DE102013006370A1 - Turbine for an exhaust gas turbocharger and modular system for such a turbine - Google Patents

Abstract

The invention relates to a turbine (10) for an exhaust gas turbocharger, comprising a turbine housing (12) having a receiving space (14) for a turbine wheel (16) rotatable about an axis of rotation (18) relative to the turbine housing (12) and at least two in the axial direction the turbine wheel (16) at least partially successive and via respectively, in the axial direction successive nozzle cross-sections (38, 40) in the receiving space (14) opening feed channels (32, 34), wherein an adjusting device (42) is provided, which at least a first obturator (44) displaceable relative to the turbine housing (12) about the axis of rotation (18) for adjusting a first (38) of the nozzle cross-sections (38, 40) and at least one displaceable relative to the turbine housing (12) about the axis of rotation (18) and in the axial direction on the first locking body (44) following, second locking body (46) for adjusting the second nozzle cross-section (40) comprises, as well as a building block nsystem for such a turbine (10).

Description

The invention relates to a turbine for an exhaust gas turbocharger according to the preamble of patent claim 1 and to a modular system for such a turbine.

From serial production it is known to equip respective internal combustion engines for driving the motor vehicles with a charging system. Such a charging system serves to supply the respective internal combustion engine with compressed air. For this purpose, the charging system comprises at least one exhaust gas turbocharger with at least one turbine, by means of which a compressor of the exhaust gas turbocharger is drivable. The compressor is used for compressing the air supplied to the internal combustion engine. The continuous tightening of emission limit values, in particular with regard to NO _x and soot emissions, has a strong influence on the design of such charging systems. Due to growing demands on the boost pressure provision in conjunction with high EGR rates, especially over medium load ranges up to the full load of the internal combustion engine is more and more a tendency to reduce the size of the turbines geometrically. This means that the turbines are equipped with relatively small flow cross-sections through which exhaust gas can flow. Demanded, high turbine performance is thus realized by increasing the Aufstaufähigkeit or by reducing the absorption capacity of the turbines in interaction with the associated internal combustion engine.

Furthermore, the inlet pressure level of the respective turbine is further driven upwards by the backpressure of a soot filter provided downstream of the turbine, whereby the turbine again has to be designed for smaller flow cross sectional area requirements for the compressor exhaust side air exhaust delivery requirements to be able to satisfy. However, this is accompanied by the reduction of the efficiency.

In order to realize an advantageous agility and thus very good driveability of the internal combustion engine, in particular in the use of supercharging systems for the supercharging of passenger car Otto engines, simple variations are advantageous, which have high reliability even at high temperatures. By means of such variability, flow conditions downstream and / or upstream of a respective turbine wheel of the turbine can be influenced. In particular, it is possible by means of such variability to be able to variably set a narrowest flow cross-section upstream of the turbine wheel and / or downstream of the turbine wheel. For this purpose, the variability includes, for example, a so-called Verstellmimik for adjusting at least one corresponding adjusting element. It is desirable in this respect to keep internal exhaust gas leakage of the variability low, so that low-efficiency acceleration phases of respective rotors of the exhaust gas turbocharger can be realized.

In order to meet the described, high demands, it is known to use double-flow, asymmetric turbines. Such a turbine comprises a turbine housing, which has a receiving space for a turbine wheel rotatable about an axis of rotation relative to the turbine housing and at least two feed channels opening at least partially in the axial direction of the turbine wheel and opening into the receiving space via respective nozzle cross-sections arranged side by side in the axial direction. Such a turbine is usually also referred to as a twin-flow turbine, wherein the nozzle cross sections in the axial direction can at least partially overlap one another. In the case of the usual design boundary conditions, which are also defined by the nominal point of the internal combustion engine from the charge side and consumption side, the lower engine speed range can therefore be determined in terms of EGR rate and air-fuel ratio in an asymmetric, double-flow turbine designed as a solid geometry turbine, for example. Ratio can not be optimally operated when the nominal point without a negative impact on the efficiency influencing so-called blowdown upstream of the turbine is to be driven charge-favorable. A solid geometry turbine is fixed with respect to its turbine geometry, d. H. not adjustable or changeable.

Blowing is usually referred to as bypassing the turbine wheel of exhaust gas. To realize such a blow-off, at least one bypass channel is provided, via which the turbine wheel can be bypassed by exhaust gas. The exhaust gas flowing through the bypass channel does not drive the turbine wheel, so that energy contained in the exhaust gas can not be used to drive the turbine wheel.

In order to be able to set the ratio of the EGR rates to the necessary air-fuel ratios in a particularly large operating range very well, a double-flow turbine type would be helpful, which would allow a simple and robust variability with a geometrical adaptability to the consumption, emission and thermal management requirements for rapid warm up of exhaust aftertreatment devices is operable.

The DE 10 2008 039 085 A1 discloses a turbine for an exhaust gas turbocharger, with a Turbine housing, which has a receiving space for a about a rotational axis relative to the turbine housing rotatable turbine and at least two axially in the axial direction of the turbine at least partially successive and via respective, in the axial direction successive nozzle cross-section opening into the receiving space feed channels. This turbine is thus designed as a twin-flow turbine.

Of the CN 202500653 U a so-called segment turbine is to be taken as known, in which the feed channels open in the circumferential direction of the turbine wheel over its circumference one behind the other into the receiving space. In other words, the nozzle cross sections are arranged not successively in the axial direction, but in the circumferential direction of the turbine wheel over its circumference.

The DE 10 2006 051 628 A1 discloses an exhaust gas turbocharger for an internal combustion engine, comprising a housing and a running tool, wherein the housing has a flow-through exhaust guide section and the running tool has a turbine wheel and a shaft rotatably connected to the turbine with a rotational axis. The turbine wheel is rotatably mounted in the exhaust gas guide section. The turbine wheel can be acted upon by exhaust gas. In the exhaust gas guide portion, a guide device for changing the application of the turbine wheel is arranged by the exhaust gas. The guide device has an adjustable in the direction of the axis of rotation axial slide, wherein the guide device is associated with an adjusting device with an adjustment fork. In this case, a guide element is provided, which extends in the direction of the axis of rotation, wherein the adjusting fork along the guide element is designed to be translationally movable.

The WO 2010/068557 A1 discloses an exhaust gas turbocharger with a turbine having a variable turbine geometry. In order to realize the variable turbine geometry, respective guide vanes are provided, which are rotatable about respective axes of rotation relative to the turbine housing, wherein these axes of rotation are spaced in the radial direction from the axis of rotation of the turbine wheel to the outside.

Finally, also reveals the WO 2012/170754 A1 a turbine with variable turbine geometry, which is also formed by about respective axes of rotation rotatable relative to the turbine housing vanes.

It is an object of the present invention to provide a turbine of the aforementioned type and a modular system for a turbine, by means of which a particularly efficient and robust operation of the turbine can be realized.

This object is achieved by a turbine for an exhaust gas turbocharger having the features of patent claim 1 and by a modular system having the features of patent claim 10. Advantageous embodiments with expedient and non-trivial developments of the invention are specified in the remaining claims.

In order to further develop a turbine for an exhaust gas turbocharger of the kind indicated in the preamble of patent claim 1 such that a particularly efficient and particularly robust operation of the turbine is possible even at high exhaust gas temperatures, an adjusting device is provided which at least one about the axis of rotation of the turbine wheel relative to the turbine housing displaceable, first Versperrkörper for adjusting a first of the nozzle cross sections and at least one about the rotational axis relative to the turbine housing displaceable and in the axial direction following the first Versperrkörper, second Verperrkörper for adjusting the second nozzle cross section comprises.

It can be provided that the Versperrkörper or nozzle cross sections in the circumferential direction of the turbine wheel over its circumference not offset from each other, d. H. are not offset and arranged relative to each other, so that the Versperrkörper or the nozzle cross sections completely overlap each other in the axial direction. Alternatively it can be provided that the nozzle cross-sections or the Versperrkörper circumferentially of the turbine over the circumference are arranged offset from one another in such a way that they partially overlap each other in the axial direction or that they do not overlap each other in the axial direction, so are arranged without overlapping each other , The turbine is designed as a multi-segment turbine, in which the nozzle cross sections are not arranged sequentially in the circumferential direction of the turbine wheel over its circumference or successively in the manner of a multi-segment turbine, but in the axial direction.

By using such a twin-flow turbine and the adjusting device with the respective locking bodies for respectively adjusting the nozzle cross-sections, the twin-flow turbine can be adapted at least substantially optimally to different operating points of an associated internal combustion engine and thus to different exhaust gas mass flows flowing through the supply channels, so that the turbine has a particularly has advantageous adaptability to different consumption, emission and thermal management requirements. Due to its particularly flexible adaptability, the turbine can be particularly efficient even with different Exhaust gas mass flows, ie operated at very high and in contrast to low exhaust gas mass flows.

The adjustment with the Versperrkörpern is designed as a so-called tongue slider. Such a tongue slider has a very high robustness, especially against high exhaust gas temperatures. In other words, jamming and / or other malfunction of the tongue slider can be avoided in a simple manner, even at high exhaust gas temperatures, so that the turbine in a very large exhaust gas temperature range, in which there are very different exhaust gas temperatures with associated thermal expansion, operated and on the different exhaust gas mass flows can be adjusted. Through the use of the respective Versperrkörper beyond a particularly needs-based adjustment of the respective nozzle cross-sections is possible.

The twin-flow turbine has advantages over a multi-segment turbine in terms of a lower mechanical load on the turbine wheel. The feed ducts of the twin-flow turbine, which are preferably long and, for example, designed as spiral passages, lead to lower pressure pulsations with respect to the multi-segment turbines on the blading of the turbine wheel, whereby the expense for ensuring the mechanical functionality of the turbine wheel and the turbine can be kept low overall. The turbine is thus also particularly inexpensive to produce.

The feed channels are formed for example as spiral channels. Such a spiral channel extends in the circumferential direction of the turbine wheel over its circumference at least substantially helically. A respective extent of the feed channels or the spiral channels running in the circumferential direction of the turbine wheel over its circumference is usually referred to as the wrap angle.

In a particularly advantageous embodiment of the invention, the Versperrkörper are different from each other. This is to be understood in particular that the blocking bodies are different from one another with respect to their respective extent extending in the circumferential direction of the turbine wheel over its circumference and / or with regard to their respective position in the circumferential direction of the turbine wheel over its circumference relative to the turbine housing and / or with regard to their respective cross-sectional profile. In this way, a particularly needs-based, respective adjustment of the respective nozzle cross section can be realized. In other words, the setting of the respective nozzle cross section can be adapted to the purpose of the respective feed channel.

Preferably, the feed channels are asymmetrical to one another, in particular with regard to their respective flow cross-section through which exhaust gas can flow. Alternatively or additionally, the feed channels may also be designed asymmetrically with respect to a respective course, in particular a spiral course. This course or spiral course extends from a respective exhaust gas inlet of the respective feed channel up to the respective nozzle cross section. As a result of this asymmetrical design, the feed channels can be optimized for a particular purpose to be fulfilled. Here, a first of the feed channels, for example, the purpose of having an advantageous Aufstauverhalten so as to provide or realize particularly high EGR rates. By contrast, the other supply channel fulfills, for example, the purpose of being able to realize a desired and advantageous fuel / air ratio in at least one combustion chamber, in particular in the form of a cylinder, of the associated internal combustion engine. The fuel-air ratio is usually denoted by λ.

If, for example, the two locking bodies are at least substantially identical with regard to their respective profile cross section and are arranged at the same height with respect to a respective first end in the circumferential direction of the turbine wheel or at the same height over the circumference of the turbine wheel over the circumference thereof the Versperrkörper differ from each other in particular with respect to their respective extending in the circumferential direction of the turbine wheel over its circumference extent. As a result, respective, in the circumferential direction of the turbine wheel over its circumference from the respective first end spaced, second ends or tips of the Versperrkörper are arranged in the circumferential direction of the turbine wheel over its circumference at different heights. In other words, one of the Versperrkörper extends from the respective first ends in the circumferential direction of the turbine wheel over its circumference further than the other Versperrkörper. This means that the respective, second ends or tips of the Versperrkörper are in different angular positions.

These different angular positions can - if the Versperrkörper example, the same profile cross-section and the same extent - be realized, for example, also in that the Versperrkörper circumferentially of the turbine wheel are arranged offset from each other over its circumference. Thus, the Versperrkörper overlap each other in the axial direction of the turbine wheel in a respective sub-area, while in a respective, further sub-area in Axial direction are arranged without overlap each other.

However, the Versperrkörper can also the same or different from each other extensions or lengths and / or the same different profiles or profile cross-section, d. H. Outer contours.

In a particularly advantageous embodiment of the invention, the Versperrkörper are connected to a coupling element, via which the Versperrkörper are simultaneously displaceable relative to the rotational axis relative to the turbine housing. The two Versperrkörper can thus be connected to each other via the coupling element and are moved via the coupling element together by means of an actuator relative to the turbine housing. As a result, the number of parts, the weight and the cost of the turbine can be kept low. The coupling element is, for example, a ring, which extends in the circumferential direction of the turbine wheel over its circumference and is arranged in the axial direction between the two locking bodies.

It has proven to be particularly advantageous if, for mutual sealing of the feed channels, at least one sealing element supported on the coupling element on the one hand and on the wall of the turbine housing fluidically separated from one another at least in a partial region is provided. The sealing element may be, for example, a piston ring, so that a cost effective and effective seal is ensured. By sealing mutual interference of the feed channels can be avoided or at least kept low, which benefits the efficient operation of the turbine.

It has proven to be particularly advantageous if the nozzle cross-sections are arranged offset from each other in the circumferential direction of the turbine wheel over its circumference. In this case, the nozzle cross-sections in the circumferential direction of the turbine wheel can be arranged offset relative to one another over its circumference such that they do not overlap one another in the axial direction, ie. H. are arranged without overlap each other. Alternatively, it may be provided that the nozzle cross sections overlap each other in the axial direction in a respective subregion. By this displacement of the nozzle cross-sections relative to one another, the turbine wheel can be driven particularly well by the exhaust gas and, in particular, even if the feed channels are used for mutually different purposes, as described above.

In a further particularly advantageous embodiment of the invention, the respective Versperrkörper in a position, in particular in an intermediate position, which is based on an adjustment of the respective Versperrkörpers in the middle between a maximum opening of the respective nozzle cross-section open position and a maximum cross-sectional area of the respective nozzle cross-section, in Radial direction of the turbine wheel to the outside at least in a sub-area covered by a belonging to the respective Versperrkörper feed channel in the radial direction inwardly at least partially bounding wall of the turbine housing, said subregion has a circumferential extent of the turbine wheel over its circumference extending extension and wherein the respective adjustment , over which the respective locking body is displaceable, is at least twice the extent of the partial area. As a result, the turbine can be adapted particularly well and flexibly to different exhaust gas mass flows.

Another embodiment is characterized in that the extent of the respective subregion, i. H. the extent of the overlap amounts to at least 10% of a respective wrap angle of the corresponding feed channel running in the circumferential direction of the turbine wheel over its circumference. This also makes the turbine particularly advantageous to different exhaust gas mass flows adjustable. In addition, a particularly high absorption capacity of the turbine can be realized, so that, for example, a very high throughput spread can be realized.

The invention also includes a modular system for a turbine of an exhaust gas turbocharger. The modular system comprises at least one turbine housing, which has a receiving space for a about a rotational axis relative to the turbine housing rotatable turbine and at least two axially in the axial direction of the turbine at least partially successive and via respective, in the axial direction successive nozzle cross-sections opening into the receiving space feed channels. The turbine is thus designed or formable in the manner of a twin-flow turbine.

The modular system further comprises a first adjusting device for adjusting the respective nozzle cross-section. In addition, the modular system comprises at least one second adjusting device, which is different from the first adjusting device, for setting the respective nozzle cross section. Optionally, the first adjusting device or the second adjusting device can be mounted in the turbine housing. In other words, the turbine housing optionally with the first adjustment or with the second Adjustment be provided. By means of the modular system, it is possible to adapt the turbine to different purposes in a simple and, in particular, modular manner, by using the first adjusting device or the second adjusting device, depending on the intended use.

Alternatively or in addition to the mutually different adjustment, the modular system may also comprise at least two mutually different turbine wheels, wherein either a first of the turbine wheels or optionally a second of the turbine wheels in the turbine housing can be arranged. The turbine wheels differ in particular with regard to respective Radaußenkonturen and / or with respect to respective Radaustrittsdurchmesser. In particular, they differ with respect to the so-called Trims. The so-called trim is a ratio between a Radeintrittsdurchmesser and a Radaustrittsdurchmesser the turbine wheel.

In addition, the modular system may include at least a second turbine housing, which is formed differently from the first turbine housing. In particular, the turbine housings can differ from one another with regard to respective flow cross sections of the feed channels through which exhaust gas can flow and / or with regard to the respective nozzle cross sections and / or with regard to the respective wrap angles of the feed channels. As a result, different variants of the turbine can be formed in a simple, time-consuming and cost-effective manner, which can be operated efficiently depending on the boundary conditions and enable efficient operation of the respective associated internal combustion engine.

Further advantages, features and details of the invention will become apparent from the following description of preferred embodiments and from the drawing. The features and feature combinations mentioned above in the description as well as the features and feature combinations mentioned below in the description of the figures and / or in the figures alone can be used not only in the respectively specified combination but also in other combinations or in isolation, without the scope of To leave invention.

The drawing shows in:

1 a schematic longitudinal sectional view of a turbine for an exhaust gas turbocharger of an internal combustion engine, with a turbine housing having a receiving space for a rotational axis relative to the turbine housing rotatable turbine and at least two axially in the axial direction of the turbine at least partially successive and on respective successive in the axial direction nozzle cross-sections in the receiving space opening feed channels, wherein an adjusting device is provided which at least one displaceable about the axis of rotation relative to the turbine housing, the first Versperrkörper for adjusting a first of the nozzle cross-sections and at least one about the axis of rotation relative to the turbine housing displaceable and in the axial direction of the first Versperrkörper , second Verperrkörper for adjusting the second nozzle cross section comprises;

2 a partial cross-sectional view of the turbine;

3 a diagram illustrating different embodiments of the turbine;

4 a diagram illustrating different embodiments of the turbine;

5 a detail of another schematic cross-sectional view of the turbine;

6 1, a schematic longitudinal sectional view of the turbine wheel according to a first embodiment;

7 a fragmentary schematic longitudinal sectional view of the turbine wheel according to a second embodiment;

8th 1, a schematic longitudinal sectional view of the turbine wheel according to a third embodiment;

9 a diagram illustrating different embodiments of the turbine;

10 a diagram illustrating an application of the turbine according to a first embodiment;

11 a diagram illustrating an application of the turbine according to a second embodiment;

12 a diagram illustrating different embodiments of the turbine;

13 a diagram illustrating different embodiments of the turbine;

14 a diagram illustrating different embodiments of the turbine;

15 a diagram illustrating different embodiments of the turbine;

16 a diagram illustrating different embodiments of the turbine;

17 a diagram illustrating different embodiments of the turbine;

18 a diagram illustrating different embodiments of the turbine;

19 a diagram illustrating different embodiments of the turbine; and

20 a diagram illustrating different embodiments of the turbine;

In the figures, identical or functionally identical elements are provided with the same reference numerals.

1 shows in a schematic longitudinal sectional view with a whole 10 designated turbine for an exhaust gas turbocharger of an internal combustion engine. The exhaust gas turbocharger serves to supply the internal combustion engine with compressed air. For this purpose, the exhaust gas turbocharger includes the turbine 10 and one in 1 unrecognizable compressor, which from the turbine 10 is drivable.

The turbine 10 includes a turbine housing 12 which is in 1 can be seen in sections. The turbine housing 12 has a recording room 14 on which a turbine wheel 16 at least partially included. The turbine wheel 16 is about a rotation axis 18 relative to the turbine housing 12 rotatable. The turbine wheel 16 has a whole with 20 designated blading, from which in 1 an impeller blade 22 can be seen. The impeller blade 22 has an entry edge 24 which in turn has an axial extension b _RAD running in the axial direction, which thus has the width of the leading edge 24 is. The impeller blade 22 also has a trailing edge 26 on. About the leading edge 24 becomes the turbine wheel 16 from the turbine housing 12 flowing through exhaust gas of the internal combustion engine, wherein the leading edge 24 in a so-called entry area 28 of the turbine wheel 16 is arranged. The entrance area 28 and thus the leading edge 24 are arranged on an entrance diameter D _E.

The trailing edge 26 is an exit area 30 assigned, the turbine wheel 16 over the trailing edge 26 is discharged from the exhaust gas. The exit area 30 has an exit diameter D _A. The turbine wheel 16 has a so-called trim, which describes the relationship between the inlet diameter D _E and the outlet diameter D _A. In other words, the trim results in:

The turbine housing 12 has a first feed channel 32 on, which is designed as a first spiral channel. Furthermore, the turbine housing 12 a second feed channel 34 on, which is designed as a second spiral channel. This means that the feed channels 32 . 34 in the circumferential direction of the turbine wheel 16 extend over the circumference at least substantially spiral over a respective wrap angle. The wrap angle of the first feed channel 32 is also designated by φ ₁₀ , while the wrap angle of the second feed channel 34 is designated by φ ₂₀ . For the description of a respective cross-section of the feed channels through which exhaust gas can flow 32 . 34 a running variable φ is used, wherein the running variable φ from the respective beginning of the feed channels 32 . 34 , ie based on the respective feed channel 32 . 34 from the value 0 ° to the respective end of the feed channel 32 . 34 ie, extends to a respective maximum value.

This means that a respective profile of the respective flow cross section of the feed channels 32 . 34 from the respective beginning to the respective end as a function of the variable φ can be expressed. The respective flow cross section can be variable, wherein the flow cross section of the feed channel 32 with As1 and the flow cross-section of the feed channel 34 labeled As2. The feed channel 32 starts from a so-called inlet cross-section of the feed channel 32 , wherein the inlet cross-section of the feed channel 32 with As10 or also with A _{S0, λ} is called. The feed channel 32 starts from an inlet cross-section of the feed channel 34 , wherein the inlet cross-section of the feed channel 34 with As2 or with A _{S0, AGR} is called.

Relative to the circumferential direction of the turbine wheel is the inlet cross section of the feed channel 32 at an angle φ ₁₀ , while the inlet cross-section of the feed channel 32 at an angle φ ₂₀ . This angle φ ₁₀ is also referred to as entrance angle φ _{λ, 0} . The angle φ ₂₀ is also referred to as entrance angle φ _{AGR, 0} . The running variable φ has the value 0 ° at the entry angle φ ₁₀ . Similarly, the running variable φ at the entrance angle φ _{20 has} the value 0 °. This means that the running variable φ in each case on the feed channel 32 . 34 is or can be, in order to describe this at any point in the circumferential direction of the turbine wheel over its circumference. Relative to the feed channel 32 the variable is called φ _λ . Relative to the feed channel 43 the variable is called φ _AGR .

Preferably, it is provided that a respective profile of the respective flow cross-section As1 and As2 obeys the following law: As1 = AS10 x (1 - _φ λ / φ ₁₀₎ ^ ex1 and As2 = As20 · (1 - φ _AGR / φ ₂₀ ) ^ eX2.

In other words, these laws make a respective course, in particular spiral course, of the feed channels 32 . 34 for a respective Flächenabgriff yet to be explained below Versperrkörpern an adjustment of the turbine 10 described. In this case, ex1 is a first exponent which has at least the value 2 or greater. Furthermore, ex2 is a second exponent which has at least the value 2 or greater. In this case, a natural, positive number can be used as the respective exponent ex1 and ex2, the exponent ex1 and / or the exponent ex2 preferably being 2, 3, 4 or 5. The exponents ex1 and ex2 may be the same or different from each other.

How out 1 can also be seen, the feed channel opens 32 with a first width b1 in the receiving space 14 while the second feed channel 32 with a second width b2 in the receiving space 14 empties. Thus, the feed channels lead 32 . 34 the exhaust gas of the internal combustion engine to the turbine wheel 16 which is flowed by the exhaust gas and thereby driven.

Out 1 is also a wall 36 of the turbine housing 12 recognizable, by means of which the feed channels 32 . 34 are fluidly separated from each other at least in a partial area. The feed channels 32 . 34 lead through a respective nozzle cross-section 38 . 40 in the recording room 14 , In 1 with b3 is a third width of the wall 36 denotes which the wall 36 at the height of the nozzle cross sections 38 . 40 having. The turbine 10 also includes an adjustment 42 , which is designed as a so-called tongue slider. This tongue slider is about the axis of rotation 18 relative to the turbine housing 12 displaceable. The tongue slider or the adjusting device 42 includes a first locking body 44 and a second locking body 46 , The locking bodies 44 . 46 are via a coupling element in the form of a ring 48 connected with each other. Preferably, the Versperrkörper 44 . 46 and the ring 48 formed integrally with each other. In this case, the tongue slider may preferably be formed as a precision casting. Starting from the height of the nozzle cross sections 38 . 40 in the radial direction of the turbine wheel 16 the ring tapers inwards 48 so that he is on the side of the turbine wheel 16 a fourth width b4, which is substantially smaller than the width b3 on the side of the wall 36 ,

As a result of their connection, the Versperrkörper 44 . 46 simultaneously, ie simultaneously around the axis of rotation 18 relative to the turbine housing 12 postponed. By turning the locking bodies 44 . 46 can the respective nozzle cross section 38 . 40 be set. In other words, a respective value of the nozzle cross sections 38 . 40 by turning the locking bodies 44 . 46 around the axis of rotation 18 relative to the turbine housing 12 variably adjustable.

How out 1 is recognizable, serves the first Versperrkörper 44 for adjusting the first nozzle cross-section 38 while the second locking body 46 for adjusting the second nozzle cross-section 40 serves. An adjustment of the second nozzle cross-section 40 by means of the first locking body 44 is just as impossible as an adjustment of the first nozzle cross-section 38 by means of the second locking body 46 ,

In addition, is off 1 recognizable that the feed channels 32 . 34 in the axial direction of the turbine wheel 16 are arranged consecutively. As a result, the nozzle cross sections are also 38 . 40 in the axial direction consecutively, ie side by side, arranged. The turbine 10 is thus designed as a twin-flow turbine. This arrangement of nozzle cross sections 38 . 40 Corresponding are the Versperrkörper 44 . 46 in the axial direction consecutively, ie side by side, arranged.

The tongue slider has an inner peripheral side diameter, ie, an inner diameter D _I and an outer peripheral side diameter, that is, an outer diameter D _A.

The turbine 10 also includes a in 1 partially recognizable contour piece 50 , which is interchangeable. This means that in 1 recognizable contour piece 50 can be exchanged for other contour pieces. The contour piece 50 follows an outer contour of the turbine wheel 16 at least substantially, being between the contour piece 50 and the turbine wheel 16 , in particular the impeller blade 22 , a gap S1 is provided. The gap S1 is preferably in a range of 0.6 to 0.65 mm inclusive.

The design of the Versperrkörper 44 . 46 can be especially good 2 based on the locking body 44 be removed. In 2 is the first feed channel 32 recognizable, the inlet cross-section A _{S0, λ} at φ _λ = φ = 0 °. In 2 is with S the Centroid of the inlet cross-section A _{S0, λ} denotes. Furthermore, the inlet diameter D _{E of} the turbine wheel 16 in 2 denoted by D3.

In 2 In addition, the inlet cross-section A _{S0, AGR is} illustrated, which actually related to the image plane of 1 behind the first feed channel 34 lies. How out 2 can be seen, the inlet cross-section A _{S0, AGR is} substantially less than the inlet cross-section A _{S0, λ} . Relative to the second feed channel 34 is the inlet cross section A _{S0, AGR} at φ _AGR = φ = 0 °. Here, the inlet cross section A is _{S0, AGR} by a differential angle Δφ in the circumferential direction of the turbine wheel 16 offset over the circumference of the inlet cross-section A _{S0, λ} . In the present case, the difference angle Δφ is at least substantially 23 °. Consequently, the second supply channel is also the one 34 and accordingly to the inlet cross section A _{S0, AGR} belonging nozzle cross-section 40 in the circumferential direction of the turbine wheel 16 about its circumference by the difference angle Δφ of at least substantially 23 ° relative to the first feed channel 32 and consequently offset from the inlet cross-section A _{S0, λ} .

The first feed channel 32 is also referred to as a λ-channel or λ-spiral, since the feed channel 32 is especially used to the turbine wheel 16 and about to drive the compressor so that sets a desired fuel-air ratio in at least one combustion chamber in the form of a cylinder of the internal combustion engine. In this case, the fuel-air ratio is denoted by λ. The second feed channel 34 is also referred to as EGR passage or as EGR scroll. This is the case since the feed channel 34 is designated in particular for the representation of high exhaust gas recirculation rates. In the context of such exhaust gas recirculation, which is abbreviated to EGR, exhaust gas is recirculated from an exhaust tract to an intake tract of the internal combustion engine, whereby the emission and in particular the nitrogen oxide (NO _x ) emissions of the internal combustion engine can be kept low. In order to be able to realize particularly high EGR rates, the EGR channel preferably has a high build-up behavior. Such a high Aufstauverhalten example, by a particularly small flow cross section As2 feasible.

Out 2 is also apparent that the Versperrkörper 44 is formed at least substantially in the manner of a wing profile. The locking body 44 is also called a tongue. The above and below to the locking body 44 Described can easily on the Versperrkörper 46 be transmitted.

Since the tongues (Versperrkörper 44 . 46 ) are interconnected, are respective adjustment ranges over which the Versperrkörper 44 . 46 relative to the turbine housing 12 are displaceable, the same. This respective adjustment range is, for example, in the circumferential direction of the turbine wheel over its circumference at least 80 °, so that the adjustment range can also be expressed by 80 ° + x °. With x ° in this case a correction value is referred to, which will be explained below.

As part of a modular system for producing different variants of the turbine 10 For example, three different embodiments of the tongue slider can be provided. A first of these embodiments is also referred to as S ₀ , this first embodiment being the basic tongue slider. In this basic tongue slider are respective tongue tips 52 the locking body 44 . 46 relative to the respective variable φ of the feed channels 32 . 34 arranged in an angular position of φ = 30 °. In other words, the locking body extends 44 up to φ = Φ _λ = 30 °, while also the Versperrkörper 46 up to φ = φ _AGR = 30 °. This position of the respective tongue tip 52 is also called zero position. The zero position refers to a respective intermediate position of the Versperrkörper 44 . 46 , The intermediate position is - based on the respective adjustment of the Versperrkörper 44 . 46 - in the middle between a respective nozzle cross-section 38 . 40 maximum open position and one of the respective nozzle cross-section 38 . 40 maximum narrowing closed position. With an adjustment range of 80 °, the locking bodies are 44 . 46 thus - referring to the image plane of 2 - Moving from the intermediate position (zero position) by 40 ° counterclockwise and 40 ° clockwise.

The tongue tip position of a second, with S _{0 + 10} is extended relative to the zero position by 10 °, so that the Versperrkörper 44 extends up to φ _λ = 40 °. As a result, the locking body also extends 46 up to φ _AGR = 40 °.

Compared to the base tongue slider, the tongue tip position is shortened by 10 ° in the third embodiment designated S _0-10 . This means that the locking body 44 extends up to φ _λ = 20 °, while the Versperrkörper 46 extends up to φ _AGR = 20 °.

The locking bodies 44 . 46 are each between the respective, the respective nozzle cross-section 38 . 40 maximum releasing open position and the respective, the respective nozzle cross-section 38 . 40 slidably closed maximum closing position. Here are the Versperrkörper 44 . 46 in the intermediate position and in several, so-called adaptation positions between the closed position and the intermediate position and between the Adjustable between the intermediate position and the open position. Starting from the lying in the middle between the closed position and the open position zero position (intermediate position) of the tongues is the angle range to the closed position 40 °, whereby the tongues can each move in the closed position in the first embodiment to φ = 70 °, in the second embodiment to φ = 60 ° and in the third embodiment to φ = 80 °. The outgoing from the zero position adjustment range for opening, ie the open position is - (40 ° + x °), causing the tongues of the tongue slider in the respective open position according to the first embodiment to φ = - (10 ° + x °), in the second embodiment until φ = - (20 ° + x °) and in the third embodiment can move to φ = - (0 ° + x °). The correction value x ° is a variable, which can be between 0 ° and 10 ° inclusive, to take account of possibly very high lever and torque ratios, and to be able to realize a high degree of robustness of the tongue slider against this background.

These three embodiments of the tongue slide are advantageously either in the turbine housing 12 to assemble. In other words, the turbine housing 12 optionally be provided with the first embodiment, the second embodiment or the third embodiment of the tongue slider.

In addition, it is preferably provided in all three embodiments that the Versperrkörper 44 . 46 in particular offset by 23 ° to each other. In terms of the particular embodiment, the tongues can be at least substantially the same profilings, ie outer contours and equal lengths, ie at least substantially the same, in the circumferential direction of the turbine wheel 16 have extending over its circumference extensions. However, the profiles and / or the extents may also be different. In the following, however, the same profiles and equal lengths of the tongues of the different embodiments are assumed.

How out 5 can be seen, the tongue slide on at least one axial end face 54 at least one support element 56 in the form of a support bucket or a support profile. Preferably, a respective support profile for the nozzle cross-section 38 (λ-nozzle) and for the nozzle cross-section 40 (EGR nozzle) provided. The support element 56 serves for the axial stabilization of the tongue slider.

In 2 is with α ₀ the flow angle at a nozzle exit of the feed channel 32 illustrates in which the exhaust gas from the feed channel 32 to the turbine wheel 16 flows. Accordingly, there are also based on the feed channel 34 and on the locking body 46 a flow angle α ₀ , below which the exhaust gas from the feed channel 34 to the turbine wheel 16 flows. The flow angle α ₀ is the mean, absolute flow angle directly in front of the turbine wheel 16 , A tongue spacing Δa extending in the radial direction is preferably at least substantially 5% of the inlet diameter D ₃ or D _E , the inlet diameter being equal to the outside diameter of the turbine wheel 16 corresponds.

Out 2 is also a flange 33 recognizable, over which the feed channel 32 fluidly connectable with an exhaust pipe of the exhaust tract of the internal combustion engine. As a result, the exhaust gas flowing through the exhaust gas piping into the feed channel 32 overflow. Also the feed channel 34 is assigned a flange, which with respect to the image plane of 2 behind the flange 33 lies. About this flange, the feed channel 34 be fluidly connected to the exhaust piping, so that the exhaust gas in the feed channel 34 can flow in.

3 shows a graph 58 in which the three embodiments S _0-10 , S ₀ and S _{0 + 10} are entered in columns. Line by line are different embodiments of the turbine wheel 16 in the diagram 58 entered. A first of these embodiments is designated TR-88/72, a second of the embodiments of TR-88/74 and the third embodiment of TR-88/76. These different embodiments of the turbine wheel 16 differ with respect to their trims, each having an entrance diameter D _E of 88 mm. The first embodiment of the turbine wheel 16 has an exit diameter D _A of 72 mm, while the second embodiment has an exit diameter D _A of 74 mm and the third embodiment has an exit diameter D _A of 76 mm.

A combination of the second embodiment TR-88/74 of the turbine wheel 16 with the first embodiment S _{0 of} the tongue slider provides a 60 designated base of the turbine 10 dar. Starting from the base 60 arise - as indicated by directional arrows in 3 is shown - different characteristics of the turbine 10 , In a combination of the first embodiment TR-88/72 of the turbine wheel 16 With the second embodiment S _{0 + 10 of} the tongue slider results in the context of the modular system, the smallest possible Turbinenschluckfähigkeit. A combination of the third embodiment TR-88/76 with the second embodiment S _{0 + 10} gives a small degree of reaction. A combination of the first embodiment TR-88/72 with the third embodiment S _0-10 gives a In contrast, large degree of reaction. A combination of the third embodiment TR-88/76 with the third embodiment S _0-10 results in the largest possible absorption capacity of the turbine in the context of the modular system 10 ,

4 shows a diagram 62 to illustrate the different embodiments. Another possibility of variation exists with respect to the variation of the exponents ex1 and ex2. These exponents ex1 and ex2 are selected according to the expected demand from the engine side. The modular system thus preferably comprises the three described embodiments of the tongue slider, the three described embodiments of the turbine wheel 16 and two different embodiments of the turbine housing 12 , A first of these embodiments of the turbine housing 12 For example, the exponent ex1 is 2 while the exponent ex2 is 3. The second embodiment provides that the exponent ex1 is 5, while the exponent ex2 is also 5. As a result, a very high throughput spread can be realized.

On the abscissa 64 of the diagram 62 the respective wrap angle φ is plotted, while on the ordinate 66 the respective profile of the flow cross sections As1 and As2 is to be applied. Further, in the diagram 62 applied the different embodiments S ₀ , S _{0 + 10} and S _{0-10 of} the tongue slider. A straight 68 illustrates a base curve of the λ-channel, while a straight line 70 illustrates a basic course of the EGR channel.

A course 72 characterizes the course of the flow cross section As1 of the λ spiral when the exponent ex1 is 1. Accordingly, a course characterizes 74 the course of the flow cross section As1, when the exponent ex1 is 2. A course 76 characterizes the course of the flow cross section As1 when the exponent ex1 is 3. A course 78 characterizes the course of the flow cross section As1 over that from the abscissa 64 applied run variables φ, if the exponent ex1 is 4. Finally, a course characterizes 80 the course of the flow cross section As1, when the exponent ex1 is the value 5. Analogous to this, a course characterizes 82 the course of the flow cross section As2 over the running variable φ, ie over the wrap angle, when the exponent ex2 is 1. A course 84 illustrates the course of the flow cross section As2 when the exponent ex2 is 2. A course 86 illustrates the course of the flow cross section As2 when the exponent ex2 is 3. A course 88 illustrates the course of the flow cross section AS2 when the exponent ex2 is 4. And finally, a history illustrates 90 the course of the flow cross section As2, when the exponent ex2 is the value 5.

5 shows the turbine 10 in another cross-sectional view. Relative to the respective wrap angle and thus to the respective run variable φ is the zero position of the respective tongue tip 52 the locking body 44 . 46 at φ = 40 °, the Versperrkörper 44 . 46 are formed identically in terms of their length and in terms of their profiling. Furthermore, it is off 5 to realize that the locking bodies 44 , 46 are offset by the difference angle Δφ of 23 ° to each other. This means that in 5 the second embodiment S _{0 + 10 of} the tongue slider is illustrated.

This results in an adjustment range starting from the zero position to the closed position of + 40 ° and the open position of - (40 ° + x °), where x is in a range of 0 ° to 10 ° inclusive inclusive.

Out 1 it can be seen that for mutual sealing of the feed channels 32 . 34 on the one hand, on the ring 48 and on the other hand, on the wall 36 supported sealing element 92 is provided, which is formed for example as a piston ring. This seal is based on 5 preferably on a sealing diameter D _D.

As starting geometry for the production of the tongues are preferably used blade profiles. For example, the blade profiles are turned to a diameter of 113.2 mm, resulting in an overlap angle of 40 ° with the turbine housing 12 is realizable. In other words, out 2 , which the locking body 44 shows in the zero position, it can be seen that the locking body 44 in the radial direction of the turbine wheel 16 to the outside in a subarea 94 through a housing tongue 96 of the turbine housing 12 is covered. This subarea 94 has in the zero position (intermediate position) one in the circumferential direction of the turbine wheel 16 extending over its circumference extent of preferably 40 °. In other words, a coverage of 40 ° is provided, which by the said overlap angle of 40 ° between the housing tongue 96 and the locking body 44 (and thus the locking body 46 ) is provided.

Advantageously, extending in the radial direction distance between the respective tongue tip 52 and the entry area 28 of the turbine wheel 16 at least substantially 10% of the radius of the turbine wheel 16 ie half of the exit diameter DA or preferably the entry diameter DE.

In the present case, the tongues have an at least substantially identical profiling. The position of the respective support elements 56 in the form of the support profiles is preferably in the circumferential direction of the turbine wheel 16 over its circumference 180 ° to the tip of the tongue 52 of the locking body 44 ,

6 to 8th show the three described, different embodiments TR-88/72, TR-88/74 and TR-88/76 of the turbine wheel 16 , It shows 6 the first embodiment TR-88/72, while 7 the second embodiment TR-88/74 and 8th the third embodiment TR-88/76 shows. In this case, the inlet diameter DE is always the same. The axial extent b _{RAD of} the leading edge 24 is for example 13.5 mm. Out 6 is also an extending in the axial direction extension a and extending in the radial direction, radial extent b of the leading edge 24 with the trailing edge 26 connecting intermediate edge 27 the impeller blade 22 to recognize. As a result of the corresponding ratios of inlet diameter D _E and outlet diameter DA, it follows that the in 6 shown first embodiment TR-88/72 a trim of 82 having. The second embodiment TR-88/74 has a trim of 84 while the third embodiment TR-88/76 has a trim of 86 having.

9 shows a graph 98 to illustrate possible combinations of the three embodiments of the tongue slider relative to the λ-channel associated Versperrkörper 44 with the three different embodiments of the tongue slider relative to the barrier body associated with the EGR channel 46 ,

In a first column 100 of the chart 98 is the first embodiment S _{0 of} the tongue slider relative to the Versperrkörper 44 enlisted while in a first line 102 the first embodiment S _{0 of} the tongue slider relative to the Versperrkörper 46 is registered. In a column 104 is the second embodiment S _{0 + 10 of} the tongue slider relative to the Versperrkörper 44 enlisted while in a row 106 the second embodiment S _{0 + 10 of} the tongue slider relative to the Versperrkörper 46 is registered. Accordingly, in a column 108 the third embodiment S _{0-10 of} the tongue slider relative to the Versperrkörper 44 enlisted while in a row 110 the third embodiment S _{0-10 of} the tongue slider relative to the Versperrkörper 46 is registered. In the diagram 98 are the same tongue lengths of the locking bodies with G 44 . 46 characterized. In other words, that is on the Versperrkörper 44 related, first embodiment S _{0 of} the tongue slider with the on the Versperrkörper 46 related, first embodiment S _{0 of} the tongue slider combined, so have the Versperrkörper 44 . 46 a same tongue length, each extending up to φ _λ = φ _AGR = 30 °. However, as described above, it may be provided that they are offset by the difference angle Δφ of 23 ° in the circumferential direction of the turbine wheel 16 over whose circumference offset from one another. This means that they overlap each other in the axial direction in a respective sub-area and are arranged in a respective, further sub-area without overlapping each other.

The combination of the first locking body 44 related second embodiment S _{0 + 10} with the on the second Versperrkörper 46 referenced, third embodiment S _0-10 results in a U_λ designated combination with unequal tongue lengths of Versperrkörper 44 . 46 , Accordingly, a combination of the results on the Versperrkörper 44 referenced, third embodiment S _0-10 with the on the Versperrkörper 46 referred second embodiment S _{0 + 10} a designated U_agr combination with unequal tongue lengths of the Versperrkörper 44 . 46 , As already described, there is another possibility of design and variation with regard to the respective exponents ex1 and ex2, the exponent ex1 being located on the λ channel (feed channel 32 ) and the exponent ex2 on the EGR channel (feed channel 34 ).

It thus stands next to the trim of the turbine wheel 16 with the different possible combinations with respect to tongue length and the exponents ex1, ex2 strong impact on the turbine holding, creating at least a 4-dimensional parameter combination in a systematic kit for a desired, adapted and optimal turbine behavior for the corresponding associated, supercharged internal combustion engine by simply replacing the relevant elements is possible. The respective combination options of the different tongue lengths can be represented by a respective variant or embodiment of the tongue slider, these different embodiments preferably optionally with the turbine housing 12 or with the different embodiments of the turbine housing 12 of the kit can be combined. The same applies to the different embodiments TR-88/72, TR-88/74 and TR-88/76 of the turbine wheel 16 to which also optionally with the different embodiments of the turbine housing 12 and can be combined with the different embodiments of the tongue slider.

10 shows a diagram 112 , on the abscissa 114 the adjustment of the tongue slider is applied. Since the tongue slider around the axis of rotation 18 is moved or rotated, the adjustment is a Verstellwinkelbereich.

The adjusting device 42 in the form of the tongue slider is thus adjustable over an adjustment range, which is preferably in the circumferential direction of the turbine wheel 16 extends over its circumference from the closed position up to and including the open position over 80 °. Exactly in the middle between the closed position and the open position, ie at an adjustment angle of 40 ° of the tongue slider, is the said zero position. The adjustment of the tongue slider thus includes angular positions in which the tongue slider is adjustable. In the open position, the angular position is for example 0 °, while the angular position in the closed position relative to the adjustment range is 80 °. In order to set the adjustment range as required, it can be varied by means of a correction factor x °, the correction value x ° preferably being in a range from 0 ° to 10 ° inclusive.

On the ordinate 116 of the diagram 112 is the flow rate parameter of the turbine 10 applied according to a corresponding embodiment. The basis of 10 illustrated embodiment of the turbine 10 includes the tongue slider with the combination G with respect to the respective, on the Versperrkörper 44 . 46 related second embodiment S _{0 + 10} and the turbine wheel according to the second embodiment TR-88 / 74th Furthermore, the exponent ex1 is 2, while the exponent ex2 is 3.

A course 118 illustrates the overall turbine loading, while a course 120 the impingement of the λ-channel and a course 122 illustrates the admission of the EGR channel. The zero position of the tongue slider is in 10 by a dashed line 124 illustrated.

11 shows the diagram 112 , which now turns to another embodiment of the turbine 10 of the modular system relates. The embodiment of the turbine 10 according to 11 includes the tongue slider with the combination G with respect to the respective, on the Versperrkörper 44 . 46 related, second embodiment S _{0 + 10} . The turbine 10 according to 11 includes the turbine wheel 16 according to the second embodiment TR-88/74, which is the basic turbine wheel of the modular system. According to 11 the exponent ex1 is 5, while the exponent ex2 is 5. Like a synopsis of 11 and 10 can be removed, resulting from the corresponding combination of different embodiments, a significant change in the gradients 118 . 120 and 122 ,

12 shows a diagram 126 , on the abscissa 128 the adjustment angle (adjustment) of the tongue slider is applied. On the ordinate 130 is the respective flow angle of the exhaust gas at the respective outlet of the feed channels 32 . 34 applied, this exit is also referred to as a nozzle exit. The basis of 12 illustrated, different embodiments of the turbine 10 each case include the tongue slider with the combination G with respect to the respective, on the Versperrkörper 44 . 46 related third embodiment S _0-10 . The courses 132 . 134 . 136 . 138 . 140 . 142 illustrate a respective course of a flow angle at the respective nozzle exit. In this case, the course refers 132 to the flow angle at the nozzle exit of the λ-channel, wherein the exponent ex1 of the turbine housing 12 the value is 2. The to the course 132 belonging course 136 refers to the flow angle at the nozzle exit of the EGR passage, the exponent ex2 of the turbine housing 12 the value is 3. The history 134 is a cumulative course of the courses 132 and 136 , In other words, the course is 134 formed from the sum of the courses 132 and 136 ,

The history 138 refers to the flow angle at the nozzle exit of the λ-channel, where the exponent ex1 of the turbine housing 12 the value is 5. The history 142 refers to the flow angle at the nozzle exit of the EGR passage, the exponent ex2 of the turbine housing 12 the value is 5. This includes the course 142 to the course 138 , The history 134 is the cumulative course from the course 138 and the course 142 ,

13 the diagram 126 , where the turbine 10 now includes the tongue slider with the combination G with respect to the respective, related to the tongues first embodiment S ₀ .

14 shows the diagram 126 , where the turbine 10 according to 14 now includes the tongue slider with the combination G with respect to the respective, on the tongues related second embodiment S _{0 + 10} . Like from a synopsis of 12 to 14 can be seen, resulting by varying the tongue slider used different courses of the flow angle at the respective nozzle exit.

15 shows the diagram 112 , The turbine 10 according to 15 includes the turbine housing 12 with the exponent ex1 = 2 and the exponent ex2 = 3. Also includes the turbine 10 according to 15 the tongue slider with the combination U_agr with respect to the Versperrkörper 44 referenced, third embodiment S _0-10 and on the Versperrkörper 46 related, second embodiment S _{0 + 10} . This means that the Versperrkörper 44 (λ-tongue) against the Versperrkörper 46 (AGR tongue) is shortened by 20 °. Accordingly, the course relates 120 on the combination U_agr, where the course 118 again the sum course from the courses 120 and 122 is.

Another course 144 in the diagram 112 refers to the tongue slider with the combination G with respect to the respective, on the tongues related third embodiment S _0-10 . Accordingly, a course 146 the cumulative course from the course 144 and the course 122 , Thus, based on the diagram 112 Particularly well the effect can be recognized, which results if instead of the tongue slider with the combination U_agr the tongue slider with the combination G with respect to the respective, related to the tongues third embodiment S _0-10 is used.

16 shows the diagram 112 , where the turbine housing 12 the turbine 10 according to 16 has the exponent ex1 = 2 and the exponent ex2 = 3. The turbine 10 according to 16 includes the tongue slider with the combination U_λ the gradient 122 refers to just this combination U_λ, so that is the Versperrkörper 46 (AGR tongue) opposite the locking body 44 (λ-tongue) is shortened by 20 °. The history 118 is the cumulative course from the course 120 and the course 122 ,

Another course 148 refers to the use of the tongue slider with the combination G with respect to the respective tongues-related third embodiment S _0-10 . The history 146 is again the summation course from the course 120 and the course 148 , Thus, based on 16 Particularly, the difference between the combination U_λ and the combination G with respect to the respective, related to the tongues third embodiment S _0-10 .

Based on the dashed line 124 is in 15 the zero position of the tongue tip 52 of the locking body 46 while illustrated by the dashed line 124 in 16 the zero position of the tongue tip 52 of the locking body 44 is illustrated.

17 shows the diagram 112 , where the turbine 10 according to 17 the turbine housing 12 with the exponent ex1 = 5 and the exponent ex2 = 5. As with the turbine 10 according to 10 . 11 . 15 and 16 includes the turbine 10 the turbine wheel 16 according to the second embodiment TR-88/74 (basic turbine wheel). Furthermore, the turbine includes 10 according to 17 the tongue slider, the respect of the locking body 46 according to the second embodiment S _{0 + 10} and in terms of Versperrkörpers 44 According to the third embodiment S _{0-10 is} formed and thus has the combination U_agr.

Based on the dashed line 124 is - as with 15 - the zero position of the tip of the tongue 52 of the locking body 46 illustrated. The turbine 10 according to 17 includes the turbine housing 12 , which has the exponent ex1 = 5 and the exponent ex2 = 5. The history 120 refers to the described combination U_agr, wherein the λ-tongue is shortened relative to the AGR tongue by 20 °. The history 118 is the cumulative course from the course 120 and the course 122 , The history 144 refers to the combination G on the Versperrkörper 44 related third embodiment S _0-10 with the on the Versperrkörper 46 related third embodiment S _0-10 . Here is the course 146 the cumulative course from the courses 144 and 122 ,

18 shows the diagram 112 , where the turbine 10 according to 18 the basic turbine wheel and the turbine housing 12 with the exponent ex1 = 5 and the exponent ex2 = 5. Furthermore, the turbine includes 10 according to 18 the tongue slider, which now related to the Versperrkörper 46 according to the third embodiment S _0-10 and based on the Versperrkörper 44 S _{0 + 10 is} formed according to the second embodiment.

Based on the dashed line 124 is thus the zero position of the tip of the tongue 52 the λ-tongue is illustrated. In the tongue slider according to 18 Thus, the combination U_λ is provided, in which the AGR tongue is shortened by 20 ° with respect to the λ-tongue. As a result, the history relates 122 on the combination U_λ, where the course 118 the cumulative course from the courses 122 and 120 is. The history 148 again relates to the combination G, in which the tongue slider is formed with respect to the λ-tongue according to the second embodiment S _{0 + 10} and with respect to the AGR tongue also according to the second embodiment S _{0 + 10} . The history 146 is the sum course from the progressions 120 and 148 ,

19 shows the diagram 126 , where the turbine 10 according to 19 includes the tongue slider with the combination U_agr.

20 shows the diagram 126 , which is now on the turbine 10 which includes the tongue slider with the combination U_λ. In comparison with 12 to 14 in which the combination G is provided in each case, the effects of the variations of the tongue slider can be recognized particularly well.

Discrepancies in the respective courses arise through opening phases of the Tongue slider when the tongues move into the spiral spout. The throughput parameter barely changes when the respective movable tongue under the housing tongue 96 is rotated or pushed. In contrast to multi-segment turbines results in the twin-flow turbine by opening the two parallel, ie in the axial direction consecutive tongues relative to the housing tongue 96 Of course, no Umblasequerschnitte between the two floods in the form of feed channels 32 . 34 ,

LIST OF REFERENCE NUMBERS

10

turbine

12

turbine housing

14

accommodation space

16

turbine

18

axis of rotation

20

blading

22

impeller blade

24

leading edge

26

trailing edge

27

intermediate edge

28

entry area

30

exit area

32

feed

33

flange

34

feed

36

wall

38

Nozzle area

40

Nozzle area

42

adjustment

44

Versperrkörper

46

Versperrkörper

48

ring

50

contour piece

52

tongue

54

front

56

supporting

58

graph

60

Base

62

diagram

64

abscissa

66

ordinate

68

Just

70

Just

72

course

74

course

76

course

78

course

80

course

82

course

84

course

86

course

88

course

90

course

92

sealing element

94

subregion

96

housing tongue

98

graph

100

column

102

row

104

column

106

row

108

column

110

row

112

diagram

114

abscissa

116

ordinate

118

course

120

course

122

course

124

dashed line

126

diagram

128

abscissa

130

ordinate

132

course

134

course

136

course

138

course

140

course

142

course

144

course

146

course

A _{S0, AGR}

Inlet cross-section

A _{S0, λ}

Inlet cross-section

S

Centroid

S1

gap

D _A

Outlet diameter

D _A1

Outlet diameter

D _E

Inlet diameter

D _I

Inner diameter

b1

width

b2

width

b3

width

b4

width

b _RAD

axial extent

D ₃

Inlet diameter

α ₀

flow angle

φ _{AGR, 0}

entry angle

φ _{λ, 0}

entry angle

Δφ

difference angle

S ₀

first embodiment

S _{0 + 10}

second embodiment

S _0-10

third embodiment

TR-88/72

first embodiment

TR-88/74

second embodiment

TR-88/76

third embodiment

a

axial extent

b

radial extent

G

combination

U_agr

combination

U_λ

combination

QUOTES INCLUDE IN THE DESCRIPTION

This list of the documents listed by the applicant has been generated automatically and is included solely for the better information of the reader. The list is not part of the German patent or utility model application. The DPMA assumes no liability for any errors or omissions.

Cited patent literature

• DE 102008039085 A1 [0008]
• CN 202500653 U [0009]
• DE 102006051628 A1 [0010]
• WO 2010/068557 A1 [0011]
• WO 2012/170754 A1 [0012]

Claims (10)

Turbine ( 10 ) for an exhaust gas turbocharger, with a turbine housing ( 12 ), which has a receiving space ( 14 ) for one about a rotation axis ( 18 ) relative to the turbine housing ( 12 ) rotatable turbine wheel ( 16 ) and at least two in the axial direction of the turbine wheel ( 16 ) at least partially successive and via respective, in the axial direction successive nozzle cross sections ( 38 . 40 ) in the reception room ( 14 ) feed channels ( 32 . 34 ), characterized in that an adjusting device ( 42 ) is provided, which at least one about the axis of rotation ( 18 ) relative to the turbine housing ( 12 ) displaceable, first locking body ( 44 ) for setting a first ( 38 ) of the nozzle cross sections ( 38 . 40 ) and at least one about the axis of rotation ( 18 ) relative to the turbine housing ( 12 ) displaceable and in the axial direction on the first locking body ( 44 ) following, second locking body ( 46 ) for adjusting the second nozzle cross section ( 40 ). Turbine ( 10 ) according to claim 1, characterized in that the locking bodies ( 44 . 46 ) are different from each other. Turbine ( 10 ) according to claim 2, characterized in that the locking bodies ( 44 . 46 ) with respect to their respective, in the circumferential direction of the turbine wheel ( 16 ) extending along its circumference and / or with regard to their respective position in the circumferential direction of the turbine wheel ( 16 ) over its circumference relative to the turbine housing ( 12 ) and / or with respect to their respective outer contour are different from each other. Turbine ( 10 ) according to one of the preceding claims, characterized in that the locking bodies ( 44 . 46 ) with a coupling element ( 48 ), over which the locking bodies ( 44 . 46 ) simultaneously about the axis of rotation ( 18 ) relative to the turbine housing ( 12 ) are displaceable. Turbine ( 10 ) according to claim 4, characterized in that for mutual sealing of the feed channels ( 32 . 34 ) at least one on the coupling element ( 48 ) and on the other hand at one of the feed channels ( 32 . 34 ) at least in a partial region fluidly separating wall ( 36 ) of the turbine housing ( 12 ) supported sealing element ( 92 ) is provided. Turbine ( 10 ) according to one of the preceding claims, characterized in that the adjusting device ( 42 ) on at least one axial end face ( 54 ) at least one of the Versperrkörpern ( 44 . 46 ) different, additionally provided support element ( 56 ), via which the adjusting device ( 42 ) on the turbine housing ( 12 ) is supported. Turbine ( 10 ) according to one of the preceding claims, characterized in that the nozzle cross sections ( 38 . 40 ) in the circumferential direction of the turbine wheel ( 16 ) are arranged offset over the circumference to each other. Turbine according to one of the preceding claims, characterized in that the respective locking body ( 44 . 46 ) in a position, in particular in an intermediate position, which relative to an adjustment of the respective Versperrkörpers ( 44 . 46 ) in the middle between a respective nozzle cross-section ( 38 . 40 ) maximum opening position and one of the respective nozzle cross section ( 38 . 40 ) maximum narrowing closed position, in the radial direction of the turbine wheel ( 16 ) to the outside at least in a partial area ( 94 ) by a the respective Versperrkörper ( 44 . 46 ) feed channel ( 32 . 34 ) in the radial direction inwardly at least partially delimiting wall ( 96 ) of the turbine housing ( 12 ), the subregion ( 94 ) one in the circumferential direction of the turbine wheel ( 16 ) has over the circumference extending extension and wherein the respective adjustment range, over which the respective Versperrkörper ( 44 . 46 ) is displaceable, at least twice the extent of the subregion ( 94 ). Turbine ( 10 ) according to one of the preceding claims, characterized in that the respective locking body ( 44 . 46 ) in a position, in particular in an intermediate position, which relative to an adjustment of the respective Versperrkörpers ( 44 . 46 ) in the middle between a respective nozzle cross-section ( 38 . 40 ) maximum opening position and one of the respective nozzle cross section ( 38 . 40 ) maximum narrowing closed position, in the radial direction of the turbine wheel ( 16 ) to the outside at least in a partial area ( 94 ) by a the respective Versperrkörper ( 44 . 46 ) feed channel ( 32 . 34 ) in the radial direction inwardly at least partially delimiting wall ( 96 ) of the turbine housing ( 12 ), the subregion ( 94 ) one in the circumferential direction of the turbine wheel ( 16 ) extending extent and wherein the extent of the subregion ( 94 ) at least 10% of a respective, in the circumferential direction of the turbine wheel ( 16 ) extending over the circumference wrapping angle of the corresponding feed channel ( 32 . 34 ) is. Modular system for a turbine ( 10 ) of an exhaust gas turbocharger, with at least one turbine housing ( 12 ), which has a receiving space ( 14 ) for one about a rotation axis ( 18 ) relative to the turbine housing ( 18 ) rotatable turbine wheel ( 16 ) and at least two in the axial direction of the turbine wheel ( 16 ) at least partially successive and via respective, in the axial direction successive nozzle cross sections ( 38 . 40 ) in the reception room ( 14 ) feed channels ( 32 . 34 ), with a first adjusting device ( 42 ) for adjusting the respective nozzle cross section ( 38 . 40 ) and with at least one of the first adjusting device ( 42 ) different, second adjusting device ( 42 ) for adjusting the respective nozzle cross section ( 38 . 40 ), wherein optionally the first adjusting device ( 42 ) or the second adjusting device ( 42 ) in the turbine housing ( 12 ) is mountable.

Images