DE102014217169A1 - Bearing arrangement for an exhaust gas turbocharger - Google Patents

Abstract

The invention relates to a bearing arrangement (1) for an exhaust gas turbocharger, comprising a loader housing (2) with an axial receiving bore (3), at least one radial bearing (6) which can be arranged in the axial receiving bore (3) and which has at least one bearing outer ring (7, 8). wherein on an inner circumferential surface of the bearing outer ring (7, 8) at least one circumferential raceway (10) or sliding layer of the radial bearing (6) is arranged, a partially and rotatably in the bearing outer ring (7, 8) can be arranged rotor shaft (13), at least a with the bearing outer ring (7, 8) cooperating bearing portion (14) and at least one turbine side axially spaced or immediately adjacent to the bearing portion (14) arranged sealing portion (15), wherein on an outer circumferential surface of the sealing portion (15) at least one circumferential sealing groove ( 17) is arranged, and at least one in the sealing groove (17) arranged radial sealing element (18). In order to provide a bearing arrangement (1) for an exhaust-gas turbocharger, with which the exhaust-gas turbocharger can be operated under reduced friction, it is proposed with the invention that the bearing arrangement (1) has at least one intermediate ring (19) arranged at least partially within the axial extent of the receiving bore (3) ) which is rotatably in the charger housing (2) can be arranged and on its inner circumferential surface having a radial sealing element (18) cooperating cylindrical contact surface, wherein an inner diameter of the intermediate ring (19) is smaller than an outer diameter of the bearing outer ring (7, 8).

Description

Field of the invention

• – ein Ladergehäuse mit einer axialen Aufnahmebohrung,
• – wenigstens ein in der axialen Aufnahmebohrung anordenbares Radiallager, das wenigstens einen Lageraußenring aufweist, wobei an einer Innenmantelfläche des Lageraußenrings wenigstens eine umlaufende Laufbahn oder Gleitschicht des Radiallagers angeordnet ist,
• – eine teilweise und drehbar in dem Lageraußenring anordenbare Läuferwelle, die wenigstens einen mit dem Lageraußenring zusammenwirkenden Lagerabschnitt und wenigstens einen turbinenseitig axial beabstandet oder unmittelbar benachbart zu dem Lagerabschnitt angeordneten Dichtabschnitt aufweist, wobei an einer Außenmantelfläche des Dichtabschnitts wenigstens eine umlaufende Dichtnut angeordnet ist, und
• – wenigstens ein in der Dichtnut angeordnetes Radialdichtelement.

The invention relates to a bearing arrangement for an exhaust gas turbocharger, comprising

• A loader housing with an axial receiving bore,
• At least one radial bearing which can be arranged in the axial receiving bore and has at least one bearing outer ring, wherein at least one circumferential raceway or sliding layer of the radial bearing is arranged on an inner lateral surface of the bearing outer ring,
• A rotor shaft which can be arranged partially and rotatably in the bearing outer ring and which has at least one bearing section interacting with the bearing outer ring and at least one axially spaced turbine bore or immediately adjacent to the bearing section, wherein at least one circumferential sealing groove is arranged on an outer lateral surface of the sealing section, and
• - At least one arranged in the sealing groove radial sealing element.

State of the art

An exhaust-gas turbocharger has a turbine wheel, a compressor wheel and a rotor shaft connecting the turbine wheel in a rotationally fixed manner to the compressor wheel. The rotor shaft is rotatably arranged in at least one radial rolling bearing or radial plain bearing in a supercharger housing of the exhaust gas turbocharger.

The DE 10 2010 054 939 A1 discloses a bearing assembly for an exhaust gas turbocharger. In this case, the bearing arrangement comprises a loader housing with an axial receiving bore and arranged in the axial receiving bore radial roller bearing, which is designed to accommodate radial and axial load as a double-row angular contact ball bearings. The radial rolling bearing has two bearing outer rings and a preloaded spring element arranged between the bearing outer rings. On an inner circumferential surface of each bearing outer ring, a raceway is arranged in each case, on which roll the rolling elements of the radial rolling bearing. The bearing arrangement furthermore comprises a rotor shaft which is rotatably arranged in the outer bearing rings and which has a bearing section cooperating with the bearing outer rings and a sealing section axially spaced from the turbine bearing side on the turbine side. On an outer circumferential surface of this sealing portion two circumferential sealing grooves are arranged. The bearing assembly further comprises two arranged in the sealing grooves radial sealing elements.

In such a bearing arrangement, the radial rolling bearing is introduced from the turbine side into the supercharger housing. Here, the diameter of the axial receiving bore must be greater than or equal to the outer diameter of the bearing rings. In a stepped bore course, the receiving bore at its end facing the turbine, on which the sealing portion is provided, have their largest diameter. The sealing portion of the rotor shaft and the radial sealing elements approaching it are to be dimensioned correspondingly large with respect to their radial dimension.

Disclosure of the invention

The object of the invention is to provide a bearing assembly for an exhaust gas turbocharger, with which the exhaust gas turbocharger is operable under reduced friction.

This object is solved by the independent claim. Advantageous embodiments are set forth in particular in the dependent claims, which in themselves or in various combinations with one another may constitute an aspect of the invention.

• – ein Ladergehäuse mit einer axialen Aufnahmebohrung,
• – wenigstens ein in der axialen Aufnahmebohrung anordenbares Radiallager, das wenigstens einen Lageraußenring aufweist, wobei an einer Innenmantelfläche des Lageraußenrings wenigstens eine umlaufende Laufbahn oder Gleitschicht des Radiallagers angeordnet ist,
• – eine drehbar in dem Lageraußenring anordenbare Läuferwelle, die wenigstens einen mit dem Lageraußenring zusammenwirkenden Lagerabschnitt und wenigstens einen turbinenseitig axial beabstandet oder unmittelbar benachbart zu dem Lagerabschnitt angeordneten Dichtabschnitt aufweist, wobei an einer Außenmantelfläche des Dichtabschnitts wenigstens eine umlaufende Dichtnut angeordnet ist,
• – wenigstens ein in der Dichtnut angeordnetes Radialdichtelement, und
• – wenigstens einen zumindest teilweise innerhalb der axialen Erstreckung der Aufnahmebohrung angeordneten Zwischenring, der drehfest im Ladergehäuse anordenbar ist und an seiner Innenmantelfläche eine mit dem Radialdichtelement zusammenwirkende zylindrische Anlagefläche aufweist, wobei ein Innendurchmesser des Zwischenrings kleiner als ein Außendurchmesser des Lageraußenrings ist.

The inventive bearing assembly for an exhaust gas turbocharger comprises

• A loader housing with an axial receiving bore,
• At least one radial bearing which can be arranged in the axial receiving bore and has at least one bearing outer ring, wherein at least one circumferential raceway or sliding layer of the radial bearing is arranged on an inner lateral surface of the bearing outer ring,
• A rotor shaft which can be arranged rotatably in the bearing outer ring and which has at least one bearing section interacting with the bearing outer ring and at least one axially spaced turbine bore or immediately adjacent to the bearing section, at least one circumferential sealing groove being arranged on an outer lateral surface of the sealing section,
• - At least one arranged in the sealing groove radial sealing element, and
• - At least one at least partially disposed within the axial extent of the receiving bore intermediate ring which is rotatably arranged in the charger housing and on its inner circumferential surface cooperating with the radial sealing element cylindrical contact surface, wherein an inner diameter of the intermediate ring is smaller than an outer diameter of the bearing outer ring.

According to the invention, between the sealing portion of the rotor shaft with the arranged in circumferential grooves at least one radial sealing element on the one hand and the charger housing on the other arranged the intermediate ring. The arranged on the sealing portion radial sealing element thus does not come as at DE 10 2010 054 939 A1 with the charger housing, but with the inner circumferential surface of the intermediate ring in contact. As a result, the sealing portion and the radial sealing element can be dimensioned smaller according to the dimensions of the intermediate ring, as it is at DE 10 2010 054 939 A1 is required. A contact surface between the radial sealing element and the intermediate ring is thus smaller than a contact surface between a radial sealing element and the charger housing accordingly DE 10 2010 054 939 A1 ,

With this inventive reduction of the friction surface between the radial sealing element and intermediate ring is opposite DE 10 2010 054 939 A1 a significant reduction in the friction occurring in the operation of a suitably equipped exhaust gas turbocharger in the region of the radial sealing element or intermediate ring connected.

The radial bearing of the bearing assembly according to the invention may be formed as a radial roller bearing or as a radial sliding bearing. In the case of a radial rolling bearing, the bearing outer ring has on its inner circumferential surface at least one circumferential raceway for guiding rolling elements of a row of rolling elements of the radial rolling bearing. In the case of a radial bearing in the form of a radial sliding bearing, the bearing outer ring has at least one circumferential sliding layer on its inner circumferential surface.

The radial bearing may comprise at least one bearing inner ring radially enclosing the rotor shaft, on whose outer lateral surface at least one raceway or sliding layer is arranged. Alternatively, raceways or sliding layers may be provided directly on the outer lateral surface of the bearing section of the rotor shaft.

At the bearing outer ring can be arranged at least one Spritzölbahrung for applying rolling elements and / or the raceways or sliding layers with a lubricating oil. The respective spray oil bore may be communicatively connected to a circumferential groove disposed on the outer circumferential surface of the bearing outer race which is supplied with lubricating oil through at least one supply bore in the charger body. The radial bearing may have two coaxially arranged, correspondingly formed bearing outer rings which are acted upon by a force between them arranged, biased spring element in the axial direction. In addition, the radial bearing can be designed as a double-row angular contact ball bearings or double-row oblique shoulder bearings.

In a radial bearing in the form of a radial roller bearing, the raceway of the bearing section of the rotor shaft via rolling elements interacts indirectly with the arranged on the inner circumferential surface of the bearing outer raceway track. In this case, the raceway may be formed, for example, from a nitriding steel. In the case of a radial bearing designed as a radial slide bearing, the outer circumferential surface of the bearing section of the rotor shaft interacts directly with the sliding layer arranged on the inner lateral surface of the bearing outer ring via a lubricating oil film.

The sealing portion of the rotor shaft is axially spaced turbine side or disposed immediately adjacent to the bearing portion of the rotor shaft. On the outer circumferential surface of the sealing portion and two or more circumferential sealing grooves may be arranged, in each of which a radial sealing element is arranged in order to adapt the sealing effect to the particular application can.

The radial sealing element may be formed as a piston ring. The number of radial sealing elements preferably corresponds to the number of sealing grooves arranged on the sealing section of the rotor shaft.

The bearing assembly may be provided prior to assembly in the charger housing with a turbine wheel, which is connected by means of a joining method, such as friction, electron beam or laser welding, with the rotor shaft. Furthermore, the bearing arrangement may have at least one anti-twist device for preventing a rotation of the bearing outer ring relative to the loader housing. Also, the bearing assembly may include at least one axial stop for limiting axial movement of the bearing outer ring relative to the loader housing.

In addition, the bearing arrangement can have at least one heat-deflecting element which can be arranged on the turbine side, for example a heat-deflecting sheet. As a result, first the manufacture of the rotor shaft, the joining of rotor shaft and turbine wheel and the complete assembly of a bearing unit can be performed. When assembling an exhaust gas turbocharger then only the pre-assembled storage unit must be inserted into the charger housing.

According to an advantageous embodiment, the bearing assembly comprises at least one temperature-resistant sealing ring, wherein on an outer circumferential surface of the intermediate ring at least one circumferential groove is arranged, in which this temperature-resistant sealing ring can be arranged. The temperature-resistant sealing ring may for example be partially or completely formed of brass.

The arrangement of the temperature-resistant sealing ring, which with both the intermediate ring Also comes in contact with the charger housing, improves the tightness of the arrangement formed from these components, so that leakage of lubricating oil in the turbine section of the exhaust gas turbocharger and entry of impurities in the radial bearing region of the exhaust gas turbocharger can be largely avoided.

According to a further advantageous embodiment, at least one circumferential radial flange is arranged on the outer lateral surface of the intermediate ring, wherein an outer diameter of the radial flange is greater than a diameter of the axial receiving bore. The radial flange can be used as an axial end stop, which can be brought into contact with a turbine-side end face of the charger housing.

A further advantageous embodiment provides that the axial receiving bore on the turbine side has a bore portion for at least partially receiving the intermediate ring, which has a radial step relative to the remaining part of the axial receiving bore, wherein a diameter of the bore portion larger than a diameter of the remaining portion of the axial receiving bore is. The radial step of the bore portion forms an axial end stop for the intermediate ring.

According to a further advantageous embodiment, the bearing arrangement comprises at least one can be arranged within the axial receiving bore, which radially surrounds the bearing outer ring. The socket can in this case fulfill the task of a commonly used carrier ring between bearing outer ring and charger housing. At least one radial oil bore can be arranged on the bush, with which lubricating oil can be supplied from a supply bore in the charger housing to a spray oil bore of the bearing outer ring. Here, at least one circumferential groove may be arranged on the outer lateral surface of the bush, which is communicatively connected to the radial oil bore.

Advantageously, the bush is formed integrally with the intermediate ring. As a result, a compact and easy to handle unit is created, whereby the assembly of the bearing assembly is simplified. The bush can be made monolithic with the intermediate ring or be subsequently connected to the intermediate ring.

It is furthermore advantageous if the bush has at least one radial oil drain opening whose dimension is greater than that of the rolling bodies of the radial bearing. In this embodiment, the radial bearing is designed as a radial roller bearing with at least one row of rolling elements. The radial roller bearing may also have at least one roller cage for spaced guiding of the rolling elements. The oil drain opening may be circular or, for example, designed as a slot. In an assembly of the bearing assembly, first, the sleeve can be arranged together with the intermediate ring on the rotor shaft, so that the intermediate ring surrounds the sealing portion at least partially radially. Subsequently, the, preferably spherical, rolling elements can be successively guided through the oil drain opening and thereby brought into position relative to the disposed on the outer circumferential surface of the bearing section of the rotor shaft or a bearing inner raceway and inserted into pockets of a rolling element cage arranged there. Once all rolling elements have been positioned, the bush can be brought into its final position together with the intermediate ring via an axial movement. Consequently, the bearing assembly according to this embodiment can be pre-assembled in a simple manner by the assembly of bush and the associated intermediate ring is used as an assembly aid.

According to a further advantageous embodiment, the radial oil drain opening is arranged on a directly adjacent to the intermediate ring, the turbine-side portion of the socket. This makes the above-described positioning of rolling elements particularly simple, since a turbinenabseitige end face of the intermediate ring can be used as a bearing surface or running surface for the rolling elements.

Advantageously, an end face of the intermediate ring at least partially falls in the direction of the rotor shaft. As a result, an inclined plane is formed, which causes the rolling elements introduced through the oil drain opening guided by the use of their gravity on the sleeve in the direction of their desired end position roll, which further simplifies the assembly of the bearing assembly.

According to a further advantageous embodiment, the bearing arrangement comprises at least one heat-rejecting element, wherein the intermediate ring has a ring section extending outside the axial receiving bore, on which the heat-deflecting element is arranged circumferentially on the circumference. The heat-rejecting element can be designed, for example, as a heat-deflecting sheet. The heat-rejection element protects the radial bearing from the high turbine-side operating temperatures of the exhaust-gas turbocharger.

The invention is not limited to the specified combination of the features of the independent claim and the dependent claims. There are also other possibilities, individual features, especially if They can be combined from the claims, the following description of the embodiments or directly from the figures. In addition, the reference of the claims to the figures by the use of reference numerals is not intended to limit the scope of the claims to the illustrated embodiments.

Preferred embodiments of the invention will be explained in more detail with reference to the accompanying figures. These show:

1 a schematic sectional view of an embodiment of a bearing assembly according to the invention;

2 a schematic sectional view of a mounting state of in 1 shown bearing arrangement;

3 a schematic sectional view of a detail of in 2 shown bearing arrangement;

4 a schematic sectional view of another mounting state of in 1 shown bearing arrangement;

5 a schematic sectional view of another embodiment of a bearing assembly according to the invention;

6 a schematic sectional view of another embodiment of a bearing assembly according to the invention; and

7 a schematic sectional view of another embodiment of a bearing arrangement according to the invention.

Detailed description of the drawings

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

1 shows a schematic sectional view of an embodiment of a bearing assembly according to the invention 1 for an exhaust gas turbocharger, not shown.

The bearing arrangement 1 includes a charger housing 2 with an axial receiving bore 3 , In the charger housing 2 are two supply holes 4 designed for lubricating oil supply. Furthermore, in the charger housing 2 an oil drain gallery 5 designed for discharging lubricating oil. The axial receiving bore 3 has a uniform diameter.

The bearing arrangement 1 further includes a in the axial receiving bore 3 arranged radial bearing 6 in the form of a double-row oblique shoulder bearing or angular contact ball bearing. The radial bearing 6 has two bearing outer rings 7 and 8th on, between which a prestressed spring element 9 is arranged in the form of a plate spring. On an inner circumferential surface of each bearing outer ring 7 respectively. 8th is an all-round career 10 for guiding rolling elements 11 of the radial bearing 6 arranged, arranged in revolving rows of rolling elements and on Wälzkörperkäfigen 12 are guided.

The bearing arrangement 1 also includes a rotatable in the bearing outer rings 7 and 8th arranged rotor shaft 13 , the turbine side with a turbine wheel 29 connected is. The rotor shaft 13 includes one with the bearing outer rings 7 and 8th cooperating bearing section 14 and a turbine side axially spaced from the bearing portion 14 arranged sealing section 15 , On an outer circumferential surface of the bearing section 14 are two groove-shaped circumferential raceways 16 for guiding the rolling elements 11 arranged the respective rolling element row. On an outer circumferential surface of the sealing portion 15 are two circumferential sealing grooves 17 arranged, in each of which a radial sealing element 18 is arranged.

The bearing arrangement 1 also includes a part within the axial extent of the receiving bore 3 arranged intermediate ring 19 , the rotatably in the charger housing 2 is arranged and on its inner lateral surface one with the radial sealing elements 18 having cooperating cylindrical contact surface. An inner diameter of the intermediate ring 19 is smaller than an outer diameter of the bearing outer rings 7 and 8th and an outer diameter of the intermediate ring 19 is greater than or equal to the outer diameter of the bearing outer rings 7 and 8th , The intermediate ring 19 is in the axial receiving bore 3 pressed.

The bearing arrangement 1 further includes one within the axial receiving bore 3 and radially outward circumferentially on the bearing outer rings 7 and 8th arranged socket 20 , which are integral with the intermediate ring 19 connected is. At one to the intermediate ring 19 immediately adjacent, turbine-side section of the socket 20 is a radial oil drain opening 21 arranged, whose dimension is greater than that of the rolling elements 11 of the radial bearing 6 is dimensioned, what made 3 becomes clearer. Likewise will be out 3 more evident that a compressor-side face 22 of the intermediate ring 19 at least partially in the direction of the rotor shaft 13 falls or is conical. The socket 20 is in the axial receiving bore 3 pressed.

The bearing arrangement 1 further includes a heat rejection element 23 in the form of a heat rejection plate, wherein the intermediate ring 19 one outside the axial receiving bore 3 arranged ring section 24 has, on the radially outer circumference of the heat rejection element 23 is arranged.

On the outer surface of the socket 20 are two circumferential grooves 25 arranged communicating with the supply holes 4 are connected. At the socket 20 are also two radial oil holes 26 arranged, each with a circumferential groove 25 communicatively connected. On the outer circumferential surface of each bearing outer ring 7 respectively. 8th each is a circumferential groove 27 arranged. The oil wells 26 are communicating with the circumferential grooves 27 connected. At every bearing outer ring 7 respectively. 8th Furthermore, each is a spray oil hole 28 arranged, each with a circumferential groove 27 is communicatively connected.

The bearing arrangement 1 also includes a radial anti-rotation element 32 placed in a radial hole on the bushing 20 is introduced and partially between the bearing outer rings 7 and 8th extends to a twisting of the socket 20 and the bearing outer rings 7 and 8th relative to the loader housing 2 to prevent.

2 shows a schematic sectional view of a mounting state of in 1 shown bearing assembly 1 with vertically aligned rotor shaft 13 , In this mounting state, the bearing assembly 1 not yet provided with a loader housing and a complete radial bearing, as in 1 is shown. In the mounting state shown was the socket 20 together with the intermediate ring 19 so relative to the rotor shaft 13 positioned that the intermediate ring 19 the upper radial sealing element 18 and a part of the sealing portion 15 radially comprises. At the same time is the heat rejection element 23 on the intermediate ring 19 been arranged. In addition, a Wälzkörperkäfig 12 at the height of the turbine-side career 16 on the outer circumferential surface of the bearing section 14 the rotor shaft 13 positioned. Subsequently, a spherical rolling element 11 according to the arrow 30 through the oil drain opening 21 has been guided, which at least partially in the direction of the rotor shaft 13 sloping axial end face 22 of the intermediate ring 19 in a pocket on the rolling element cage 12 rolled. The other rolling elements 11 can then after progressive rotation of the socket 20 relative to the Wälzkörperkäfig 12 , or vice versa, into the remaining pockets of the rolling element cage 12 be introduced.

3 shows a schematic sectional view of a detail of in 2 shown bearing assembly 1 , It is the dimensions of the oil drain opening 21 and the spherical rolling element 11 to recognize. In addition, at least partially in the direction of the rotor shaft 13 sloping face 22 of the intermediate ring 19 to see, with the in 3 shown part of the axial end face 22 falls to the right.

4 shows a schematic sectional view of another mounting state of in 1 shown bearing assembly 1 , This mounting state is from the in the 2 and 3 shown assembly state brought about by the fact that the socket 20 together with the intermediate ring 19 according to the arrow 31 axially relative to the rotor shaft 13 has been moved so that the intermediate ring 19 both radial sealing elements 18 and at least partially the sealing portion 15 radially surrounds. Furthermore, the anti-rotation element 32 , the bearing outer rings 7 and 8th , the spring element 9 , the second rolling element cage 12 and the rolling elements 11 the second row of rolling elements mounted.

5 shows a schematic sectional view of another embodiment of a bearing assembly according to the invention 1 , This bearing arrangement 1 differs from that in the 1 to 4 shown bearing assembly 1 in that they have a temperature-resistant sealing ring 33 having, wherein on an outer circumferential surface of the intermediate ring 19 at least one circumferential groove 34 is arranged, in which the temperature-resistant sealing ring 33 is arranged. Another difference is that on the outer circumferential surface of the intermediate ring 19 a circumferential radial flange 35 is arranged, wherein an outer diameter of the radial flange 35 larger than a diameter of the axial receiving bore 3 is. Otherwise corresponds to in 5 bearing arrangement shown 1 in the 1 to 4 shown bearing assembly 1 why here on the description of the 1 to 4 is referenced.

6 shows a schematic sectional view of another embodiment of a bearing assembly according to the invention 1 , This bearing arrangement 1 differs thereby from the in 5 shown bearing assembly 1 that the socket 20 not with the intermediate ring 19 connected is. The socket 20 can from the compressor side in the axial receiving bore 3 be introduced. Subsequently, the anti-rotation element 32 be arranged as intended.

7 shows a schematic sectional view of another embodiment of a bearing assembly according to the invention 1 , This bearing arrangement 1 differs thereby from the in 6 shown bearing assembly 1 in that no bush is present and that the axial location hole 3 Turbine side a bore section 36 for receiving the intermediate ring 19 which is opposite to the remaining part 38 the axial receiving bore 3 a radial step 37 having a diameter of the bore portion 36 larger than a diameter of the remaining part 38 the axial receiving bore 3 is. In addition, on the intermediate ring 19 no outer circumferential groove with a temperature-resistant sealing ring and no radial flange available. The bearing outer rings 7 and 8th are in the axial receiving bore 3 pressed.

LIST OF REFERENCE NUMBERS

1

bearing arrangement

2

charger case

3

location hole

4

supply hole

5

Oil drain Gallery

6

radial bearings

7

Bearing outer ring

8th

Bearing outer ring

9

spring element

10

career

11

rolling elements

12

Rolling Element

13

rotor shaft

14

bearing section

15

sealing portion

16

career

17

sealing groove

18

Radial sealing element

19

intermediate ring

20

Rifle

21

Oil drain opening

22

face

23

Hitzeabweiselement

24

ring section

25

groove

26

oil well

27

groove

28

Oil-drilling

29

turbine

30

arrow

31

arrow

32

anti-rotation

33

seal

34

groove

35

flange

36

bore section

37

step

38

remaining part

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 102010054939 A1 [0003, 0008, 0008, 0008, 0009]

Claims (10)

Bearing arrangement ( 1 ) for an exhaust gas turbocharger, comprising - a loader housing ( 2 ) with an axial receiving bore ( 3 ), - at least one in the axial receiving bore ( 3 ) can be arranged radial bearing ( 6 ), the at least one bearing outer ring ( 7 . 8th ), wherein on an inner circumferential surface of the bearing outer ring ( 7 . 8th ) at least one continuous career ( 10 ) or sliding layer of the radial bearing ( 6 ) is arranged - a partially and rotatably in the bearing outer ring ( 7 . 8th ) mountable rotor shaft ( 13 ), which at least one with the bearing outer ring ( 7 . 8th ) cooperating bearing section ( 14 ) and at least one turbine side axially spaced or immediately adjacent to the bearing portion ( 14 ) arranged sealing portion ( 15 ), wherein on an outer circumferential surface of the sealing portion ( 15 ) at least one circumferential sealing groove ( 17 ), and - at least one in the sealing groove ( 17 ) arranged radial sealing element ( 18 ), characterized by - at least one at least partially within the axial extent of the receiving bore ( 3 ) arranged intermediate ring ( 19 ), the rotation in the charger housing ( 2 ) can be arranged and on its inner circumferential surface one with the at least one radial sealing element ( 18 ) has cooperating cylindrical contact surface, wherein an inner diameter of the intermediate ring ( 19 ) smaller than an outer diameter of the bearing outer ring ( 7 . 8th ). Bearing arrangement ( 1 ) according to claim 1, characterized by at least one temperature-resistant sealing ring ( 33 ), wherein on an outer circumferential surface of the intermediate ring ( 19 ) at least one circumferential groove ( 34 ) is arranged, in which the temperature-resistant sealing ring ( 33 ) can be arranged. Bearing arrangement ( 1 ) according to claim 1 or 2, characterized in that on the outer circumferential surface of the intermediate ring ( 19 ) at least one circumferential radial flange ( 35 ), wherein an outer diameter of the radial flange ( 35 ) greater than a diameter of the axial receiving bore ( 3 ). Bearing arrangement ( 1 ) according to claim 1 or 2, characterized in that the axial receiving bore ( 3 ) on the turbine side a bore section ( 36 ) for at least partially receiving the intermediate ring ( 19 ) compared with the rest of the 38 ) of the axial receiving bore ( 3 ) a radial step ( 37 ), wherein a diameter of the bore portion ( 36 ) greater than a diameter of the remaining part ( 38 ) of the axial receiving bore ( 3 ). Bearing arrangement ( 1 ) according to one of claims 1 to 4, characterized by at least one within the axial receiving bore ( 3 ) mountable socket ( 20 ), the at least one bearing outer ring ( 7 . 8th ) encloses radially. Bearing arrangement ( 1 ) according to claim 5, characterized in that the bushing ( 20 ) in one piece with the intermediate ring ( 19 ) is trained. Bearing arrangement ( 1 ) according to claim 5 or 6, characterized in that the bushing ( 20 ) at least one radial oil drain opening ( 21 ) whose dimension is greater than that of the rolling elements ( 11 ) of the radial bearing ( 6 ) is dimensioned. Bearing arrangement ( 1 ) according to claim 7, characterized in that the radial oil drain opening ( 21 ) on one to the intermediate ring ( 19 ) immediately adjacent, turbine-side portion of the bush ( 20 ) is arranged. Bearing arrangement ( 1 ) according to claim 8, characterized in that an end face ( 22 ) of the intermediate ring ( 19 ) at least partially in the direction of the rotor shaft ( 13 ) drops. Bearing arrangement ( 1 ) according to one of claims 1 to 9, characterized by at least one heat-rejecting element ( 23 ), wherein the intermediate ring ( 19 ) one outside the axial receiving bore ( 3 ) extending ring section ( 24 ), on the radially outer circumference of the heat rejection element ( 23 ) is arranged.

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