阅读说明：本技术 尤其是用于废气涡轮增压器的可变涡轮机几何结构的碟簧 (Disc spring, in particular for a variable turbine geometry of an exhaust gas turbocharger ) 是由 达朗·布勒布勒安 金荷·托艾·彭 于 2019-06-03 设计创作，主要内容包括：本发明涉及一种尤其是用于废气涡轮增压器的可变涡轮机几何结构的碟簧(1)。所述碟簧(1)包括环形基体(2),其中心纵向轴线(M)限定所述基体(2)的轴向(A)。所述基体(2)的在包含所述中心纵向轴线(M)的侧廓平面(P)中的侧廓(3)具有波形轮廓(4),其具有一径向内侧最小值和一径向外侧最小值(9a,9b)并且具有布置在两个最小值(9a,9b)之间的一中间最大值(10)。所述波形轮廓从径向内侧端点(5a)延伸到径向外侧端点(5b),其中所述径向内侧端点(5a)在所述轴向(A)上相对于所述径向外侧端点(5b)成偏移布置。(The invention relates to a disc spring (1), in particular for a variable turbine geometry of an exhaust gas turbocharger. The disc spring (1) comprises an annular base body (2) whose central longitudinal axis (M) defines an axial direction (A) of the base body (2). The lateral contour (3) of the base body (2) in a lateral contour plane (P) containing the central longitudinal axis (M) has a wave contour (4) having a radially inner minimum and a radially outer minimum (9a, 9b) and having an intermediate maximum (10) arranged between the two minima (9a, 9 b). The wavy profile extends from a radially inner end point (5a) to a radially outer end point (5b), wherein the radially inner end point (5a) is arranged offset in the axial direction (A) with respect to the radially outer end point (5 b).)

1. A disc spring (1), in particular for a variable turbine geometry of an exhaust gas turbocharger,

-comprising an annular base body (2) whose central longitudinal axis (M) defines an axial direction (A) of said base body (2),

-wherein a profile (3) of the base body (2) in a profile plane (P) containing the central longitudinal axis (M) has a wave-shaped profile (4) with a radially inner minimum and a radially outer minimum (9a, 9b) and with an intermediate maximum (10) arranged between the two minima (9a, 9b), the wave-shaped profile extending from a radially inner end point (5a) to a radially outer end point (5b), wherein the radially inner end point (5a) is arranged offset in the axial direction (a) with respect to the radially outer end point (5 b).

2. The disc spring according to claim 1,

it is characterized in that

The main body (2) has a first and a second deflection point (6a, 6b) in the lateral contour (3), both arranged in a common plane (E) extending perpendicularly to the axial direction (A).

3. The disc spring according to claim 2,

it is characterized in that

The two turning points (6a, 6b) and thus the common plane (E) are arranged at the height of the radially outer end point (5b) with respect to the axial direction (A).

4. Disc spring according to one of the claims 1 to 3,

it is characterized in that

-the profile (3) comprises a radially inner profile section (8a) and a radially outer profile section (8b), the radially inner profile section (8a) being defined radially inwards by the radially inner end point (5a), the radially outer profile section (8b) being defined radially outwards by the radially outer end point (5b) and being at a distance from the radially inner profile section (8a),

-the profile (4) of the radially outer profile section (8b) is a mirror image of the radially inner profile section (8a) about a mirror axis (S) extending between the two profile sections (8a, 8b) parallel to the central longitudinal axis (M) of the base body (2), wherein the profile (4) of the radially outer profile section (8b) is arranged offset in the axial direction (a) from the profile (4) of the radially inner profile section (8 a).

5. The disc spring according to claim 4,

it is characterized in that

The radially inner and outer profile sections (8a, 8b) are arranged relative to each other offset in the axial direction (A) by the same amount (Δ h) as the radially inner and outer end points (5a, 5 b).

6. The disc spring according to claim 4 or 5,

it is characterized in that

The radially inner profile section (8a) is defined radially outwards by the second turning point (6 a).

7. Disc spring according to one of the preceding claims,

it is characterized in that

The radially inner minimum (9a) is arranged in the radially inner profile section (8a) and the radially outer minimum (9b) is arranged in the radially outer profile section (8 b).

8. Disc spring according to one of the claims 4 to 7,

it is characterized in that

The radially inner profile section (8a) is passed over to the radially outer profile section (8b) by means of a transition profile section (8c) in which the intermediate maximum (10) is arranged.

9. The disc spring according to claim 8,

it is characterized in that

The two profile sections (8a, 8b) each enter the transition profile section (8c) continuously and without bending.

10. The disc spring according to claim 8 or 9,

it is characterized in that

-the radially inner profile section (8a) adjoins the transition profile section (8c) at the second turning point (6 b); and/or

-the radially outer profile section (8b) adjoins the transition profile section (6b) at a third turning point (6 c).

11. The disc spring according to claim 10,

it is characterized in that

The third turning point (6c) is arranged offset with respect to the axial direction (A) with respect to a common plane (E) in which the first and second turning points (6a, 6b) are arranged.

12. Disc spring according to one of the preceding claims,

it is characterized in that

The side profile (3) of the disc spring (21) is continuous, in particular without steps, and/or is free of bends.

13. A variable turbine geometry for an exhaust gas turbocharger,

-a bearing housing comprising a bearing shell,

-comprising a disc spring (1) according to any of the preceding claims arranged on the bearing housing.

14. An exhaust-gas turbocharger for an internal combustion engine of a motor vehicle,

-comprising a compressor and comprising a turbine,

-having a variable turbine geometry according to claim 14.

Technical Field

The invention relates to a disc spring, in particular for a variable turbine geometry of an exhaust gas turbocharger.

Background

The disc spring of a variable turbine geometry of an exhaust gas turbocharger generally performs two functions: on the one hand, they serve as heat shields in order to shield the waste heat generated during operation in the exhaust gas turbocharger from the kinematic conditions of the variable turbine geometry. Furthermore, certain parts of the variable turbine geometry may be pre-tensioned by means of disc springs.

Such conventional disc springs are known, for example, from DE102008032808a1 and WO2009/092678a 1.

A disadvantage of such conventional disc springs is that, due to the usually very high operating temperatures of up to 850 ℃ in exhaust gas turbochargers, the disc springs relax, so that plastic deformation can occur, in particular because they usually have very high tension levels in the installed state. Furthermore, there is usually only little installation space in an exhaust gas turbocharger, which leads to a short spring deflection and a high stiffness of the disk spring.

Disclosure of Invention

The object of the invention is to indicate a new path in the development of a disc spring, in particular for a variable turbine geometry for an exhaust gas turbocharger. In particular, a disc spring is provided in which the above-mentioned disadvantages no longer occur or only occur in a significantly reduced form.

This object is solved by the subject matter of the independent claims. Preferred embodiments are the subject of the dependent claims.

The basic idea of the invention is therefore to have the contour of the disc spring have a wave shape with two minima and an intermediate maximum, so that the contour has a large radius of curvature. In this way, the elastically deformable region of the disc spring is enlarged compared to a conventional disc spring. Relaxation effects caused by undesired operation in the disc spring can in this way be minimized or even completely prevented without an accompanying decrease in stiffness or increase in spring deflection.

The disc spring according to the invention, in particular for a variable turbine geometry of an exhaust gas turbocharger, comprises an annular base body, the central longitudinal axis of which defines the axial direction of the base body. The profile of the base body in a profile plane containing the central longitudinal axis has a wave-shaped profile with a radially inner minimum and a radially outer minimum and with an intermediate maximum arranged between the two minima. The contour in this case extends from a radially inner end point to a radially outer end point with respect to a radial direction perpendicular to the axial direction. The radially inner end point is arranged axially offset with respect to the radially outer end point.

According to a preferred embodiment, the base body has a first deflection point and a second deflection point in a lateral contour, both arranged in a common plane extending perpendicularly to the axial direction. The geometry associated with this embodiment allows for the implementation of particularly large radii of curvature, which then counteract the formation of relaxation zones of the disc spring plastic deformation.

Preferably, the two turning points and thus the common plane are arranged at the height of the radially outer end point with respect to the axial direction. This variant makes it possible to maximize the elastically deformable area.

According to an advantageous further development, the profile comprises a radially inner profile section, which is defined radially inwardly by the radially inner end point, and a radially outer profile section, which is defined radially outwardly by the radially outer end point. In this further development, the radially outer and the radially inner profile sections are arranged at a distance from one another. In this case, the contour of the radially outer profile section is a mirror image of the radially inner profile section about a mirror axis which is arranged between the two profile sections and extends parallel to the central longitudinal axis of the base body. In this case, the contour of the radially outer profile section is arranged offset in the axial direction from the contour of the radially inner profile section. This variant also makes it possible to enlarge the elastically deformable zone.

Particularly preferably, the radially inner and outer profile sections are arranged relative to each other axially offset by the same amount as the radially inner and outer end points. This measure thus results in an increase of the elastically deformable area of the disc spring.

Advantageously, the radially inner profile section is defined radially outwards by the second turning point.

Particularly preferably, the radially inner minimum is arranged in the radially inner profile section and the radially outer minimum is arranged in the radially outer profile section. In particular, the radially inner minimum may define a radially inner profile section radially outward. This measure thus results in a particularly large radius of curvature in the waveform profile.

According to an advantageous further development, the radially inner profile section is passed over to the radially outer profile section by means of a transition profile section in which an intermediate maximum value is arranged, said maximum value being arranged between the minimum values. The disc spring configured in this manner can be produced by a simple forming process using a metal plate layer as a starting material.

Advantageously, two side profile sections (i.e. a radially inner side profile section and a radially outer side profile section), each entering the transition side profile section continuously and without bending. A disk spring constructed in this way has a particularly high spring constant and thus a particularly high stiffness.

According to an advantageous further development, the radially inner profile section adjoins the transition profile section at the second turning point. Alternatively or additionally, in this further development, the radially outer profile section adjoins the transition profile section at a third turning point.

According to an advantageous further development, the third turning point is arranged offset with respect to the axial direction with respect to a common plane in which the first and second turning points are arranged.

Particularly preferably, the profile is designed to be continuous, in particular without steps, and/or without bends. A disk spring constructed in this way has a particularly high spring constant.

The invention also relates to a variable turbine geometry for an exhaust-gas turbocharger. The variable turbine geometry according to the invention comprises a bearing shell on which the previously described disc springs are arranged. The advantages of the disc spring described previously are therefore also transferred to the variable turbine geometry according to the invention.

The invention also relates to an exhaust-gas turbocharger comprising a turbine, comprising a compressor and comprising the aforementioned variable turbine geometry. The advantages of the disc spring explained earlier therefore also apply to the exhaust-gas turbocharger according to the invention.

Further important features and advantages of the invention can be taken from the dependent claims, the figures and the associated description of the figures with reference to the figures.

It is to be understood that the features mentioned above and explained further below can be used not only in the respectively given combination but also in other combinations or alone without departing from the scope of the present invention.

Drawings

Preferred exemplary embodiments of the invention are shown in the drawings and will be described in detail in the following description, wherein like reference numerals refer to identical or similar or functionally identical components.

In the drawings, schematically:

figure 1 shows an example of a disc spring according to the invention in a transverse cross-sectional view,

fig. 2 shows the disc spring of fig. 1 in a side view.

Detailed Description

Fig. 1 shows an example of a disc spring 1 according to the invention in a transverse sectional view. The disc spring 1 includes an annular base body 2, and the base body 2 may be formed by sheet metal molding. The axial direction a of the base body 2 is defined by a central longitudinal axis M of the base body 2. The base body 2 extends in a circumferential direction U, which extends perpendicularly to the central longitudinal axis M and thus also in the axial direction a, and is adjacent to the through opening. The radial direction R extends perpendicularly to the central longitudinal axis M and thus also perpendicularly to the axial direction a and perpendicularly to the circumferential direction U.

Fig. 2 shows a side profile 3 of the basic body 2 in a side profile plane P which includes the central longitudinal axis M. Thus, the side profile 3 has a wave profile 4 extending from a radially inner end point 5a to a radially outer end point 5 b. In this case, the radially inner end point 5a is arranged offset in the axial direction a with respect to the radially outer end point 5 b. The profile 3 of the base body 2 is preferably continuous, in particular does not form a step, and is also free of bends.

According to fig. 1, the main body 2 has a first deflection point 6a and a second deflection point 6b in the side profile 3, which are arranged in a common plane E, which in turn extends perpendicularly to the axial direction a. The common plane E orthogonally intersects the profile plane P. With respect to the axial direction a, the two turning points 6a, 6b and thus the common plane E are arranged at the level of the radially outer end point 5 b.

According to fig. 2, the profile 3 of the base body 2 has a radially inner profile section 8a, which is delimited radially inward by the inner end point 5a, and a radially outer profile section 8b, which is delimited radially outward by the outer end point 5 b. The radially inner profile section 8a is passed over to the radially outer profile section 8b by means of a transition profile section 8c, i.e. the radially inner profile section 8a and the radially outer profile section 8b are arranged at a distance from one another in the radial direction. In this case, the radially inner and outer profile sections 8a, 8b enter the transition profile section 8c continuously and without bending. The contour 4 of the radially outer profile section 8b is a mirror image of the radially inner profile section 8a about a mirror axis S, which extends between the two profile sections, parallel to the central longitudinal axis M of the base body 2.

As is clearly illustrated in fig. 2, the contour 4 of the radially outer contour section 8b is offset in the axial direction a with respect to the contour 4 of the radially inner contour section 8 a. In this case, the radially inner and outer profile sections 8a, 8b are arranged relative to one another offset in the axial direction by the same amount Δ h as the inner and outer end points 5a, 5 b. The radially inner profile section 8a adjoins the transition profile section 8c at the second turning point 6 b. The radially outer profile section 8b adjoins the transition profile section 8c at a third turning point 6c, which is different from the first and second turning points 6a, 6 b. The third turning point 6c inwardly defines a radially outer profile section 8 b. The radially inner profile section 8a is delimited radially outwards by the second turning point 6 b.

As can be seen from fig. 2, the third turning point 6c is arranged offset with respect to the axial direction a with respect to a common plane E in which the first turning point 6a and the second turning point 6b are arranged.

As can also be seen from fig. 2, the profile of the main body 2 has a radially inner minimum 9a and a radially outer minimum 9b, and an intermediate maximum 10 arranged between these two minima 9a, 9 b. A radially inner minimum 9a is arranged in the radially inner lateral section 8a, and a radially outer minimum 10b is arranged in the radially outer lateral section 8 b. The intermediate maximum 10 is arranged in the transition profile section 8 c.

In the example of fig. 2, the profile 4 has a predetermined radius of curvature r between the two turning points 6a, 6 b. The distance y from the radially inner minimum 9a measured in the axial direction a to the plane E is a quarter of the radius of curvature r, i.e. y is 0.25 r. The distance x between the radially inner end point 5a and the radially inner end minimum 9a measured in the radial direction R follows the following relation: x is r +2 Δ h.