Rotor of a supercharging device

Abstract

A rotor for a supercharging device may include an arrangement; the arrangement may include a compressor wheel operatively coupled to a turbine wheel. A cup-shaped bearing bush configured to receive a radial air bearing may be arranged on at least one longitudinal end of the arrangement. The bearing bush may define an interior including at least one hollow space and a plurality of stiffening ribs extending into the at least one hollow space.

Claims

1. A rotor for a supercharging device, comprising: an arrangement defining a rotation axis and including a compressor wheel operatively coupled to a turbine wheel, the arrangement on at least one longitudinal end further including a cup-shaped bearing bush for a radial air bearing, wherein the bearing bush defines an interior including at least one hollow space and a plurality of stiffening ribs extending into the at least one hollow space, and wherein the bearing bush is screwed to at least one of the compressor wheel and the turbine wheel.

2. The rotor according to claim 1, wherein the bearing bush defines an axial face wall having an axial bearing surface, and wherein the axial face wall is reinforced.

3. The rotor according to claim 1, wherein the plurality of stiffening ribs are annular and project into the interior of the bearing bush to define the at least one hollow space.

4. The rotor according to claim 1, wherein the plurality of stiffening ribs delimit a plurality of hollow spaces, wherein the plurality of hollow spaces define a plurality of axially parallel bores.

5. The rotor according to claim 4, wherein the plurality of hollow spaces are disposed symmetrically in the interior of the bearing bush with respect to an axis of rotation of the bearing bush.

6. The rotor according to claim 1, wherein: the compressor wheel and the turbine wheel each include a central recess facing one another; the arrangement further includes a sealing disc disposed between the compressor wheel and the turbine wheel, the sealing disc including a central recess arranged coaxially to the central recess of the compressor wheel and the turbine wheel; and the compressor wheel, the sealing disc and the turbine wheel are secured to one another via a central screw arranged in the respective central recesses.

7. The rotor according to claim 6, wherein the bearing bush and the central screw are configured as one piece.

8. The rotor according to claim 6, wherein the sealing disc further includes a plurality of annular sealing fins defining a labyrinth seal.

9. The rotor according to claim 6, wherein the sealing disc further includes a first annular step and a second annular step disposed axially opposite one another with respect to the rotation axis; and wherein the compressor wheel engages the first annular step via a first annular edge and the turbine wheel engages the second annular step via a second annular edge.

10. The rotor according to claim 1, wherein the bearing bush is sealingly connected to and extends annularly about at least one of the compressor wheel and the turbine wheel.

11. The rotor according to claim 1, wherein the bearing bush includes an axial face wall, wherein the axial face wall defines a convex profile defined by a bulge projecting in a direction towards the interior.

12. A supercharging device, comprising: a rotor defining a rotation axis and including a compressor wheel having a first face end operatively coupled to a turbine wheel having a second face end, the second face end of the turbine wheel facing towards the first face end of the compressor wheel, wherein the rotor includes a first longitudinal end opposite the first face end of the compressor wheel and a second longitudinal end opposite the second face end of the turbine wheel; at least one bearing bush disposed coaxially to the rotor on at least one of the first longitudinal end and the second longitudinal end, the at least one bearing bush including an axial face wall and a circumferentially extending radial wall defining an interior, the interior of the at least one bearing bush including at least one hollow space and a plurality of stiffening ribs extending into the at least one hollow space; and wherein the plurality of stiffening ribs extend in a circumferential direction of the rotation axis and project towards the interior into the at least one hollow space; or wherein the at least one hollow space includes a plurality of hollows spaces defined by the plurality of stiffening ribs extending in an axial direction of the rotation axis, and wherein the plurality of hollow spaces define a plurality of axially extending bores disposed in the interior of the at least one bearing bush.

13. The supercharging device according to claim 12, wherein the plurality of stiffening ribs delimit the plurality of axially extending bores, and wherein the plurality of axially extending bores are arranged parallel to one another and distributed symmetrically in the interior with respect to the rotation axis of the rotor.

14. The supercharging device according to claim 12, wherein the plurality of stiffening ribs extend in the circumferential direction and have an annular shape.

15. The supercharging device according to claim 12, wherein the rotor further includes a sealing disc disposed between the compressor wheel and the turbine wheel, wherein the sealing disc is coupled on one end to the first face end of the compressor wheel and on another end to the second face end of the turbine wheel.

16. A rotor for a supercharging device, comprising: a compressor wheel having a first face end and a first longitudinal end; a turbine wheel operatively coupled to the compressor wheel, the turbine wheel having a second face end and a second longitudinal end, the second face end of the turbine wheel facing towards the first face end of the compressor wheel; a sealing disc disposed between the compressor wheel and the turbine wheel, wherein the sealing disc is coupled on one end to the first face end of the compressor wheel and on another end to the second face end of the turbine wheel; and at least one bearing bush disposed on at least one of the first longitudinal end of the compressor wheel and the second longitudinal end of the turbine wheel, the at least one bearing bush including a face wall and a circumferential wall defining an interior, the interior including at least one hollow space defined between a plurality of stiffening ribs projecting into the interior, wherein the plurality of stiffening ribs extend at least one of axially and circumferentially along the interior of the at least one bearing bush with respect to an axis of rotation to define the at least one hollow space.

17. The rotor according to claim 16, wherein the compressor wheel, the turbine wheel and the sealing disc respectively include a central recess arranged coaxially to each other; and a central screw arranged in the respectively central recesses securing the compressor wheel, the turbine wheel and the sealing disc to one another.

18. The rotor according to claim 16, wherein the at least one bearing bush is secured to the at least one of the first longitudinal end and the second longitudinal end via a screw connection.

19. The rotor according to claim 18, wherein the screw connection includes an external thread disposed on the at least one bearing bush received in an internal thread disposed on the at least one of the first longitudinal end and the second longitudinal end.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) There it shows, in each case schematically,

(2) FIG. 1 a sectional representation through a rotor according to the invention with a bearing bush in the region of a turbine wheel,

(3) FIG. 2 a representation as in FIG. 1, however with a differently configured bearing bush,

(4) FIG. 3 a part sectional representation and a view of a bearing bush according to FIG. 2,

(5) FIG. 4 a representation as in FIG. 1, however with bearing bush that can be screwed in,

(6) FIG. 5 a bearing bush that can be screwed on in a view.

DETAILED DESCRIPTION

(7) According to the FIGS. 1, 2 and 4, a rotor 1 according to the invention of a supercharging device 2 which is otherwise merely schematically hinted, in particular of an exhaust gas turbocharger, comprises a compressor wheel 3 and a turbine wheel 4 which is indirectly fastened thereon. Between the compressor wheel 3 and the turbine wheel 4 a sealing disc 5 with multiple annular sealing fins or labyrinths 6 is arranged. The sealing disc 5 is preferentially produced from a titanium material, which minimises the heat transfer from the turbine wheel 4 to the compressor wheel 3. On the turbine wheel side a pot-shaped bearing bush 7 for the radial air bearing is provided, which comprises at least one hollow space 8 and multiple stiffening ribs 9 extending into this hollow space. On its face wall 10, the bearing bush 7 can have an axial bearing surface in particular a grooved axial air bearing.

(8) Through the hollow design of the bearing bush 7, the same can be formed comparatively light, i.e. with little weight, which in particular is of special advantage for using the rotor 1 in a supercharging device 2 in a motor vehicle. Because of the additionally provided stiffening ribs 9, the strength of the bearing bush 7, in particular in radial direction, can be significantly increased which likewise has a positive effect on a rotor natural frequency of the rotor 1. In the case of the rotor 1 according to the invention, the rotor natural frequency can be increased via the rotational speed of the rotor 1 so that the same during the operation of the exhaust gas turbocharger is never reached and accordingly no natural frequency problems occur. In order to further increase the rotor natural frequency, the weight at the rotor ends can be reduced, by way of which a deformation of the bearing bush 7 through the stiffening is prevented.

(9) According to the FIGS. 1 and 2, the bearing bush 7 in this case is merely provided on the turbine side, wherein it is obviously also conceivable that such a bearing bush 7 is exclusively provided on the compressor side or on both sides.

(10) Looking at a face wall 10 of the bearing bush 7, it is evident with the bearing bush 7 shown according to FIG. 1 that the same has a convex bulge and is thereby reinforced which likewise has a positive effect on the strength and stiffness of the bearing bush 7. The stiffening ribs 9 shown according to FIG. 1 are annular in design and project towards the interior into the hollow space 8 collar-like. Generally, the bearing bush 7 according to FIG. 1 merely has a single hollow space 8.

(11) In contrast with the bearing bush 7 according to FIG. 1, the bearing bush 7 according to FIG. 2 comprises multiple hollow spaces 8 and multiple stiffening ribs 9, which are produced through axially parallel bores 11 (see in particular FIG. 3). In addition to producing the hollow spaces 8 by drilling, these can obviously be produced also by erosion processes.

(12) Looking once more at the FIGS. 1 and 2 it is evident that the compressor wheel 3 and the turbine wheel 4 each have a central recess 12 facing one another, just like the sealing disc 5 located between the compressor wheel 3 and the turbine wheel 4. All three components of the rotor 1, i.e. the compressor wheel 3, the turbine wheel 4 and the sealing disc 5 in this case are screwed together, i.e. fastened to one another by a central screw 13. By unscrewing the central screw 13, disassembly of the rotor 1, in particular for example for replacing individual components, such as for example the sealing disc 5, is easily possible. Tightening of the screw 13 in this case is performed from the compressor side, for the purpose of which the bearing bush 7 is removed.

(13) The bearing bush 7 is connected annularly sealingly to the turbine wheel 4, in particular for example welded, soldered, upset or glued. The sealing disc 5 has two annular steps 14 and 14 located opposite, wherein the compressor wheel 3 with an annular edge 15 engages in one of these, whereas the turbine wheel 4 with an annular edge 15 engages in the other annular step 14.

(14) According to FIG. 4 an embodiment is shown in which the bearing bush 7 is screwed to the turbine wheel 4. For this purpose, the bearing bush 7 comprises an external thread 16 and the turbine wheel 4 a complementarily associated internal thread 17 (see also FIG. 5). Accordingly, to disassemble the rotor 1, the bearing bush 7 has to be first unscrewed in order to make possible access to the screw 13. To save weight, the bearing bush 7 shown according to the FIGS. 4 and 5 also has hollow spaces 8.

(15) In a further embodiment, the screw 13 and the bearing bush 7 in FIG. 4 can be formed in one piece so that the three components of the rotor 1, i.e. the compressor wheel 3, the turbine wheel 4 and the sealing disc 5 are screwed to one another by attaching the bearing bush 7, i.e. fastened to one another.

(16) With the rotor 1 according to the invention it is possible to realise a radial air bearing at the rotor 1 with high strength in radial direction. For this purpose, the radial bearing element, i.e. concretely the bearing bush 7 comprises multiple stiffening ribs 9, which engage in at least one hollow space 8 of the bearing bush 7 or delimit multiple of these hollow spaces 8. Because of the stiffening ribs 9, a deformation tendency of the bearing bush 7 in the case of high rotor rotational speed can additionally be reduced. The stiffening ribs 9 likewise have an advantageous effect on the rotor natural frequency of the rotor 1.

(17) With the rotor 1 according to the invention, the rotor natural frequency in particular can be raised above the rotational speed of the rotor 1, so that the same exclusively rotates in a sub-critical range. This is mainly achieved through the bearing located outside and the increased stiffness.