EP1734231B1 - Turbocharger with variable geometry turbine - Google Patents

Description

The invention relates to a turbocharger according to the preamble of claim 1. Such a turbocharger is known from EP 0 204 033 A known.

Another turbocharger is from the EP 1 394 364 A1 known.

In this turbocharger design, the vane ring is provided with spacers to maintain a clearance for the vanes of a baffle. In order to fix the blade bearing ring on the turbine housing, the spacers of the blade bearing ring are each provided with a bore for connecting bolts. In the assembled state, the connecting bolts pass through the holes and engage in a bearing ring of the turbine housing arranged adjacent to the blade bearing ring.

It is accordingly an object of the present invention to provide a turbocharger according to the preamble of claim 1, which allow a simplification of assembly by reducing the items to be assembled.

The solution of this object is achieved by the features of claim 1. The inventive one-piece design of the fastening device for fixing the blade bearing ring to the spacers thereof, it is possible to both the attachment of holes in the spacers and the provision and mounting of separate connecting pin without.

Rather, in the course of the arrangement of the blade bearing ring whose fixation can be achieved by engaging mating surfaces of the fastening device of the blade bearing ring and corresponding mating surfaces on the turbine housing.

An embodiment of the invention provides as a fastening device before a radially aligned centering surface, which forms a press fit with a suitably arranged and formed counter surface of the turbine housing in the assembled state. Radial alignment in this context means that the centering surface has radially inwardly with respect to the axis of rotation of the turbine rotor, wherein the mating surface of the turbine housing accordingly faces radially outward.

The dependent claims have advantageous developments of the invention to the content.

In forming the fastener as a press fit, it is also possible to provide additional axial securing of the vane ring by cooperating with a disc assembly disposed between the turbine housing and the bearing housing of the turbocharger. This disc arrangement can be formed in a particularly preferred embodiment by a arranged on the side of the bearing housing disc spring and a heat shield, which faces the turbine housing.

For applications in the low temperature range, in which the turbine housing is formed of a material which has a low temperature resistance, it is possible to arrange an insert disk of particularly temperature-resistant material for protecting the guide vanes between the blade bearing ring and the turbine housing.

Further details, features and advantages of the invention will become apparent from the following description of exemplary embodiments with reference to the drawings.

Fig. 1:

eine teilweise im Schnitt dargestellte Perspektivansicht eines erfindungsgemäßen Turboladers,

Fig. 2:

eine perspektivische Ansicht eines nicht erfindungsgemäßen Schaufellagerrings,

Fig. 3:

eine Teilansicht des Schaufellagerrings gemäß Fig. 2,

Fig. 4:

eine Teilansicht des nicht erfindungsgemäßen Turboladers zur Verdeutlichung des Montagezustandes des Schaufellagerrings gemäß der Fig. 2 und 3,

Fig. 5 und 6:

der Fig. 4 entsprechende Darstellungen des erfindungsgemäßen Turboladers zur Verdeutlichung einer Ausführungsform des erfindungsgemäßen Schaufellagerrings, und

Fig. 7:

eine der Fig. 5 entsprechende Darstellung eines Teiles des erfindungsgemäßen Turboladers zur Verdeutlichung einer weiteren Ausführungsform.

It shows:

Fig. 1:

a partially sectioned perspective view of a turbocharger according to the invention,

Fig. 2:

a perspective view of a non-inventive blade bearing ring,

3:

a partial view of the blade bearing ring according to Fig. 2 .

4:

a partial view of the non-inventive turbocharger to illustrate the mounting state of the blade bearing ring according to the FIGS. 2 and 3 .

5 and 6:

of the Fig. 4 corresponding representations of the turbocharger according to the invention to illustrate an embodiment of the blade bearing ring according to the invention, and

Fig. 7:

one of the Fig. 5 corresponding representation of a part of the turbocharger according to the invention to illustrate a further embodiment.

In Fig. 1 a turbocharger 1 according to the invention is shown, which has a turbine housing 2 and a compressor housing 3 connected thereto via a bearing housing 28. The housings 2, 3 and 28 are arranged along a rotation axis R. The turbine housing is shown partially in section to illustrate the arrangement of a vane ring 6 and a radially outer vane 18 formed therefrom which has a plurality of circumferentially spaced vanes 7 with pivot axes 8. As a result, nozzle cross-sections are formed, which are larger or smaller depending on the position of the guide vanes 7 and apply more or less to the located in the middle of the axis of rotation R turbine rotor 4 with the supplied via a feed channel 9 and discharged via a central port 10 exhaust gas of an engine to drive via the turbine rotor 4 a seated on the same shaft compressor motor 17.

In order to control the movement or the position of the guide vanes 7, an actuating device 11 is provided. This can be designed to be arbitrary, but a preferred embodiment, a control housing 12, which controls the control movement of a ram member 14 attached to her to implement the movement thereof to a located behind the blade bearing ring 6 adjusting 5 in a slight rotational movement of the same. Between the vane ring 6 and an annular part 15 of the turbine housing 2, a clearance 13 for the vanes 7 is formed. In order to secure this space 13, the blade bearing ring 6 integrally molded spacers 16, which in detail in FIGS. 2 and 3 are shown. In the example case, three spacers 16 are arranged at an angular distance of 120 ° in each case on the circumference of the blade bearing ring 6. In principle, it is possible to provide more or less such spacers 16, but results in accordance with the training Fig. 2 a particularly advantageous geometric arrangement.

In the Fig. 2 to 4 a vane bearing ring 6 is shown, which has a fastening device 19 for fixing the vane bearing ring 6 on the turbine housing 2, which in one piece at least one of the spacers 16 is arranged. In the embodiment shown in these figures, the fastening device 19 has a groove 20 which is arranged between a, preferably cylindrically shaped, main part 22 of the spacer 16 and a centering shoulder 23. As can be seen from the detailed view of Fig. 3 results in the main part 22 due to the one-piece design in the blade bearing ring 6 and the Zentrierabsatz 23 is disposed at the free end of the spacer 16. By attaching the groove 20 between the main part 22 and the centering 23, the results Fig. 3 in detail apparent hook shape. As Fig. 3 also clarified, the centering shoulder 23 is provided with respect to the main body 22 with a shoulder, so that adjacent to the groove 20, an axial bearing surface 24 and a radially aligned centering surface or a centering result.

Im in Fig. 4 shown mounting state engages a web 21 of the turbine housing 2 in the groove 20 and thus forms a bayonet-like closure device for fixing the vane bearing ring 6 on the turbine housing. 2

For this purpose and for the formation of the vane bearing ring according to the embodiments of Fig. 2 to 4 In addition to the written description, reference is explicitly made to the graphic representation of the aforementioned figures.

In the FIGS. 5 and 6 an inventive turbocharger 1 and an inventive blade bearing ring 6 is shown.

This embodiment has a fastening device 19 ', which instead of a groove on at least one of the spacers 16 and a corresponding web on the turbine housing 2 has a radially aligned centering surface 26 at least one of the spacers 16, which in the in the FIGS. 5 and 6 shown assembled state with a mating surface 27 of the turbine housing 2. By this interaction, a press fit in the radial direction is achieved, which is sufficient in principle to fix the blade bearing ring 6 on the turbine housing 2.

To support the fixation is in the in the FIGS. 5 and 6 Particularly preferred embodiment further comprises a projection 29 which is arranged on an inner peripheral surface 30 of the blade bearing ring 6, which in detail from the FIGS. 5 and 6 results.

The projection 29 in this case has radially inward, ie in the direction of the axis of rotation R, and is arranged at the axial end 31 of the blade bearing ring 6, which is the spacers 16 adjacent. This projection 29, which forms a radially encircling collar, cooperates with a disc assembly 32, which is mainly from the enlarged view of Fig. 6 is apparent.

In the illustrated embodiment, the disc assembly 32 has a conical disc spring 33 and a heat shield 34 disposed on sides of the turbine housing 2.

Due to the fact that the disk arrangement 32 rests on the projection 29 at its radially outer end, it is possible during assembly for an axial force F (see FIG Fig. 5 ), which makes an additional axial clamping of the blade bearing ring 6 possible. In Fig. 7 an arrangement is shown, that of the FIGS. 5 and 6 largely corresponds, so that reference can be made to the above explanation.

It concerns with the Fig. 7 However, to one embodiment of the turbocharger 1, which is intended for a low-temperature use, in which, accordingly, the material of the turbine housing 2 may have lower temperature resistance.

However, in order to protect the guide vanes 7, a high-temperature resistant insert 35 is provided between the blade bearing ring 6 and the turbine housing 2, which is shown in detail from the illustration of Fig. 7 results.

LIST OF REFERENCE NUMBERS

1

turbocharger

2

Tubinengehäuse

3

compressor housing

4

turbine rotor

5

adjusting

6

Nozzle ring

7

vanes

8th

swiveling axes

9

feed

10

Axialstutzen

11

actuator

12

control housing

13

Free space for vanes 7

14

plunger member

15

annular part of the turbine housing 2

16

Spacer / spacer cams

17

compressor rotor

18

guide grid

19

fastening device

20

groove

21

web

22

Bulk

23

centering

24

axial contact surface

25

Centering or centering diameter of the spacer

26

centering

27

counter surface

28

bearing housing

29

head Start

30

Inner circumferential surface

31

axial end

32

disk assembly

33

Belleville spring

34

heat shield

35

insert disc

R

axis of rotation

F

axial preload force

Claims (5)

1. Turbocharger (1) with variable turbine geometry (VTG),

   - having a turbine housing (2) with a feed duct (9) for exhaust gases;

   - having a turbine rotor (4) which is rotatably mounted in the turbine housing (2);

   - having a guide baffle (18) of variable turbine geometry, which surrounds the turbine rotor (4) radially at the outside and which has a blade bearing ring (6) which is equipped with spacers (16) for maintaining a free space (13) for guide blades (7) of the guide baffle (18); and

   - having a fastening device (19; 19') which is formed integrally on at least one of the spacers (16) and which serves for the fixing of the blade bearing ring (6) to the turbine housing (2),
   characterized

   - in that the fastening device (19') is formed as a radially oriented centering surface (26) which, in the installed state of the blade bearing ring (6), forms an interference fit with a counterpart surface (27) of the turbine housing (2).
2. Turbocharger according to Claim 1, characterized in that the blade bearing ring (6) has a radially inwardly protruding projection (29) on its inner circumferential surface (30).
3. Turbocharger according to Claim 2, characterized in that the projection (29) is arranged on that axial end (31) of the blade bearing ring (6) which is adjacent to the spacers (16).
4. Turbocharger according to Claim 2 or 3, characterized in that the projection (29) interacts, in the installed state of the blade bearing ring (6), with a disk arrangement (32), preferably composed of a disk spring (33) and a heat shield (34) facing toward the turbine housing (2), in order to generate axial bracing of the blade bearing ring (6) between the bearing housing (28) and the turbine housing (2).
5. Turbocharger according to one of Claims 1 to 4, characterized in that a washer (35) is arranged between the turbine housing (2) and the blade bearing ring (6).

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