DE102004062091A1 - Supercharger for internal-combustion engine has axial slide gate valve which exhibits two cut section such that these sections are provided and displaced from each other in circumferential direction around angle which is formed - Google Patents

Abstract

The supercharger has second spiral channel (9) enclosed in the casing (2) and is separated with the first spiral channel (8). The first and second spiral channel are arranged with the first (14) and second guide ends (15) respectively which can be rotated. A slide gate valve (7) exhibits two cut section that are provided and displaced from each other in the circumferential direction around a formed angle. An independent claim is also include for an internal combustion engine.

Description

The The invention relates to an exhaust gas turbocharger for an internal combustion engine the preamble of claim 1 and an internal combustion engine according to the preamble of claim 15.

In the generic patent DE 43 15 474 C1 An exhaust gas turbocharger for an internal combustion engine is described, which comprises a turbine with a spiral channels housing and with an impeller with turbine blades and impeller channels, wherein as impeller channels, the areas between two adjacent turbine blades are designated. The housing has at least one spiral channel with an annular gap opening onto the impeller and a tongue with a tongue end, the tongue separating the beginning and end of the spiral channel as close as possible over the impeller, so that the exhaust gas is completely out of the spiral channel up to the end of the tongue flows into the impeller channels. In order to design the exhaust gas turbocharger in a structurally simple and structurally compact manner, so that a much higher energy is taken off than without regulation and can be used in the impeller with high efficiency for driving the supercharger, especially at low speeds, the annular gap is limited by a shut-off device in a limited, variable sector, which each begins at the tongue, completely shut off just above the impeller. Thus, no exhaust gas can be flowed into the impeller ducts in this shut-off sector.

Of the Invention is based on the object, on the one hand a turbine of a To provide exhaust gas turbocharger whose impeller in the engine brake operation meeting high mechanical and thermal requirements and on the other hand to design an internal combustion engine so that the for the engine braking operation aimed at high braking performance at relatively low thermal Loads of the impeller of the turbine is achieved.

These Task is according to the invention with the Characteristics of claim 1 or of claim 15 solved. The under claims give expedient further education at.

The Invention is based on the idea generated by flow lateral forces mechanical loads of an impeller of a turbine of an exhaust gas turbocharger to lower by a rotation of the spiral channels. The spiral channels become while at an angle γ to a rotation axis of the impeller rotated to each other. By the rotation of the spiral channels grip the flow transverse forces occurring on the impeller no longer one-sided, but opposite so that the transverse flow forces compensate each other can. One in a receiving opening a housing the turbine to reduce the thermal load arranged axial slide indicates the increase in power of the turbine in engine braking mode Internal combustion engine on two axially adjacent cutouts, these two cutouts in the circumferential direction to each other in an angular distance of the angle γ provided are.

In an embodiment according to claim 2, the first cutout and the second cutout have an axial distance S _AB from one another, wherein the axial distance S _AB corresponds to a width B _{T of} a separating wall separating the spiral channels. If the value of the distance S _{AB of} the two cutouts from each other were greater or less than the value of the width B _{T of} the dividing wall, there would be a lossy flow in a flow region located between the spiral passages and the impeller.

In a further embodiment according to claim 3, a cutout start of the cutouts is associated with a specific characteristic cross-sectional area of the associated spiral channel. These characteristic cross-sectional areas cause a spin velocity c _{U of} the flow required for engine braking operation. A first axial cut-out edge of the first cutout is associated with the characteristic cross-sectional areas A _{SA of} the first spiral channel and a second axial cut-out edge of the second cutout is associated with the characteristic cross-sectional area A _{SB of} the second spiral channel.

In a further embodiment according to claim 4, the first section has an opening angle δ _A and the second section an opening angle δ _B , wherein the opening angle δ _{A of} the first section or the opening angle δ _{B of} the second section between the corresponding cross-sectional area A _SA and A _SB and an associated tongue end of the associated spiral channel is included. The opening angle δ _A or the opening angle δ _B defines an area for the flow released on the impeller, which determines the turbine output in engine braking operation in accordance with thermodynamic interpretations.

In a further embodiment according to claim 5, the value of the opening angle δ _A or the value of the opening angle δ _{B is} smaller than 180 °.

In a further embodiment according to An Claim 6 corresponds to a maximum axial width B _{A of} the first section or a maximum axial width B _{B of} the second section of an axial width B _{RA of} a first annular gap or an axial width B _{RB of} a second annular gap, whereby a trouble-free flow can be ensured.

In a further embodiment according to claim 7 have to avoid of flow separation one the partition opposite first Side wall of the first section or one of the partition wall opposite second Side wall of the second section tangential to the first spiral channel adapted, convex curved first radial side wall contour or the second spiral channel tangentially adapted, convexly curved second radial side wall contour on.

In a further embodiment according to claim 8 is for flow guidance the axial slide frontally a ring with an outwardly curved end face intended.

In A further embodiment according to claim 9 has to avoid of flow losses a housing side opposite the axial slide of the housing the turbine a housing contour on, in which the ring with its outwardly arched front sealingly insertable is.

In a further embodiment according to claim 10, the curvature of the end face of the ring of the axial slide and the housing contour of the front side of the axial slide opposite housing side are formed so that they form a tight contact with the low-loss flow in a closed position of the axial slide. In this case, the first cutout releases a partial region of the first annular gap corresponding to the opening angle δ _A , and the second cutout releases a partial region of the second annular gap corresponding to the opening angle δ _B. Through the release of the corresponding subregions of the first and the second annular gap, the turbine power is determined during engine braking operation.

In a further embodiment according to claim 11 is the frontal bulge of the ring of the axial slide designed so that in an open position of the axial slide for trouble-free Flow of Axial slider in the receiving opening is inserted and the frontal curvature of the ring a second housing contour one the receiving opening having housing side rounded off.

In A further embodiment according to claim 12, the first spiral channel and the second spiral channel symmetrical or asymmetrical to the partition wall built up.

In a further embodiment according to claim 13, the angle γ is between 160 ° and 200 °.

In a further embodiment according to claim 14, the angle γ is 180 °.

ergibt. Diese Beziehung führt zu einem Bremsbetrieb mit hohen Bremsleistungen bei relativ geringen thermischen Belastungen des Laufrades. Der Turboladerbremsfaktor T_BF ist erfindungsgemäß kleiner 0,005 und liegt bevorzugt zwischen 0,001 und 0,003. Vorteilhafterweise liegt der Turboladerbremsfaktor T_BF bei 0,002.In a further embodiment according to claim 15, an inlet diameter D _{T of} the impeller, a total volume V _{H of} the internal combustion engine, which is formed from a differential volume of maximum displacement and minimum displacement of the internal combustion engine, the cross-sectional area A _SA and the cross-sectional area A _SB and a Abblasequerschnitt A. _{ABBLASE of} a blower so related to each other that a turbocharger braking factor T _BF according to the relationship

results. This relationship leads to a braking operation with high braking performance at relatively low thermal loads on the impeller. The turbocharger braking factor T _BF according to the invention is less than 0.005 and is preferably between 0.001 and 0.003. Advantageously, the turbocharger braking factor T _BF is 0.002.

Further Advantages and expedient designs The invention are the other claims, the description of the figures and to take the drawings.

It demonstrate:

1 a schematic diagram of an internal combustion engine with an exhaust gas turbocharger according to the invention,

2 a cross section through a double-flow turbine with an axial slide of the exhaust gas turbocharger, wherein the cross section lies within a first spiral channel and shows a first cutout and a first spiral channel cover of the axial slide,

3 a cross section through the twin-flow turbine with the axial slide of the exhaust gas turbocharger, wherein the cross section lies within a second spiral channel and shows a second cutout and a second spiral channel cover of the axial slide,

4 a longitudinal section through the twin-flow turbine of the exhaust gas turbocharger in a closed position of the axial slide,

5 a cross section through the axial slide of the exhaust gas turbocharger and

6 a graphic development of the axial slide of the exhaust gas turbocharger.

In the 1 to 6 are the same or equivalent components provided with the same reference numerals.

In 1 is an internal combustion engine 45 with an exhaust gas turbocharger according to the invention 40 shown. The turbocharger 40 has a double-flow turbine 1 and one with the turbine 1 over a wave 42 rotatably connected compressor 41 on. The turbine 1 is in one of the internal combustion engine 45 associated, a first tide 58 and a second flood 59 having exhaust gas line 49 accommodated.

The internal combustion engine 45 has two exhaust manifold, a first exhaust manifold 56 and a second exhaust manifold 57 up in the exhaust system 49 the internal combustion engine 45 are housed. The first exhaust manifold 56 is with a first spiral channel 8th the turbine 1 over the first tide 58 connected. The second exhaust manifold 57 is with a second spiral channel 9 the turbine 1 over the second flood 59 connected.

The turbine 1 gets out of the internal combustion engine 45 flowing exhaust gas and drives over the shaft 42 the compressor 41 on, in one of the internal combustion engine 45 associated intake tract 48 Suction and compressed combustion air. Downstream of the compressor 41 is a charge air cooler 44 for cooling the combustion air heated in the intake tract as a result of the compression 48 intended.

Downstream of the turbine 1 is an exhaust aftertreatment device 46 intended. For blowing off exhaust gas in front of the turbine 1 is a blow-off valve 55 with a bleed cross section A _ABBLASE in a bypass 54 arranged, the upstream of the turbine 1 from the exhaust system 49 branches. The bypass 54 opens downstream of the turbine 1 back in the exhaust system 49 , The bypass 54 points upstream of the blow-off valve 55 a first bypass connection 60 to the first flood 58 and a second bypass connection 61 to the second flood 59 on.

A control and control unit 47 the internal combustion engine 45 is to control and control indirectly with the exhaust aftertreatment device 46 , the blow-off valve 55 and one in 2 shown axially displaceable axial slide 7 the turbine 1 connected.

An in 2 closer illustrated impeller 3 the turbine 1 is exposed as a result of exposure to the exhaust gas mechanical and thermal loads, wherein the mechanical stresses considered here occur as flow transverse forces of the exhaust gas. These lateral flow forces can have a negative effect on a 1 illustrated rotor bearing 43 an exhaust gas turbocharger 40 have, taking under the rotor bearing 43 a not-shown bearing all peripheral components of the exhaust gas turbocharger 40 to understand. The rotating components of the exhaust gas turbocharger 40 are the compressor 41 , the turbine 1 and the wave 42 , which are collectively referred to as rotor in general.

In 2 is a cross section through the twin-flow turbine 1 with the axial slide 7 the exhaust gas turbocharger 40 shown, wherein the cross section within the first spiral channel 8th lies and the axial slide 7 with a first section 16 and a first spiral channel cover 18 shows. The turbine 1 includes a double-flow housing 2 with the first spiral channel 8th and a second spiral channel 9 as well as the impeller 3 with his in 4 closer illustrated axis of rotation 4 and his in 4 closer illustrated diameter D _T.

The housing 2 indicates an in 2 closer illustrated first spiral channel entrance 10 of the first spiral channel 8th a first tongue 12 with a first tongue end 14 and at a second spiral channel entrance 11 of the second spiral channel 9 a second tongue 13 with a second tongue end 15 on. The tongues 12 . 13 separate with their tongue ends 14 . 15 a spiral channel beginning and a spiral channel end of the associated spiral channel 8th . 9 , where a first spiral channel beginning 81 and a first spiral channel end 82 the first spiral channel 8th and a second spiral channel beginning 91 and a second spiral channel end 92 the second spiral channel 9 assigned. At the spiral channel ends 82 and 92 have the tongues 12 and 13 one tongue underside each, a first tongue underside 36 and a second tongue base 37 ,

The tongue ends 14 and 15 the tongues 12 . 13 are at an angle γ about the axis of rotation 4 of the impeller 3 arranged rotated against each other. The angle γ in this embodiment is 180 °, with an angle γ in the range between 160 ° and 200 ° is possible.

Between the first spiral channel 8th or the second spiral channel 9 and the impeller 3 is concentric around the impeller 3 arranged axial slide 7 for influencing the flow direction and flow velocity. The axial slide 7 is sleeve-shaped.

In 3 is a cross section through the twin-flow turbine 1 with the axial slide 7 the exhaust boladers 40 shown, wherein the cross section within the second spiral channel 9 lies and the axial slide 7 with a second cutout 17 and a second spiral channel cover 19 shows.

In 4 is a longitudinal section of the turbine 1 with the axial slide 7 shown in a closed position. The two spiral channels 8th . 9 are from a partition 20 with an axial width B _T in the housing 2 separated from each other. They each have one on the impeller 3 opening annular gap on, a first annular gap 5 and a second annular gap 6 , The first annular gap 5 of the first spiral channel 8th has a width B _RA . The second annular gap 6 of the second spiral channel 9 has a width B _RB .

The axial slide 7 is in a case 2 between the spiral channels 8th . 9 and the impeller 3 provided receiving opening 32 accommodated displaceable. The first part 16 of the axial slide 7 has a width B _A , wherein this axial width B _{A of} the axial width B _{RA of} the first annular gap 5 equivalent. An axial width B _{B of} the second section 17 of the axial slide 7 corresponds to the axial width B _{RB of} the second annular gap 6 ,

One of the dividing wall 20 of the housing 2 opposite first side wall 21 of the first section 16 has a first spiral channel 8th tangentially adapted, convexly curved first radial side wall contour 23 on and it has one of the dividing wall 20 opposite second side wall 22 of the second section 17 a second spiral channel 9 tangentially adapted, convexly curved second radial side wall contour 24 on.

At the axial slide 7 is a contour ring at the front 30 with a convexly curved ring contour 31 intended. The axial slide 7 front side opposite housing side 26 of the housing 2 has a concave first housing contour 33 on, with the inward curvature of the concave first housing contour 33 the outward curvature of the convex ring contour 31 of the contour ring 30 Similar to a matrix and its negative image, its counterpart corresponds to the patrix, leaving the contour ring 30 with its ring contour 31 in the opposite side of the housing 26 with its first housing contour 33 is inserted sealingly.

In the illustrated closed position of the axial slide 7 is the axial slide 7 in the opposite side of the housing 26 pushed in, leaving the first section 16 partly the first annular gap 5 and the second section 17 partly the second annular gap 6 releases. The cutouts 16 . 17 unreleased parts of the annular gap 6 . 7 are from the spiral channel covers 18 . 19 covered.

In an open position of the axial slide, not shown 7 is the axial slide 7 so far to the right in the receiving opening 32 pushed in until the contour ring 30 with its convex curved ring contour 31 a second housing contour 35 one the receiving opening 32 having housing side 27 completed in rounded form.

In 5 is a cross section through the axial slide 7 shown. The cross section shows the first section 16 and the second section 17 of the axial slide 7 , where the first section 16 an opening angle δ _A or the second section 17 has an opening angle δ _B. The first part 16 points at the circumference of the axial slide 7 a first axial cut-out edge 50 on, which is a beginning of the first section 16 features. The second section 17 points at the circumference of the axial slide 7 a second axial cut-out edge 52 on, the beginning of a section of the second section 17 features. A cutout end of the cutouts 16 . 17 is by a third axial cut-out edge 51 or a fourth axial cut-out edge 53 on the circumference of the axial slide 7 characterized. The two axial cut-out edges 50 . 51 close the opening angle δ _{A of} the first section 16 one. The two axial cut-out edges 52 . 53 close the opening angle δ _{B of} the second section 17 one. The opening angles δ _A and δ _B have an amount of 60 ° in this embodiment.

In 5 illustrated side walls 500 . 510 . 520 . 530 the first and the second section 16 . 17 are arcuate, wherein the respective arch shape of an arc shape of the tongue undersides 36 . 37 the tongues 12 . 13 is additionally adjusted. These side wall shapes allow a separation-free flow pattern.

Starting from the axial cut-out edges 50 and 52 are the two opening angles δ _A and δ _B offset by the angle γ to each other. The size of the opening angle δ _{A of} the first section 16 or the opening angle δ _{B of} the second section 17 results from thermodynamic design calculations or principle measurements of a braking characteristic of the turbine 1 in engine braking mode the in 1 shown internal combustion engine 45 ,

The axial cut-out edges 50 . 51 . 52 and 53 the cutouts 16 . 17 mark on the axial slide 7 characteristic cross-sectional areas of the spiral channels 8th . 9 , The axial cut-out edges 50 and 52 the first and the second section 16 . 17 mark those to the corresponding tongue ends 14 . 15 the tongues 12 . 13 belonging cross-sectional areas A _{SA, 0} , A _{SB, 0} in the spiral channel entries 10 . 11 the spiral channels 8th . 9 , The axial section edge 51 and 53 the first and the second section 16 . 17 Mark cross-sectional areas A _SA , A _{SB of} the spiral channels 8th . 9 , These cross-sectional areas A _SA , A _SB perform a certain, for an engine braking operation of the internal combustion engine 45 required spin velocity c _{U of} a flow at the impeller 3 cause.

In 6 is a graphic development of the axial slide 7 shown. The first part 16 and the second section 17 have an axial distance S _AB from each other, about the width B _{T of} the partition 20 equivalent.

To the rotor bearing 43 the turbine 1 in the engine braking operation, not to be burdened on one side by the occurring transverse flow forces, the second spiral channel 9 opposite the first spiral channel 8th arranged twisted by the angle γ, so that the on the turbine 1 can compensate for occurring transverse flow forces. Thus, the characteristic for the engine braking operation cross-sectional areas A _SA , A _{SB of} the associated spiral channels 8th . 9 will be released, also the two sections 16 and 17 rotated by the angle γ to each other in the axial slide 7 except. A trouble-free and separation-preventing flow of the exhaust gas is through the spiral channels 8th . 9 tangentially adapted, convexly curved radial side wall contours 23 . 24 and the on the axial slide 7 provided contour ring 30 achieved.

If the distance S _{AB of} the two sections 16 . 17 each other significantly larger or smaller than the width B _{T of} the partition 20 , so would be in the flow area between the spiral channels 8th . 9 and the impeller 3 a significant lossy flow before, because protruding or indented edges of the cutouts 16 . 17 could lead to flow separation. The axial widths B _A , B _{B of} the cutouts 16 . 17 are for trouble-free flow to the axial widths B _RA , B _{RB of} the annular gaps 5 . 6 adapted executed.

In the in 4 illustrated closed position of the axial slide 7 in the turbine 1 becomes the wheel 3 only from the released clippings 16 . 17 of the axial slide 7 flowing exhaust gas applied. From those of the spiral channel covers 18 . 19 of the axial slide 7 enclosed areas of the spiral channels 8th . 9 no exhaust gas flows on the impeller 3 , The closed position of the axial slide 7 is predominantly used in engine braking mode in 1 shown internal combustion engine 45 applied. The axial slide 7 covered in engine braking with its spiral channel covers 18 . 19 a part of the spiral channels 8th . 9 so that's the impeller 3 acting exhaust gas only through the cutouts 16 . 17 can flow. One through the spiral channel covers 18 . 19 induced area reduction of the impeller inflow area of one the complete circumference of the impeller 3 releasing impeller airflow on only one of the cutouts 16 . 17 Released Laufradanströmfläche, causes an increase in speed, pressure and temperature of the impeller 3 acting exhaust gas. This will increase the performance of the turbine 1 increased. An increased performance of the turbine 1 leads to an increased speed of the rotationally fixed over the shaft 42 with the turbine 1 connected compressor 41 so that from the compressor 41 promoted combustion air quantity can be increased. The increase in the amount of combustion air conveyed leads to an increase in the braking power during engine braking operation of the internal combustion engine 45 ,

In normal operation of the internal combustion engine 45 is the axial slide 7 in the receiving opening 32 pushed in so far that the ring contour 31 of the contour ring 30 the second housing contour 35 the receiving opening 32 having housing side 27 rounded off. The spiral channels 8th . 9 be from the axial slide 7 fully released, leaving the exhaust the impeller 3 over the full circumference of the impeller 3 can apply.

In the embodiment of the exhaust gas turbocharger according to the invention is the exhaust gas turbocharger 40 with a twin-bladed turbine 1 equipped, their spiral channels 8th . 9 symmetrical to the partition 20 are constructed. For force compensation on the impeller 3 the angle γ is suitable with a value of 180 °, with a deviation of 20 ° is possible. The axial widths B _A and B _{B of} the cutouts 16 . 17 have the same values. Also, the opening angle δ _A and δ _B cutouts 16 . 17 have the same values.

Likewise, it could be at the turbine 1 around a twin-bladed turbine 1 act, their spiral channels 8th . 9 asymmetrical to the partition 20 are constructed. In this case, the opening angles δ _A and δ _B or the widths B _A and B _{B would} not necessarily be the same size. It would have to be determined two different sized cross-sectional areas A _SA , A _SB , the obtained spin velocities c _u flow transverse forces have compensating effects on the flow. It applies to asymmetric turbines in addition to the appropriate cross-sectional areas A _SA , A _SB opening widths B _A and B _{B of} the cutouts 16 and 17 to determine the desired turbine power of the turbine 1 in engine braking mode.

Likewise, it could be at the turbine 1 around a twin-bladed turbine 1 act whose spiral channel entries 10 . 11 lie in the same plane. Then it's for one of the spiral channels 8th ; 9 the spiral channel start 81 ; 91 the corresponding spiral channel 8th ; 9 with its from the spiral channel entry 10 ; 11 to the associated tongue end 14 ; 15 constant cross-section area A _{SA, 0} ; A _{SB, 0} to extend such that the associated tongue ends 14 . 15 are offset by the angle of rotation γ to each other.

wobei T_BF einen Turboladerbremsfaktor bildet, der kleiner 0,005 ist und bevorzugt zwischen 0,001 und 0,003, insbesondere bei 0,002 liegt.By the present invention, design specifications are defined between the internal combustion engine 45 , the turbocharger 40 and an achievable engine braking power, with the aim of the lowest possible mechanical and thermal load on the exhaust gas turbocharger 40 , In this case, a total volume V _{H of} the internal combustion engine determined from the difference between the maximum and the minimum displacement of the cylinder not shown in detail 45 , the diameter D _{T of} the impeller 3 and the cross sections A _SA and A _SB and the Abblasequerschnitt A _ABBLASE a special meaning. The connection to an internal combustion engine 45 with turbocharger 40 leads, in which for braking operation high braking performance associated with relatively low mechanical and thermal loads, is as follows:

wherein T _BF forms a turbocharger braking factor that is less than 0.005 and preferably between 0.001 and 0.003, more preferably 0.002.

Claims (17)

Exhaust gas turbocharger ( 40 ) for an internal combustion engine ( 45 ), with one in a housing ( 2 ) accommodated turbine ( 1 ), which is an impeller ( 3 ) with a rotation axis ( 4 ), the housing ( 2 ) a first spiral channel ( 8th ) with one to the impeller ( 3 ) opening first annular gap ( 5 ), a first tongue ( 12 ) with a first end of the tongue ( 14 ) and a receiving opening ( 32 ) with an associated axial slide ( 7 ), characterized in that in the housing ( 2 ) at least one second spiral channel ( 9 ) formed by a partition wall ( 20 ) in the housing ( 2 ) from the first spiral channel ( 8th ) is separated, wherein the second spiral channel ( 9 ) with its second tongue ( 13 ) with her second tongue end ( 15 ) with respect to the first spiral channel ( 8th ) with associated first tongue end ( 14 ) by an angle γ about the axis of rotation ( 4 ) is arranged twisted, and the axial slide ( 7 ) has at least two axially adjacent cutouts, a first cutout ( 16 ) and a second section ( 17 ), which are provided offset in the circumferential direction by the angle γ from each other. Exhaust gas turbocharger according to claim 1, characterized in that the first section ( 16 ) and the second section ( 17 ) are axially spaced, wherein the value of the distance S _{AB is} about the value of the width B _{T of} the partition ( 20 ) between the spiral channels ( 8th . 9 ) corresponds. Exhaust gas turbocharger according to claim 1 or 2, characterized in that a first axial cut-out edge ( 50 ) of the first section ( 16 ) or a second axial cut-out edge ( 52 ) of the second section ( 17 ) a section start of the associated section ( 16 . 17 ), wherein at the periphery of the axial slide ( 7 ) the first axial cut-out edge ( 50 ) has a cross-sectional area A _{SA of} the first spiral channel ( 8th ) or the second axial cut-out edge ( 52 ) has a cross-sectional area A _{SB of} the second spiral channel ( 9 ). Exhaust gas turbocharger according to claim 3, characterized in that the first section ( 16 ) an opening angle δ _A and the second section ( 17 ) has an opening angle δ _B , wherein the opening angle δ _{A of} the first section ( 16 ) or the opening angle δ _{B of} the second section ( 17 ) between the corresponding cross-sectional area A _SA or A _SB and the associated tongue end ( 14 . 15 ) of the associated spiral channel ( 8th . 9 ) is included. Exhaust gas turbocharger according to claim 4, characterized in that the opening angles δ _A , δ _{B are} smaller than 180 °. Exhaust gas turbocharger according to claim 1, characterized in that a maximum axial width B _{A of} the first section ( 16 ) or a maximum axial width B _{B of} the second section ( 17 ) an axial width B _{RA of} the first annular gap ( 5 ) or an axial width B _{RB of} the second annular gap ( 6 ) corresponds. Exhaust gas turbocharger according to claim 1, characterized in that to avoid flow separation one of the partition wall ( 20 ) opposite first side wall ( 21 ) of the first section ( 16 ) or one of the partition ( 20 ) opposite second side wall ( 22 ) of the second section ( 17 ), a first spiral channel ( 8th ) tangentially adapted, convexly curved first radial side wall contour ( 23 ) or a second spiral channel ( 9 ) tangentially adapted, convexly curved radial second side wall contour ( 24 ) having. Exhaust gas turbocharger according to claim 1, characterized in that for flow guidance of the axial slide ( 7 ) a ring on the front side ( 30 ), whose end face is curved outwardly. Exhaust gas turbocharger according to claim 8, characterized in that a the axial slide ( 7 ) front side opposite housing side ( 26 ) of the housing ( 2 ) one the ring ( 30 ) adapted first housing contour ( 33 ) having. Exhaust gas turbocharger according to claim 9, characterized in that the curvature of the ring ( 30 ) of the axial slide ( 7 ) and the first housing contour ( 33 ) of the front side opposite housing side ( 26 ) are formed so that they in a closed position of the axial slide ( 7 ) make a close contact and the first section ( 16 ) the first annular gap ( 5 ) partially releases and the second section ( 17 ) the second annular gap ( 6 ) partially releases. Exhaust gas turbocharger according to one of claims 8 to 10, characterized in that the curvature of the ring ( 30 ) of the axial slide ( 7 ) is designed so that in an open position of the axial slide ( 7 ) the ring ( 30 ) a second housing contour ( 35 ) one the receiving opening ( 32 ) housing side ( 27 ) of the housing ( 2 ) rounded off. Exhaust gas turbocharger according to claim 1, characterized in that the first spiral channel ( 8th ) and the second spiral channel ( 9 ) symmetrical or asymmetrical to the partition wall ( 20 ) are constructed. Exhaust gas turbocharger according to claim 1, characterized in that that the angle γ is between 160 ° and 200 °. Exhaust gas turbocharger according to claim 13, characterized in that that the angle γ is 180 °. Internal combustion engine ( 45 ) with an exhaust gas turbocharger ( 40 ) according to one of claims 1 to 14, characterized in that for speed increase in engine braking operation at maximum braking power of the internal combustion engine ( 45 ) - a diameter D _{T of} the impeller ( 3 ), - a stroke volume V _{H of} the internal combustion engine ( 45 ), - the cross-sectional areas A _SA , A _{SB of} the spiral channels ( 8th . 9 ) and - a blow-off cross-section A _{ABBLASE of} a blow-off valve ( 55 ) in the following relationship:

where T _BF as turbocharger braking factor is less than 0.005. Internal combustion engine according to claim 15, characterized in that the turbocharger braking factor T _{BF is} between 0.001 and 0.003. Internal combustion engine according to claim 16, characterized in that the turbocharger braking factor T _BF is 0.002.