NOZZLE RING FOR A RADIAL TURBINE AND EXHAUST GAS TURBOCHARGER INCLUDING THE SAME

Abstract

A nozzle ring (10) for a radial turbine is described. The nozzle ring includes a disc-shaped main body (11) having a central opening (12) for passing a shaft there through. Additionally, the nozzle ring includes guide vanes (14) disposed circumferentially in a radially outer portion on a first surface (11A) of the main body (11). Two or more bores (17) are provided in a radially inner portion el of the main body (11). Further, a groove (171) is provided in the first surface (11A) of the main body (11), the groove (171) connecting at least two of the two of more bores (17).

Claims

1. A nozzle ring for a radial turbine comprising: a disc-shaped main body having a central opening for passing a shaft there through; guide vanes disposed circumferentially in a radially outer portion on a first surface of the main body; two or more bores provided in a radially inner portion of the main body; and a groove provided in the first surface of the main body, the groove connecting at least two of the two of more bores.

2. The nozzle ring of claim 1, wherein the groove extends at least partially concentrically around the central opening.

3. The nozzle ring of claim 1, wherein the groove is a closed-loop groove.

4. The nozzle ring of claim 1, wherein the two or more bores are arranged on a first virtual circle line having a first radius R.sub.1 around the central opening, and wherein the guide vanes are arranged on a second virtual circle line having a second radius R.sub.2 around the central opening, wherein the second radius R.sub.2 is R.sub.2≥1.5×R.sub.1.

5. The nozzle ring of claim 1, the groove having a cross-sectional shape selected from the group consisting of: a rectangular U-shape, a square U-shape, a round U-shape, and a cone-like shape.

6. The nozzle ring of claim 1, the groove having a width W and a depth D, the width being larger than or equal to the depth (W≥D).

7. The nozzle ring of claim 1, the groove having a width W and a depth D, the depth being larger than or equal to the width (D≥W).

8. The nozzle ring of claim 1, the groove having a width W of 2 mm≤W≤10 mm and a depth D of 0.4 mm≤D≤10 mm.

9. The nozzle ring of claim 1, further comprising a mounting flange provided in a radially inner portion on a second surface of the main body, and wherein the two or more bores extend through the mounting flange.

10. The nozzle ring of claim 9, the mounting flange being integrally formed with the main body.

11. The nozzle ring of claim 1, the guide vanes being integrally formed with the main body.

12. The nozzle ring of claim 1, the nozzle ring being an integral one piece element.

13. The nozzle ring of claim 1, wherein the two or more bores are configured to receive for receiving one or more fastening means, and wherein the two or more bores are arranged with a regular angular spacing around the central opening.

14. The nozzle ring of claim 1, wherein a second surface of the main body comprises one or more recesses for forming one or more air-filled insulation space(s) when the nozzle ring is mounted.

15. An exhaust gas turbocharger comprising: a turbine housing, a shaft which is mounted in a bearing housing and on which a turbine wheel with rotor blades is arranged, an exhaust gas inlet passage formed in the turbine housing upstream of the turbine wheel, and a nozzle ring according to claim 1, the nozzle ring being fixed to the bearing housing by fastening means extending through the two or more bores.

16. The nozzle ring of claim 1, wherein the groove connects all of the two or more bores.

17. The nozzle ring of claim 5, wherein the groove has one or more rounded edges.

18. The nozzle ring of claim 6, wherein the groove has a width-to-depth ratio W/D of 1≤W/D≤5.

19. The nozzle ring of claim 7, wherein the groove has a depth-to-width ratio D/W of 1≤D/W≤5.

20. The exhaust gas turbocharger of claim 15, wherein the fastening means are heat resistant fastening means.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0015] So that the manner in which the above recited features of the present disclosure can be understood in detail, a more particular description of the disclosure, briefly summarized above, may be had by reference to embodiments. The accompanying drawings relate to embodiments of the disclosure and are described in the following:

[0016] FIG. 1 shows a schematic perspective view on a first side, particularly a turbine side, of a nozzle ring according to embodiments described herein;

[0017] FIGS. 2a to 2d show cross sections along the line A-A indicated in FIG. 1 for illustrating exemplary embodiments of a groove provided in a first surface of the main body of a nozzle ring according to embodiments described herein;

[0018] FIG. 3a shows a schematic isometric view of a nozzle ring according to embodiments described herein, wherein the nozzle ring is mounted to a bearing housing;

[0019] FIG. 3b shows the schematic isometric view of FIG. 3a further including a turbine wheel mounted to a shaft extending through a central opening of a nozzle ring according to embodiments described herein;

[0020] FIG. 4 shows a schematic isometric view on a second side, particularly a bearing housing side, of a nozzle ring according to embodiments described herein;

[0021] FIG. 5a shows a schematic isometric view on a bearing housing side of a nozzle ring according to embodiments described, the nozzle ring having a recess for forming an air-filled insulation space when the nozzle ring is mounted;

[0022] FIG. 5b shows a schematic isometric view on a bearing housing side of a nozzle ring according to embodiments described, the nozzle ring having two or more recesses separated by ribs, the recesses being configured for forming air-filled insulation spaces when the nozzle ring is mounted; and

[0023] FIG. 6 shows a schematic cross-sectional view of a portion of an exhaust gas turbocharger having a nozzle ring according to embodiments described herein.

DETAILED DESCRIPTION OF EMBODIMENTS

[0024] Reference will now be made in detail to the various embodiments, one or more examples of which are illustrated in each figure. Each example is provided by way of explanation and is not meant as a limitation. For example, features illustrated or described as part of one embodiment can be used on or in conjunction with any other embodiment to yield yet a further embodiment. It is intended that the present disclosure includes such modifications and variations.

[0025] Within the following description of the drawings, the same reference numbers refer to the same or to similar components. Generally, only the differences with respect to the individual embodiments are described. Unless specified otherwise, the description of a part or aspect in one embodiment can apply to a corresponding part or aspect in another embodiment as well.

[0026] With exemplary reference to FIG. 1, a nozzle ring 10 for a radial turbine turbomachine according to the present disclosure is described. According to embodiments, which can be combined with other embodiments described herein, the nozzle ring includes a disc-shaped main body 11 having a central opening 12 for passing a shaft there through. Additionally, the nozzle ring includes guide vanes 14 disposed circumferentially in a radially outer portion on a first surface 11A of the main body 11. Typically, the first surface 11A is a turbine side of the main body. More specifically, typically the guide vanes are arranged and configured to direct exhaust gas onto rotor blades of a turbine wheel. As exemplarily shown in FIG. 1, typically the guide vanes 14 extend from the first surface 11A of the main body in an axial direction. Further, two or more bores 17 are provided in a radially inner portion of the main body 11. Additionally, a groove 171 is provided in the first surface 11A of the main body 11. The groove 171 connects at least two of the two of more bores 17. In other words, typically the groove is configured such that the groove provides for a path which extends at least from one bore to another bore.

[0027] Accordingly, embodiments of the nozzle ring beneficially provide a reduction of pressure disturbances near the turbine wheel when the nozzle ring is mounted. Further, with the nozzle ring as described herein, rotor blade excitations of the turbine wheel can be reduced or even substantially be avoided. More specifically, providing a nozzle ring with a groove as described herein has the effect that a pressure pulse or disturbance created as the rotor blades pass over the respective affixation means can be disbursed through the groove along the disc-shaped main body.

[0028] As exemplarily shown in FIG. 3a, the main body 11 of the nozzle ring as described herein can be configured to form a heat shield between a bearing space 40 of a bearing housing 41 and a turbine space 50 when assembled. Typically, the main body 11 of the nozzle ring extends radially outwards from the central opening 12, as exemplarily shown in FIGS. 1 and 3a. In particular, the main body of the nozzle ring is formed such that (apart from the bores 17) a closed surface is provided between the central opening 12 and the outer edge of the main body. Accordingly, beneficially a nozzle ring with an integrated heat shield can be provided, such that the number of individual elements and thus interfaces in the area of mounted nozzle ring can be reduced.

[0029] According to embodiments, which can be combined with other embodiments described herein, the groove 171 extends at least partially concentrically around the central opening 12, as exemplarily shown in FIG. 1. According to an example, the groove 171 is concentrically arranged around the central opening 12.

[0030] According to embodiments, which can be combined with other embodiments described herein, the groove 171 is a closed-loop groove. In particular, the groove 171 can be configured for connecting all of the two or more bores 17. FIGS. 1 and 3a show exemplary embodiments with four bores all of which being connected by the groove. However, it is to be understood that also other embodiments with two, three, five, six, seven, eight or more bores may be realized. Further, it is to be understood that the feature “the groove connecting at least two of the two of more bores” may apply to various embodiments, wherein the “at least two of the two of more bores” include two, three, four, five, six, seven, eight or more bores.

[0031] According to embodiments, which can be combined with other embodiments described herein, the two or more bores 17 are arranged on a first virtual circle line having a first radius R.sub.1 around the central opening 12. Further, the guide vanes 14 may be arranged on a second virtual circle line having a second radius R.sub.2 around the central opening 12. Typically, the second radius R.sub.2 is R.sub.2≥1.5×R.sub.1.

[0032] With exemplary reference to FIGS. 2a to 2d, according to embodiments, which can be combined with other embodiments described herein, groove 171 has a cross-sectional shape selected from the group consisting of: a rectangular U-shape, a square U-shape, a round U-shape, and a cone-like shape. The groove 171 can have one or more rounded edges.

[0033] As exemplarily indicated in FIGS. 2a to 2d, according to embodiments, which can be combined with other embodiments described herein, the groove 171 has a width W and a depth D. For instance, the width can be larger than or equal to the depth, i.e. W≥D. According to embodiments, which can be combined with other embodiments described herein, the groove 171 has a width-to-depth ratio W/D of 1≤W/D≤5, particularly of 1.5≤W/D≤4, more particularly of 2≤W/D≤3.

[0034] Alternatively, the depth D can be larger than or equal to the width, i.e. D≥W. Further, the groove 171 may have a depth-to-width ratio D/W of 1≤D/W≤5, particularly of 1.5≤D/W≤4, more particularly of 2≤D/W≤3.

[0035] According to embodiments, which can be combined with other embodiments described herein, the groove 171 may have a width W of 2 mm≤W≤10 mm and a depth D of 0.4 mm≤D≤10 mm.

[0036] With exemplary reference to FIGS. 5a and 5b, according to embodiments, which can be combined with other embodiments described herein, the nozzle ring 10 may include a mounting flange 15 provided in a radially inner portion on a second surface 11B of the main body 11. Typically, the two or more bores 17 extend through the mounting flange 15.

[0037] According to embodiments, which can be combined with other embodiments described herein, the mounting flange 15 is integrally formed with the main body 11. Further, the guide vanes can be integrally formed with the main body 11. In particular, the nozzle ring can be an integral one piece element. For instance, the nozzle ring can be a machined, particularly milled, one-piece element. In other words, the complete nozzle ring may be a single piece structure.

[0038] According to embodiments, which can be combined with other embodiments described herein, the two or more bores 17 are configured for receiving one or more fastening means 15A, as exemplarily shown in FIGS. 3a and 6.

[0039] According to embodiments, which can be combined with other embodiments described herein, the two or more bores 17 are arranged with a regular angular spacing around the central opening 12, as exemplarily shown in FIG. 1.

[0040] According to embodiments, which can be combined with other embodiments described herein, a second surface 11B of the main body 11, includes one or more recesses 18 for forming one or more air-filled insulation space(s) when the nozzle ring 10 is mounted. Further, radially extending ribs 19 may be provided as exemplarily shown in FIG. 5b. Such ribs can have a beneficial effect on the stability and thermal expansion behavior of the nozzle ring.

[0041] In the present disclosure, the second surface 11B of the main body typically refers to a bearing housing facing surface of the main body.

[0042] With exemplary reference to FIG. 6, an exhaust gas turbocharger 60 according to the present disclosure is described. According to embodiments, which can be combined with other embodiments described herein, the exhaust gas turbocharger 60 includes a turbine housing 51, a shaft being which is mounted in a bearing housing 41 and on which a turbine wheel 30 with rotor blades 31 is provided. Additionally, the exhaust gas turbocharger 60 includes an exhaust gas inlet passage 33 formed in the turbine housing 51 upstream of the turbine wheel 30. Further, the exhaust gas turbocharger 60 includes a nozzle ring 10 according to any embodiments described herein. In particular, as exemplarily shown in FIG. 6, the nozzle ring is fixed to the bearing housing 41 by fastening means 15A extending through the two or more bores 17. For instance, the fastening means 15A can be heat resistant fastening means,

[0043] Hence, in view of the above, it is to be understood that compared to the state of the art, the embodiments described herein provide for an improved nozzle ring and improved exhaust gas turbocharger. In particular, embodiments of the present disclosure have the advantage that rotor blade excitations of a turbine wheel can be reduced or even eliminated.

[0044] While the foregoing is directed to embodiments, other and further embodiments may be devised without departing from the basic scope, and the scope is determined by the claims that follow.

REFERENCE NUMBERS

[0045] 10 nozzle ring [0046] 11 main body [0047] 11A first surface of main body [0048] 11B second surface of main body [0049] 12 central opening [0050] 14 guide vanes [0051] 15 mounting flange [0052] 15A fastening means [0053] 16 contact surface [0054] 17 bores [0055] 171 groove [0056] 18 recesses [0057] 19 ribs [0058] 20 shaft [0059] 22 central axis [0060] 30 turbine wheel [0061] 31 rotor blades [0062] 33 exhaust gas inlet passage [0063] 40 bearing space [0064] 41 bearing housing [0065] 50 turbine space [0066] 51 turbine housing [0067] 60 exhaust gas turbocharger