least indirectly, in an airtight manner, in particular in an airtight manner, through the application of force. For this purpose, it is possible, for example, to support a lid element on one of the insert parts and on one side of the bearing housing. Here, it is also possible to use at least one spring element, with the lid element being subjected to a force on the insertion part, in particular being held firmly on it.

  A further embodiment of reducing the manufacturing costs of the exhaust gas turbocharger in the second aspect of the invention is designed as a separate element from the turbine housing and inserted into the turbine housing in the part of the exhaust gas turbocharger assembly, For insert parts. This means that the turbocharger can be assembled quickly and inexpensively.

  A third aspect of the present invention relates to a turbine for an exhaust gas turbocharger comprising a turbine housing having a receiving space for receiving a turbine wheel, which is capable of flowing at least one exhaust gas flowing through the turbine. In a spiral passage having a spiral passage and extending in the circumferential direction of the receiving space over at least a part of its circumference and having at least one inlet for allowing exhaust gas to flow into the spiral passage, Can be guided into the receiving space via a spiral passage.

  According to the invention, at least one passage is provided by dividing at least one spiral passage downstream of the inlet into at least two spiral passages. The advantageous embodiment of the first two aspects is regarded as the advantageous embodiment of the second aspect and vice versa. That is, at least two spiral passage portions are formed through the passage portion, and exhaust gas is supplied to the spiral passage portions through the common spiral passage during operation of the turbine.

  The flow of the exhaust gas passing through the spiral passage is divided into the flow of each part by the spiral passage portion, so that the exhaust gas can flow particularly favorably toward the turbine wheel housed in the housing space, the latter being Therefore, it is driven. This allows a particularly efficient and preferred turbine operation. This also reduces manufacturing complexity and manufacturing costs for the entire turbine and exhaust gas turbocharger.

  The passage part of the third aspect of the invention is designed, for example, as an insert part and thus as an element separated at least partially, in particular completely, from the turbine housing housed in the turbine housing Has been. This enables a particularly inexpensive production of the passage section and the entire turbine. The passage part is produced here, for example, as a turning part and / or a milling part, ie by turning and / or milling, or by other production processes, in particular by cutting. The passage can also be designed as an insert that is manufactured using an investment casting process. In the first two aspects of the invention, it is equally possible for the channel part to be designed as a combination of manufacturing processes and / or as an insert part manufactured through the described manufacturing process.

  As a further embodiment of the third aspect of the present invention, the passage is designed to be integrated with the turbine housing. The passage is, for example, milled here in the turbine housing. To produce a turbine housing and a passage integrated therewith, a rough contour of the passage that is cast, for example by sand casting, and a passage that is formed using mechanical processing, for example milling, Specifically, an accurate final contour of the spiral passage portion is created.

  Like the inserts of the first two aspects of the invention, the passage part of the third aspect of the invention can have a number of, ie at least two, or more than three helical passages, for example Circumferentially disposed in the circumferential direction of the passage part back to back over the circumference, or axially at the same height, circumferentially at the same height, and / or axially next to each other. Corresponding arrangements must also be compatible with the third aspect of the invention and the appropriately selected conditions of use of the turbine.

  In a further embodiment of the third aspect of the invention, the at least one helical passage part of the passage part, specifically designed as an insert part, is at least one end face of the passage part, at least in the axial direction of the turbine. Designed partially open. This means that the passage part can be manufactured particularly cheaply, in particular when the spiral passage part is designed to be fully open in the circumferential direction of the passage part.

  The region of the spiral passage portion of the passage portion in the third aspect of the present invention opens, for example, in the direction of blowout of the turbine or in the direction of the bearing housing of the exhaust gas turbocharger including the turbine of the third aspect of the present invention. Is designed to be.

  The spiral passage portion of the passage portion according to the third aspect of the present invention specifically surrounds the circumference in the axial direction of the turbine at both end face portions in the circumferential direction when the latter is designed as an insertion part. It is possible as well. This, on the one hand, allows a particularly favorable guidance to the exhaust gas containment space, and on the other hand, the passage, specifically designed as an insert, is easily and quickly incorporated at least partially into the turbine housing. As a result, it allows a particularly quick and inexpensive assembly and thus the production of an exhaust gas turbocharger turbine.

  A fourth aspect of the present invention relating to an exhaust gas turbocharger with a turbine according to the third aspect of the present invention is that the exhaust gas turbocharger or the turbine, specifically in the axial direction, the housing portion of the exhaust gas turbocharger, specifically Is formed with an internal space between the bearing housing and the passage part, in particular partially in the axial direction and at least partly delimited from the passage part, and is fluidly connected to at least one helical passage. Yes. The first three advantageous embodiments of the invention are regarded as advantageous aspects of the fourth aspect of the invention and vice versa. By fluid connection is meant at least essentially equal pressure flowing through the helical passage and the interior space. This pressure can act on the wall of the channel part, in particular essentially in the axial direction, the wall being delimited on the one hand from the interior space and on the other hand from the at least one helical channel part. On the side of the spiral passage section delimited from this wall, pressure flows in the individual spiral passage sections, specifically a static pressure that is lower than the internal space or specifically the static pressure of at least one spiral passage. A pressure lower than the space side acts.

  As a result of this pressure difference described above, a force is applied to the corresponding, in particular at least essentially the axially acting passage. The application of this force applies force to the passage part designed specifically as an insert part for further parts of the exhaust gas turbocharger and at least indirectly through the application of the force to the passage part on the part. Can be used to hold.

  This application of force can be used to hold the passage part on the corresponding part if at least one spiral passage part of the at least one end face part is designed to be at least partially opened. The part can open and tightly cover that area of the designed spiral passage. As a result, leakage that reduces efficiency from where the exhaust gas flows out of the opening in the spiral passage is at least essentially avoided.

  In the second and third aspects of the invention, the internal space is further due to the corresponding internal space provided by the fourth aspect of the invention provided between the insert part and the housing part of the turbine or exhaust gas turbocharger. It is also possible to connect at the fluid surface at the spiral passage, in particular at the feed part, so that a higher pressure flows in the interior space than inside the at least one spiral passage formed by the insert part. Thus, in order to hermetically cover the region of at least the essential spiral passage formed by the insert designed to be opened and designed in the manner described in connection with the fourth aspect of the present invention, It can be held in the same way through the application of force to a part, for example a lid element, or a housing part, for example a turbine housing.

  A fifth aspect of the present invention relates to a turbine for an exhaust gas turbocharger having a turbine housing having at least one helical passage and a receiving space in which a turbine wheel is received for rotation. The turbine wheel is actuated by exhaust gas via a spiral passage, and the turbine has an actuating device in which the spiral inlet cross section and / or the nozzle cross section of the at least one spiral passage can be adjusted to the receiving space.

According to the invention, in a fifth aspect of the invention, an actuating device having at least two meshing devices is provided for the purpose of adjusting the spiral inlet cross section and / or the nozzle cross section. The advantageous embodiments in the first four aspects of the invention are considered the opposite advantageous embodiments of the fifth aspect of the invention. Adjustment of the spiral inlet cross section and / or nozzle cross section via the meshing device allows adjustment of a particularly large width, in particular the angular range, and the spiral inlet cross section and / or nozzle cross section can be adjusted in various ways It is. This allows a particularly high throughput spread of the various turbines in the fifth aspect of the invention, so that the turbine is particularly efficient at the numerous operating points of the internal combustion engine assigned to the exhaust gas turbocharger. It is possible to adapt. This leads to a particularly efficient operation of the turbine, at least substantially in the overall feature map of the internal combustion engine, the latter being operated particularly efficiently to reduce fuel requirements and CO ₂ emissions.

  The meshing device advantageously placed in the turbine housing, in particular its adjustment function, reduces the space requirements of the turbine and solves packaging problems, especially in areas such as engine rooms where space is important Or help to avoid.

  In order to adjust the helical cross section and / or the nozzle cross section, the actuator has at least one assigned blocking element, such as a tongue that can be moved in the circumferential direction of the receiving space or turbine wheel.

  A further advantage of the meshing device is that harmonic transmission between the adjusting member for moving the shut-off device and the shut-off device itself can be achieved over the adjusting range.

  For example, the adjusting device is arranged on an adjusting ring arranged in the turbine housing so as to be able to rotate on the rotating shaft via the meshing device and the adjusting member. As the ring rotates, the blocking element moves so that the spiral inlet cross section and / or the nozzle cross section can be adjusted differently, i.e. larger or smaller.

  In an advantageous embodiment of the invention, one meshing device is fed onto the adjusting ring of the actuating device and the other meshing device is connected to the adjusting shaft of the actuating device in a rotationally fixed manner. Provided to allow rotation on the shaft. Here, the adjustment ring is connected to the adjustment member via an adjustment shaft. The adjustment member is, for example, an electric motor having an output shaft that can rotate around a rotation shaft in order to move the shut-off device. Due to the rotation of the output shaft of the electric motor, the adjusting shaft rotates and thus moves to the shut-off device, so that the adjusting shaft is here connected to or formed by the output shaft.

  Further advantages, features and details of the invention can be seen by referring to the following description of preferred exemplary embodiments and the drawings. The features and combinations of features described in the above description, and the features and feature combinations described in the following figure descriptions and / or drawings only can only be used in the combinations specified in each case. And can be used in other combinations or as such, without departing from the scope of the present invention.

1 is a schematic partial longitudinal sectional view of an exhaust gas turbocharger of an internal combustion engine having a turbine with a turbine housing into which an insert having a plurality of segments is inserted. FIG. FIG. 2 is a schematic perspective view of an insert having multiple segments of the turbine of FIG. 1. It is a schematic sectional drawing of the turbine of the exhaust gas turbocharger of FIG. FIG. 2 is a schematic partial longitudinal sectional view of a further embodiment of the exhaust gas turbocharger of FIG. 1. FIG. 5 is a schematic perspective view of an insert having multiple segments of the turbine of the exhaust gas turbocharger of FIG. 4. It is a schematic sectional drawing of the turbine of the exhaust gas turbocharger of FIG. FIG. 5 is a schematic partial longitudinal sectional view of a further embodiment of the exhaust gas turbocharger of FIGS. 1 and 4. FIG. 8 is a schematic partial longitudinal sectional view of a further embodiment of the exhaust gas turbocharger of FIG. 7. FIG. 9 is a schematic partial longitudinal sectional view of a further embodiment of the exhaust gas turbocharger of FIGS. 7 and 8. 10 is a schematic partial longitudinal sectional view of a further embodiment of the exhaust gas turbocharger of FIGS. FIG. 11 is a schematic partial longitudinal sectional view of a further embodiment of the exhaust gas turbocharger of FIGS. 7 to 10. FIG. 6 is a schematic partial longitudinal sectional view of a further embodiment of an exhaust gas turbocharger. FIG. 13 is a schematic partial front view of the exhaust gas turbocharger of FIG. 12.

  In the figures, the same reference numbers refer to at least functionally identical elements, parts and / or the like.

  FIG. 1 shows an exhaust gas turbocharger 10 having a turbine 12 consisting of a turbine housing 14 and a bearing housing 16. Through the turbine housing 14, the accommodation space 18 is formed where the turbine wheel 20 of the rotor 22 of the exhaust gas turbocharger 10 is accommodated so that it can rotate. The rotor 22 also includes a shaft 24 to which the turbine wheel 20 is connected in a relatively non-rotatable manner.

  The exhaust gas turbocharger 10 also includes a compressor not shown in FIG. 1 and includes a compressor housing, through which the receiving space is formed while the compressor wheel of the rotor 22 is received. The compressor wheel is also connected to the shaft 24 so as not to rotate relative to the compressor wheel so that the compressor wheel is driven through the shaft 24 and the turbine wheel 20. The rotor 22 is supported in the bearing housing 16 and can rotate about the rotation shaft 26.

  Through the turbine housing 14, the helical passage 28 is formed as a part that functions as a supply port. In the spiral passage 28, the exhaust gas can flow into the internal combustion engine assigned to the exhaust gas turbocharger 10 in the direction of arrow 32 via the inlet 30 of the spiral passage 28. The exhaust gas then flows through the spiral passage 28 in the direction of the arrow 34.

  An insert 36 having a plurality of segments shown in perspective and schematically in FIG. 2 is disposed within the turbine housing 14 through which the helical passage 28 is formed using a portion of the wall 68. According to FIGS. 1 to 3, the insert 36 having a plurality of segments of the exhaust gas turbocharger 10 is separated from the turbine housing 14, and the plurality of segments are partially in the direction of the arrow 46 over the circumferential direction of the insert 36 having the plurality of segments. Designed as an insert with four helical passages 38, 40, 42, 44 expanded in the circumferential direction of the insert 36 having The spiral passages 38, 40, 42, 44 are arranged at the same height, back to back in the circumferential direction and in the axial direction of the insert 36 having a plurality of segments, and thus in the direction of the arrow 49 of the exhaust gas turbocharger.

  As can be seen in particular in FIG. 3, the supply opening in the direction of the arrow 48 of the spiral passage 28 extending in the circumferential direction of the receiving space 18 extends at least partly around the circumference of the receiving space 18 of the turbine wheel 20. This function is divided into spiral passages 38, 40, 42, 44 by an insert 36 having a plurality of segments downstream of the inlet 30. The spiral passages 38, 40, 42, 44 are fluidly connected to the spiral passage 28, so that the spiral passages 38, 40, 42, 44 are commonly supplied with exhaust gas from the spiral passage 28. As a result, exhaust gas flows into the turbine wheel 20 and operates in a particularly preferred manner, at least essentially in the radial direction, and the exhaust gas turbocharger 10 operates particularly efficiently and advantageously.

  For this purpose, the spiral passages 38, 40, 42, 44 have outlets 50, 51, 52, 53, respectively, through which the spiral passages 38, 40, 42, 44 are formed in the receiving space 18. Through which the exhaust gas flows into the turbine wheel 20 in the radial direction of the insert 36 having at least essentially multiple segments in the direction of the turbine wheel 20 and the arrow 54. Turbine 12 is thus a radial turbine.

The exhaust gas turbocharger 10 also has an actuating device 56 with respective tongues 58, 60, 62, 64 assigned to the helical passages 38, 40, 42, 44 or corresponding outlets 50, 51, 52, 53. . The tongues 58, 60, 62, 64 are connected to an adjustment ring 66 that rotates about the rotation shaft 26. The rotation of the adjustment ring 66, also referred to as a tong diverter, produces an adjustment, specifically a circumferential displacement indicated by the arrows 48 of the tongs 58, 60, 62, 64. Through this movement or replacement of the tongue 58, 60, 62, 64, overview of the spiral inlet cross section _{A S} (FIG. 3 spiral passages 38, 40, 42, 44, through the spiral inlet cross section _{A S} of the spiral passageway 38, and are) and / or displaying on behalf of all spiral inlet cross section _{a S} of the spiral inlet cross section 38, 40, 42, 44, the nozzle cross section _{a R} of the spiral passageway 38, 40, 42, 44 (in FIG. 3 overview, only through the nozzle cross section _{a R} of the spiral passageway 38, are representatively shown nozzle cross section _{a R} of the spiral passageway 38, 40, 42, 44) can be variously adjusted.

  1 and 3, in the insert 36 having multiple segments of the exhaust gas turbocharger 10, the walls 70 and 72 delimit and seal the ends of the spiral passages 38, 40, 42, 44. Leakage between the corresponding exhaust of the exhaust gas exiting between 42, 44, ie one of the spiral passages 38, 40, 42, 44, into another spiral passage 38, 40, 42, 44 is avoided. As a result, the exhaust gas can be particularly preferably guided from the receiving space 18 to the turbine wheel 20 and the exhaust gas turbocharger 10 exhibits a particularly high level of efficiency.

  The insert 36 having multiple segments can be designed integrally through, for example, an investment casting process. Similarly, the insert 36 having a plurality of segments can be designed as a sheet metal part consisting of a number of sheet metals, for example forming walls 68, 70, 72 and welded together.

  Through the four spiral passages 38, 40, 42, 44, four segments are formed, through which exhaust gas flows, through which the exhaust gas is directed to the turbine wheel 20. Of course, an insert 36 having multiple segments can also have more or fewer helical passages or segments.

  As specifically shown in FIG. 1, the insert 36 having multiple segments is axially retained in the turbine housing 14 by the bearing housing 16 as indicated by arrow 49. For this purpose, a multi-segment insert 36 is supported on the bearing housing 16 via each contact surface 74 and the bearing housing 16 is connected to the turbine housing 14 by means of screws, for example. On the other hand, the insert 36 having segments is supported on the turbine housing 14 via respective contact surfaces 76. As a result, the bearing housing 16 presses the insert 36 having a plurality of segments in the axial direction against the turbine housing 14 as indicated by the arrow 49 in the direction of the turbine outlet 78 in the direction of the arrow 80, and the insert having the plurality of segments. 36 is held in the axial direction. As a result, the insert 36 having multiple segments is pressed into the turbine housing 14.

In accordance with FIGS. 1 through 3 above, FIGS. 4 through 6 show an alternative embodiment of the exhaust gas turbocharger 10, indicated by 10 ^I. In the turbine housing 14 of the turbine 12 of the exhaust gas turbocharger 10 ^I is provided an insert 36 ^I having a plurality of segments different from the insert 36 having a plurality of segments according to FIGS. That is, the spiral passageway 38, 40, 42, 44 of the insert 36 ^I having a plurality segments, in the circumferential direction indicated by arrow 48, as indicated by the arrow 49 of the end surface portion 82 of the insert 36 ^I having a multisegment In addition, it is designed to be completely opened over its circumference in its axial direction. In the relationship of FIG. 4, the open end face 82 points in the direction of the turbine outlet 78.

If the insert 36 ^I with multiple segments allows the assembly and manufacture of the exhaust gas turbocharger 10 in a particularly simple and inexpensive manner and allows its operation particularly efficiently, the insert 36 ^I with multiple segments itself is a spiral passage. The open designs 38, 40, 42, 44 of this are particularly inexpensive to produce. The insert 36 ^I with multiple segments is manufactured, for example, as a turning part and / or a milling part, through an investment casting process or specifically through a combination of the described manufacturing processes.

To avoid leaks that reduce efficiency, thereby avoiding exhaust gases from any one of the spiral passages 38, 40, 42, 44 to flow into the other spiral passages 38, 40, 42, 44. The insert 36 ^I with segments is held at its end 82 against the turbine housing 14 by the bearing housing 16, so that the turbine housing 14 passes through the helical passages 38, 40, 42, 44 of the insert 36 ^I with multiple segments. Cover completely and tightly in the corresponding area of the wall 86 of the turbine housing 14.

As indicated by the arrow 49, the multi-segment insert 36 ^I is placed on the bearing housing 16 in order to axially hold the multi-segment insert 36 ^I on the turbine housing 14 and apply a force to the turbine housing 14. It is supported via a disk spring 75. The bearing housing 16 is here supported in part not only via the disc spring 75 of the insert 36 ^I with multiple segments but also via a part of the turbine housing 14. This is because the insert 36 ^I with multiple segments is held under the spring force by the disc spring 75 against the turbine housing 14, in particular in the direction of the arrow 80, and is held on the latter, thus leaking. Is at least essentially avoided. As a result, the insert 36 ^I having multiple segments is pressed into the turbine housing 14.

The description relating to the exhaust gas turbocharger 10 and the multi-segment insert 36 with respect to FIGS. 1 to 3 is otherwise the same as the exhaust gas turbocharger 10 ^I and the multi-segment insert 36 ^I according to FIGS. Applied.

FIG. 7 shows a further alternative embodiment of the exhaust gas turbochargers 10 and 10 ^I designed as 10 ^II . In the turbine housing 14 of the turbine 12 of the exhaust gas turbocharger 10 ^II , an insert 36 ^II having a plurality of segments different from the insert 36 having a plurality of segments is accommodated, and there is no end wall 72. As a result, the spiral passageway 38, 40, 42, 44, according to arrow 48, the end face 84 of the insert 36 ^II having a plurality segments of the circumferential direction and the direction of the arrow 49, the insert 36 ^II or with multiple segments The exhaust gas turbocharger 10 ^II is designed to be completely open over the circumference in the axial direction. From the relationship of FIG. 5, it can be seen that the end surface portion 84 is disposed opposite to the end surface portion 82 in the axial direction. FIG. 7 shows the open end 84 of the multi-segment insert 36 ^II thus facing the bearing housing 16.

The exhaust gas turbocharger 10 ^II is disposed in the turbine housing 14 to completely and at least essentially cover the spiral passages 38, 40, 42, 44 of the insert 36 ^II having multiple segments against the end face 84. It has a lid 86 similar to the one. The lid 86 has a flat wall 89 that is used to completely cover the helical passages 38, 40, 42, 44 in the circumferential direction. For this purpose, the lid 86 is supported on the insert 36 ^II having a plurality segments via the respective contact surfaces 74 ^II, it abuts against the insert 36 ^II having a plurality segments. The insert 36 ^II and the lid 86 having a plurality of segments are held in the axial direction by the bearing housing 16 that abuts the lid 86 via the respective contact surfaces 74 ^I. That is, the bearing housing 16, by using the lid 86, abut against the insert 36 ^II having a plurality segments, then insert 36 ^II having a plurality segments, in contact with the turbine housing 14 via the contact surface 76, where support It has been. Through this chain of supports, the lid 86 is energized using the bearing housing 16 on the insert 36 ^II having a plurality of segments in the direction of the arrow 80, so that the helical passage 38 of the insert 36 ^II having a plurality of segments is obtained. , 40, 42, 44 are at least essentially avoided. As a result, the insert 36 ^II having a plurality of segments is similarly pressed through the lid 86, and the lid 86 is pressed into the turbine housing 14. As in the case of the exhaust gas turbochargers 10 and 10 ^I according to FIGS. 1 to 6 described above, the exhaust gas turbocharger 10 ^II according to FIG. 7 is also operated as a result of the force applied to the insert 36 ^I having a plurality of segments. In order to avoid leakage and ensure a favorable outflow to the turbine wheel 20, for example, the helical passage 38 against the turbine housing 14 or lid 86 being forced against the insert 36 ^II having multiple segments. , 40, 42, 44 are guaranteed to be at least essentially always hermetically covered.

FIG. 8 shows an alternative embodiment of the turbochargers 10, 10 ^I , 10 ^II from the previous figure, designated by the reference numeral 10 ^III . The exhaust gas turbocharger 10 ^III has a passage portion 37, and specifically, the spiral passages 38, 40, 42, 44 are designed in the same manner as the inserts 36, 36 ^I , 36 ^II having a plurality of segments. Unlike the inserts 36, 36 ^I , 36 ^II having a plurality of segments, the passage portion 37 is designed to be integrated with the turbine housing 14 of the turbine 12 of the exhaust gas turbocharger 10 ^III . The passage portion 37 is, for example, an insert 36 ^II having a plurality of segments designed integrally with the turbine housing 14 according to FIG. As can be seen from FIG. 8, the spiral passages 38, 40, 42, 44 of the passage portion 37 are circumferential in the axial direction as indicated by the arrow 49 of the end surface portion 84 of the passage portion 37 in the circumferential direction of the passage portion 37. Designed completely open.

A lid that is forced using an axial bearing housing 16 as indicated by arrow 80 to the turbine housing 14 to hermetically cover the helical passages 38, 40, 42, 44 of the passage portion 37. 86 is provided and is therefore retained on it and supported on the latter via a contact surface 74 ^II . As a result, the lid 86 is pressed into the turbine housing 14.

To produce a geometrically sophisticated passage 37, such as inserts 36, 36 ^I , 36 ^II having multiple segments, the passage 37 is milled into the turbine housing 14, for example, at arrow 54 As shown, a spiral wall 68 is formed that is separated from the spiral passages 38, 40, 42, 44 in the radial direction.

  In the manufacture of the turbine housing 14, a rough passage 37 shape is first formed, for example through a sand casting process. The final outline of the passage portion 37 shown in FIG. 8 is then formed, for example, by mechanical processing.

Figure 9 refers to the further embodiment of an exhaust gas turbocharger 10 ^IV, a possible way to hold the insert 36 ^III having a plurality segments in the turbine housing 14 of an exhaust gas turbocharger 10 ^IV of the turbine 12 Show.

The insert 36 ^III having a plurality of segments is, for example, an insert 36 having a plurality of segments of the exhaust gas turbocharger 10 according to FIGS. The insert 36 ^III having a plurality of segments also has a spiral passage 38, 40, 42, 44, and has the same function as the insert 36 having a plurality of segments.

As can be seen from FIG. 9, the insert 36 ^III having a plurality of segments is held by a bearing housing 16 in the turbine housing 14, and the bearing housing 16 is connected to the turbine housing 14 by screws, for example, and has an insert having a plurality of segments. 36 ^III is forced in the axial direction as indicated by arrow 49 on turbine housing 14 in the direction of arrow 80. An arrow 88 indicates a leakage path from the spiral passage 28 acting as a peripheral feed section, while an arrow 90 is in the axial direction between the insert 36 ^III having multiple segments and the bearing housing 16 to the receiving space 18. A further leakage path from the spiral passage 82 through the disposed internal space 92 is shown. Due to the particularly rigid holding and pressing of the insert 36 ^III with multiple segments in or on the turbine housing 14, these leakage paths are at least essentially avoided. In order to avoid such leakage particularly effectively, the sealing element 94 is provided between the insert 36 ^III having multiple segments and / or between corresponding contact surfaces of the turbine housing 14 and the bearing housing 16 and / or Between the contact surface of the insert 36 ^III having a plurality of segments and the turbine housing 14 and between the contact surface of the adjusting ring 66 and the bearing housing 16 and / or the turbine housing 14 and / or the insert 36 ^III having a plurality of segments. Be placed.

Figure 10 refers to the further embodiment of an exhaust gas turbocharger 10 ^V, a further possible to hold and push the insert 36 ^IV having a plurality segments of the exhaust gas turbocharger 10 ^V in the turbine housing 14 of turbine 12 The method is shown. Insert 36 ^IV having multiple segments, for example, an insert 36 ^I having a plurality segments of the exhaust gas turbocharger 10 ^I according to FIGS. 4 6. The insert 36 ^IV with multiple segments similarly has helical passages 38, 40, 42, 44 and has the same function as the insert 36 with multiple segments. As can be seen from FIG. 10, the bearing housing 16 is supported via each contact surface 74 ^II of the turbine housing 14. In the axial direction as indicated by the arrow 49, a disc spring 75 is arranged between the multi-segment insert 36 ^IV and the bearing housing 16 so that it is on the one hand on the multi-segment insert 36 ^IV and on the other hand the bearing housing 16. Supported on the top. Through the connection of the bearing housing 16 to the turbine housing 14 and the result of the fact that the multi-segment insert 36 ^IV is supported via the contact surface 76 on the turbine housing 14, the helical passages 38, 40, 42, As opposed to the turbine housing 14, 44 is hermetically covered by the turbine housing 14, the disk spring 75 has a prestress to apply axial force to the insert 36 ^IV having multiple segments, as indicated by arrow 80. To give prestressed into a disc spring 75, the force in the bearing housing 16 in the direction of arrow 80 is applied, it is, for example, as the bearing housing 16 via the contact surfaces 74 ^II to the turbine housing 14 is pressed This is accomplished by screwing the bearing housing 16 and the turbine housing 14 using multiple screws.

Similarly, to avoid corresponding leakage, the disc spring 75 is used in the exhaust gas turbochargers 10, 10 ^II , 10 ^III , axially between the bearing housing 16 and the lid 86, and / or Alternatively, it may be disposed between the insert 36, 36 ^II or the passage portion 37 having a plurality of segments corresponding to the lid 86.

Possible leakage paths are also indicated in FIG. 10 by arrows 88 and 90, and these leakages are at least essentially a particularly firm retention of the insert 36 ^IV with multiple segments in and within the turbine housing. And is avoided by pressing.

The advantage of the disc spring 75 here is that the heat of the assembly of the turbine housing 14, the inserts 36, 36 ^I , 36 ^II , 36 ^III , 36 ^IV with multiple segments, the bearing housing 16, and the lid 86, if applicable. Even in the event of expansion, the disc spring 75 will always at least substantially multi-segment through the turbine housing 14 and / or lid 86, for example, to hermetically cover the helical passages 38, 40, 42, 44. on the insert ^{36,36 I, 36 II, 36 III} , 36 IV with, is to act at least indirectly in a preferred considerable force.

FIG. 11 shows a further embodiment of an exhaust gas turbocharger 10 ^VI with exhaust gas turbochargers 10, 10 ^II , 10 ^III , 10 ^IV , 10 ^V. The exhaust gas turbocharger 10 ^VI has an insert 36 ^V having multiple segments, which may be, for example, an insert 36 ^IV or 36 ^I having multiple segments. The insert 36 ^V having a plurality of segments has the same function as the inserts 36 ^IV and 36 ^I having a plurality of segments having spiral passages 38, 40, 42 and 44.

In the exhaust gas turbocharger 10 ^VI , the internal space 92 is fluidly connected to the spiral passage 28 that functions as a supply unit. For this purpose, for example, a number of through openings 96 are provided here in the form of holes, one of which is shown by way of example in FIG. This fluid connection provides at least essentially the same pressure in the interior space 92 as in the helical passage 28. Specifically hydrostatic pressure of the internal space 92, the whole is greater than the hydrostatic pressure in the individual spiral passageway 38, 40, 42, 44 of the insert 36 ^V having a plurality segments. As a result of the pressure difference, the force F acts through the corresponding surface of the wall 72 on the multi-segment insert 36 ^{V and} in the direction of the turbine housing 14 indicated by the arrow 80 in the axial direction indicated by the arrow 49. At least essentially directed to.

As a result, the insert 36 ^V having multiple segments is forced through the contact surface 76 of the turbine 12 to the turbine housing 14 such that the helical passages 38, 40, 42, 44 are at least essentially covered by the turbine housing 14. To be pushed into the latter. In a similar manner, force F is also applied to the lid 86 to at least essentially hermetically cover the helical passages 38, 40, 42, 44. This is a particularly advantageous way to prevent at least essentially all leaks, for example the leak path indicated by arrows 88 and 90.

FIGS. 12 and 13 show further embodiments of the exhaust gas turbocharger 10 with exhaust gas turbochargers 10, 10 ^I , 10 ^II , 10 ^III , 10 ^IV , 10 ^V. The exhaust gas turbocharger 10 ^VII also has an insert 36 ^VI having a plurality of segments, for example, an insert 36 or 36 ^III having a plurality of segments.

The actuator 56 includes an adjustment shaft 100 and an adjustment lever 102 in addition to the adjustment ring 66 and the tongues 58, 60, 62 and 64. Adjustment ring 66 with adjustment wheel 98, respectively provided with an engagement device 104 and 106, which are arranged while meshing with each other within the turbine housing 14 of an exhaust gas turbocharger 10 ^VII of the turbine 12. The adjustment wheel 98 is connected to the adjustment shaft 100 so as not to rotate relative to the adjustment shaft 100 and is held in the bearing housing 16 so as to be able to rotate around the rotation shaft 108. The adjusting shaft 100 is also connected to an adjusting lever 102 which is arranged in the turbine housing 14 and is guided through the through opening to the outside of the bearing housing so as not to rotate relative to the adjusting shaft 100. The adjustment lever interacts with the actuator of the exhaust gas turbocharger 10 ^VII and, for example, a vacuum cell, an electric motor, other adjustment members, and the like. The actuator can move the adjustment lever 102 in the direction of the arrow 110, specifically, rotate, so that the adjustment shaft 100 rotates about the rotation shaft 108 in the direction of the arrow 112. Similarly, the adjustment wheel 98 rotates about the rotation shaft 108, and the adjustment ring 66 rotates about the rotation shaft 24 in the direction of the arrow 114 via the meshing devices 104 and 106. Through the rotation of the adjustment ring 66, the tongs 58, 60, 62, 64 are rearranged in the direction of the arrow 48 as described above, so that the spiral inlet cross section _AS and / or the nozzle cross section _AR are adjusted. Is done. This adjustment via the meshing devices 104 and 106 is achieved by a particularly high throughput spread of the various turbines 12 of the exhaust gas turbocharger 10 ^VII . The adjustment of the adjustment ring 66 according to the method shown in FIGS. 12 and 13 can also be applied to other exhaust gas turbochargers 10, 10 ^I , 10 ^II , 10 ^III , 10 ^IV , 10 ^V. Adjustment of the adjustment ring 66 and, as a result, adjustment of the tongs 58, 60, 62, 64 using the meshing devices 104 and 106, is particularly large, that is, particularly large in the circumferential direction as indicated by the arrow 48. Allow range. This also makes it possible to achieve harmonic transmission from the adjustment angle range based on the adjustment angle of the actuator to the adjustment angle of the adjustment wheel 66 (tongue diverter).

Claims (10)

Exhaust gas turbocharger ^{(10,10 I, 10 II, 10} III, 10 IV, 10 V, 10 VI, 10 VII) inserted parts (36, 36 ^I for the turbine ^{(12), 36 II, 36} III, 36 ^IV , 36 ^V , 36 ^VI )
The insert (36, 36 ^I , 36 ^II , 36 ^III , 36 ^IV , 36 ^V , 36 ^VI ) can be inserted at least partially into the housing (14) of the turbine (12). At least one spiral passageway (38, 40, 42, 44) extending in at least a portion of its circumference in the circumferential direction (48) through which exhaust gas flowing through the turbine (12) can flow. at least partially open said insertion part ^{(36,36 I, 36 II, 36} III, 36 IV, 36 V, 36 VI) of least one end face (82, 84) on axially (49) Insert part designed. Said insert part (36, 36 ^I , 36 ^II , 36 ^III , 36 ^IV , 36 ^V , 36 ^VI ) has at least one further helical passage (38, 40, 42, 44), which is said insert part (36, 36 ^I , 36 ^II , 36 ^III , 36 ^IV , 36 ^V , 36 ^VI ) in the circumferential direction (48) extends at least over its circumferential portion and through which the exhaust gas flows through the turbine (12). it is possible to flow, it said further helical path (38, 40, 42, 44) comprises insert parts ^{(36,36 I, 36 II, 36} III, 36 IV, 36 V, 36 VI) of at least one characterized in that it is designed at least partially open in the axial direction (49) on an end face portion (82, 84), the insertion of claim 1 part ^{(36,36 I, 36 II, 36} III , 36 ^IV , 36 ^V , 36 ^VI ). Said helical path (38, 40, 42, 44) is at least partially, in particular completely, the circumference of the insertion part ^{(36,36 I, 36 II, 36} III, 36 IV, 36 V, 36 VI) 3. Insert part (36, 36 ^I , 36 ^II , 36 ^III , 36 ^IV , 36 ^V , 36, according to claim 1, characterized in that it is designed to open in the circumferential direction (48) ^VI ). Turbine (12) and at least one of claims 1 to inserting component according to any one of ^{3 (36,36 I, 36 II,} 36 III, 36 IV, 36 V, 36 VI) of the internal combustion engine with An exhaust gas turbocharger (10, 10 ^I , 10 ^II , 10 ^III , 10 ^IV , 10 ^V , 10 ^VI , 10 ^VII ) for
At least partially housed in the turbine housing (14), the insertion part ^{(36,36 I, 36 II, 36} III, 36 IV, 36 V, 36 VI) wherein circumferential (48) on the circumference of the Having at least one spiral passageway (38, 40, 42, 44) extending at least partly through which the exhaust gas flowing through the turbine (12) can flow, the spiral passageway (38, 40, 42) , 44), the insertion part ^{(36,36 I, 36 II, 36} III, 36 IV, 36 V, 36 VI) of at least one of the exhaust gas turbocharger at an end face portion (82, 84) (10, 10 ^{I, 10 II, 10 III,} 10 IV, 10 V, 10 VI, 10 VII axial direction (49) of) are designed at least partially open, the exhaust gas turbocharger (10, ^{0 I, 10 II, 10 III} , 10 IV, 10 V, 10 VI, 10 VII). The insertion piece (36, 36 ^I , 36 ^II , 36 ^III , 36 ^IV , 36 ^V , 36 ^VI ) with the helical passage (38, 40, 42, 44) facing the outlet (78) of the turbine At least partially in the axial direction (49) of the exhaust gas turbocharger (10, 10 ^I , 10 ^II , 10 ^III , 10 ^IV , 10 ^V , 10 ^VI , 10 ^VII ) on one end face (82) of The exhaust gas turbocharger (10, 10 ^I , 10 ^II , 10 ^III , 10 ^IV , 10 ^V , 10 ^VI , 10 ^VII ) is designed to be open and / or designed. ^I , 10 ^II , 10 ^III , 10 ^IV , 10 ^V , 10 ^VI , 10 ^VII ) bearing housing (16) for supporting the rotor (22), the helical passages (38, 40, 42, 44). ) Is the bearing The insertion part facing the direction of Ujingu ^{(16) (36,36 I, 36} II, 36 III, 36 IV, 36 V, 36 VI) of the one end surface (84) on at the exhaust gas turbocharger (10 10. Exhaust gas according to claim 4, characterized in that it is designed to be at least partly open in the axial direction of 10 ^I , 10 ^II , 10 ^III , 10 ^IV , 10 ^V , 10 ^VI , 10 ^VII ). Turbocharger (10, 10 ^I , 10 ^II , 10 ^III , 10 ^IV , 10 ^V , 10 ^VI , 10 ^VII ). Comprising at least one lid element (86), whereby at least part of the region of the helical passage (38, 40, 42, 44) is designed open and at least partly covered The exhaust gas turbocharger according to claim 5 (10, 10 ^I , 10 ^II , 10 ^III , 10 ^IV , 10 ^V , 10 ^VI , 10 ^VII ). A exhaust gas turbocharger ^{(10,10 I, 10 II, 10} III, 10 IV, 10 V, 10 VI, 10 VII) turbine for (12),
At least one helical passage (28) comprising a turbine housing (14) having a receiving space (18) for receiving a turbine wheel (20), through which exhaust gas flowing through the turbine (12) can flow. A helical passageway (28) extending over at least a portion of the circumference in the circumferential direction (48) of the receiving space (18),
The spiral passage (28) has at least one inlet (30) that allows exhaust gas to flow into the spiral passage (28), whereby exhaust gas is introduced into the containment space (18). Is capable of flowing,
At least one passage (37), whereby the at least one spiral passage (28) is divided into at least two spiral passages (38, 40, 42, 44) downstream of the inlet (30). A turbine (12) characterized in that. A exhaust gas turbocharger having turbine (12) according to claim ^{7 (10,10 I, 10 II,} 10 III, 10 IV, 10 V, 10 VI, 10 VII),
The housing portion of the exhaust gas turbocharger ^{(10,10 I, 10 II, 10} III, 10 IV, 10 V, 10 VI, 10 VII) (16), especially among the passage portion and the bearing housing (16), An exhaust gas turbocharger (10, 10) characterized in that an internal space (92) delimited at least partly from the passage (37) is formed and in fluid connection with at least one helical passage (28). ^I , 10 ^II , 10 ^III , 10 ^IV , 10 ^V , 10 ^VI , 10 ^VII ). A exhaust gas turbocharger ^{(10,10 I, 10 II, 10} III, 10 IV, 10 V, 10 VI, 10 VII) turbine for (12),
A turbine housing (14) having at least one helical passage (28, 38, 40, 42, 44) and a turbine wheel (20) rotate through said helical passage (28, 38, 40, 42, 44); An accommodation space (18) containing a turbine wheel (20) that is actuated by exhaust gas is provided, the turbine (12) having an actuating device (56), whereby at least one flowing into the accommodation space (18). The spiral inlet cross section (A _S ) and / or the nozzle cross section (A _R ) of the two spiral passages (28, 38, 40, 42, 44) are adjusted,
The actuating device (56) has at least two meshing devices (104, 106) for the purpose of adjusting the spiral inlet cross section (A _S ) and / or the nozzle cross section (A _R ). Turbine (12).   One of the meshing devices (104) is provided on an adjustment ring (66) of the actuating device (56), and the other meshing device (106) cannot be rotated relative to the adjusting shaft of the actuating device (56). The turbine (12) according to claim 9, characterized in that it is connected to (100) and is rotatable about a rotating shaft (108).

Images