• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    Turbocharger, with a turbine for expanding a first medium, with a compressor for compressing a second medium using energy obtained in the turbine when the first medium is expanded, the turbine having a turbine housing (1) and a turbine rotor, the compressor being a Compressor housing and a compressor rotor coupled to the turbine rotor via a shaft, the turbine housing (1) and the compressor housing being connected to a bearing housing (2) arranged between the same and in which the shaft is mounted, the turbine housing (1) and the Bearing housing (2) are connected via a fastening device (5) in such a way that the fastening device (5) is mounted on a flange (6) of the turbine housing (1) with a first section (7) and a flange with a second section (9) (10) of the bearing housing (2) covered at least in sections, and wherein the fastening device (5) on one of the F flange (10) of the bearing housing (2) facing surface of the second section (9) is curved (R) is contoured. This provides a tribological shape on this surface which minimizes the risk of wear between the bearing housing (2) and the fastening device (5) if relative movements develop between the turbine (1) and the bearing housing (2) during operation.
    公开号:CH712978B1
    申请号:CH00925/17
    申请日:2017-07-14
    公开日:2021-07-30
    发明作者:Weisbrod Tobias；Klima Jiri；Jerabek David；Haag Jan-Christoph；Uhlenbrock Santiago；Rost Stefan；Bartholomä Klaus
    申请人:Man Energy Solutions Se；
    IPC主号:
    专利说明:

    The invention relates to a turbocharger.
    The basic structure of a turbocharger is known from DE 10 2013 002 605 A1. A turbocharger has a turbine in which a first medium is expanded. Furthermore, a turbocharger has a compressor in which a second medium is compressed using the energy obtained in the turbine when the first medium is expanded. The turbine of the turbocharger has a turbine housing and a turbine rotor. The compressor of the turbocharger has a compressor housing and a compressor rotor. A bearing housing is positioned between the turbine housing of the turbine and the compressor housing of the compressor, the bearing housing being connected on the one hand to the turbine housing and on the other hand to the compressor housing. A shaft via which the turbine rotor is coupled to the compressor rotor is mounted in the bearing housing.
    From practice it is known that the turbine housing of the turbine, namely a so-called turbine inflow housing, and the bearing housing are connected to one another via a fastening device preferably designed as a clamping claw. Such a fastening device designed as a clamping claw is mounted with a first section of the same on a flange of the turbine housing via fastening means and covers a flange of the bearing housing at least in sections with a second section. The association or composite of the bearing housing and the turbine housing is braced by means of such a fastening device, in particular with a sealing cover and nozzle ring clamped between the turbine housing and the bearing housing.
    The turbine housing is filled with the first medium to be expanded, in particular with exhaust gas to be expanded. The turbine inflow housing of the turbine housing directs the exhaust gas towards the turbine rotor. In the turbine inflow housing there is an overpressure in relation to the environment, which is reduced in the turbine while generating energy during the expansion of the first medium. Leakage can occur in the area of the connection point between the turbine housing or the turbine inflow housing and the bearing housing, so that the first medium to be expanded in the turbine can reach the environment via the connection area between the turbine housing and the bearing housing. This is a disadvantage.
    In order to counteract such leakage of the first medium to be relaxed in the turbine, the tension between the turbine housing or turbine inflow housing and bearing housing is increased in practice, in particular via higher tightening torques for the fastening means, via which the fastening device, preferably designed as a clamping claw, on the turbine housing is mounted. This also increases a clamping force between the fastening device and the bearing housing. A contact point between the bearing housing and the fastening device is exposed to high relative movements as a result of the different thermal expansions of the bearing housing and turbine housing or turbine inflow housing. In connection with a high contact pressure or a high preload or a high clamping force between the bearing housing and the fastening device, wear on the fastening device and / or on the bearing housing can then occur as a result of a so-called digging effect. This can then cause the first medium to be expanded in the turbine to leak into the environment, and in extreme cases the connection between the turbine housing or the turbine inflow housing and the bearing housing can loosen.
    Proceeding from this, the present invention is based on the object of creating a new type of turbocharger.
    This object is achieved by a turbocharger according to claim 1.
    The fastening device is curved on a surface of the second section facing the flange of the bearing housing. The arched contouring of the fastening device on the surface facing the flange of the bearing housing provides a defined tribological surface shape on the fastening device, which minimizes wear on the fastening device and bearing housing in the event of a relative movement between fastening device and bearing housing.
    This reduces the risk of the first medium to be expanded in the turbine leaking into the environment. Furthermore, the risk of the connection between the bearing housing and the turbine housing becoming detached is reduced.
    Preferably, a radius of curvature of the curved surface of the flange of the bearing housing facing second portion of the fastening device corresponds to between 5 times and 20 times the axial thickness of the fastening device in the region of the second section and / or first section. Such a radius of curvature of the curved surface of the fastening device provides a particularly advantageous tribological surface shape for minimizing wear.
    Preferably, the fastening device consists of a material with a hardness of at least 40 HRC or of a hardened material with a surface hardness in the area of the curved surface of at least 40 HRC. If the fastening device is designed in this way, the risk of wear on the fastening device and bearing housing can be further reduced.
    According to an advantageous first development of the invention, at least one ring is arranged between the second portion of the fastening device and the flange of the bearing housing. By arranging at least one ring between the second section of the fastening device and the flange of the bearing housing, the risk of wear on the fastening device and bearing housing can be further reduced. In particular, the or each ring has a surface hardness of at least 40 HRC, for which the respective ring is either made from a material with this hardness or is hardened on the surface while providing this hardness.
    Preferably, two rings are arranged between the second portion of the fastening device and the flange of the bearing housing, wherein a first ring rests with a first side on the flange of the bearing housing, a second ring rests with a first side on the second portion of the fastening device , wherein the two rings lie against one another with second sides. In particular, the first ring has a coefficient of thermal expansion which corresponds to the coefficient of thermal expansion of the bearing housing, the second ring having a coefficient of thermal expansion that deviates therefrom. By arranging two rings axially one behind the other in this way between the second section of the fastening device and the flange of the bearing housing, the risk of wear for the bearing housing and fastening device can be reduced in a particularly advantageous manner. It is particularly advantageous if the first ring, the first side of which is in contact with the flange of the bearing housing, has a coefficient of thermal expansion which corresponds to the coefficient of thermal expansion of the bearing housing. This minimizes relative movement between the first ring and the bearing housing. The second ring, which rests with its first surface on the second section of the fastening device, has a different coefficient of thermal expansion in order to displace a relative movement between the contact surfaces of the two rings during operation.
    According to a second, alternative development of the invention, the flange of the bearing housing is designed as a separate assembly of the bearing housing, made of a hard or hardened material with a surface hardness of at least 40 HRC and mounted by means of a thread on a base body of the bearing housing. This also makes it possible to reduce the risk of wear of the connection between the bearing housing and the turbine housing.
    According to a third, also alternative development of the invention, the flange designed as an integral assembly of the bearing housing is hardened on a surface facing the second portion of the fastening device and has a surface hardness of at least 40 HRC on this surface. This embodiment of the invention also makes it possible to reduce the risk of wear and tear of the connection between the bearing housing and the turbine housing.
    Preferred developments of the invention emerge from the dependent claims and the following description. Exemplary embodiments of the invention are explained in more detail with reference to the drawing, without being restricted thereto. 1 shows a partial cross section through a first turbocharger according to the invention in the area of a connection between a turbine housing and a bearing housing; Fig. 2 is a perspective view of Fig. 1; 3 shows a partial cross section through a second turbocharger according to the invention in the area of a connection between a turbine housing and a bearing housing; Fig. 4 shows a detail of Fig. 3; 5 shows a partial cross section through a third turbocharger according to the invention in the area of a connection between a turbine housing and a bearing housing; and FIG. 6 shows a partial cross section through a fourth turbocharger according to the invention in the area of a connection between a turbine housing and a bearing housing.
    The invention relates to a turbocharger. A turbocharger has a turbine for expanding a first medium, in particular for expanding exhaust gas from an internal combustion engine. Furthermore, a turbocharger has a compressor for compressing a second medium, in particular charge air, to be precise using the energy obtained in the turbine when the first medium is expanded. The turbine has a turbine housing and a turbine rotor. The compressor has a compressor housing and a compressor rotor. The compressor rotor is coupled to the turbine rotor via a shaft that is journalled in a bearing housing, the bearing housing being positioned between the turbine housing and the compressor housing and being connected to both the turbine housing and the compressor housing. This basic structure of a turbocharger is familiar to the person skilled in the art addressed here.
    The invention now relates to such details of a turbocharger that relate to the connection of the turbine housing and bearing housing. Different exemplary embodiments of turbochargers are described below with reference to FIGS. 1 to 6, FIGS. 1 to 6 each showing corresponding sections from a turbocharger in the area of the connection between the turbine housing and the bearing housing.
    A first embodiment of a turbocharger is shown in FIGS. 1 and 2, wherein in FIGS. 1 and 2 the connection point between a turbine housing, namely a turbine inflow housing 1 of the turbine housing, and a bearing housing 2 of the exhaust gas turbocharger is shown. Furthermore, FIG. 1 shows a nozzle ring 3 and a sealing cover 4.
    The turbine inflow housing 1 is connected to the bearing housing 2 via a fastening device 5 in such a way that the fastening device 5 is mounted on a flange 6 of the turbine inflow housing 1 with a first section 7, via several fasteners 8, and that the fastening device 5 with a second section 9 covers a flange 10 of the bearing housing 2 at least in sections. The fastening device 5 is also referred to as a clamping claw. In the exemplary embodiment in FIGS. 1 and 2, the fastening device 5 is segmented in the circumferential direction, each individual segment 5a of the fastening device 5 being mounted on the flange 6 of the turbine inflow housing 1 via a respective fastening means 8 over the respective first section 7. Preferably, a maximum of two such fastening means 8 are provided for each segment 5a of the fastening device 5 in order to mount the respective segment 5a on the flange 6 of the turbine inflow housing 1.
    In the embodiment shown in Fig. 1 and 2, each fastening means 8 comprises a threaded screw 8a screwed into the flange 6 of the turbine inflow housing 1 and a nut 8b engaging at the other end of the threaded screw 8a, whereby a defined biasing force is achieved by tightening the nuts 8b the fastening device 5 can be applied to the turbine inflow housing 1 and to the bearing housing 10. Corresponding flanges of the nozzle ring 3 and sealing cover 4 are clamped between the turbine inflow housing 1 and the bearing housing 2.
    In order to minimize a leakage flow over this connection area of the turbine inflow housing 1 and bearing housing 2, it must be avoided that the fastening device 5 in particular is subject to wear, so that a defined clamping force can always be applied to the turbine inflow housing 1 and bearing housing 2 and there is no risk of that the turbine inflow housing 1 and the bearing housing 2 detach from each other.
    According to the invention, the fastening device 5 has a curved contour on a surface of the second section 9 facing the flange 10 of the bearing housing 2. This curved contoured surface of the second section 9 of the fastening device 5 facing the flange 10 of the bearing housing 2 is curved convexly outward, with a radius of curvature R that is between 5 times and 20 times the axial thickness of the fastening device 5 corresponds in the area of the second section 9 and / or the first section 7 of the fastening device 5. In the embodiment of FIGS. 1 and 2, in which the fastening device 5 is formed by several segments 5a, each segment 5a has such a curvature in the area of the surface of the respective second section 9 facing the flange 10 of the bearing housing 2.
    About the above-described curved contouring of the fastening device 5 or the segments 5a of the fastening device 5 on the flange 10 of the bearing housing 2 facing surface of the second section 9 is provided on this surface, a tribological shape, which then when in operation Forming relative movements between the turbine inflow housing and the bearing housing, and thus between the fastening device 5 and the bearing housing 2, minimizes the risk of wear on the bearing housing 2 and on the fastening device 5.
    The fastening device 5 or the segments 5a of the same are preferably made of a metallic material with a hardness of at least 40 HRC (Rockwell hardness on the C scale), or the fastening device 5 or the segments 5a are made of a hardened metallic material with a • Surface hardness in the area of the curved surface of at least 40 HRC. The hardening of a metallic material to provide such a surface hardness is preferably carried out by nitriding. It is also possible to harden a metallic material to apply a coating to a surface to be hardened, for example using a melting or spraying process, such as laser cladding.
    The combination of the curved contouring of the fastening device 5 in the area of the flange 10 of the bearing housing 2 facing surface of the second section 9 of the fastening device 5 in combination with the hardness of the fastening device 5 described above reduces the risk of wear if there are relative movements between during operation Form fastening device 5 and bearing housing 2. In particular, the so-called digging effect can be prevented.
    In the embodiment of FIGS. 1 and 2, a ring 11 is arranged between the flange 10 of the bearing housing 2 and the second section 9 of the fastening device 5 or the segments 5a of the fastening device 5. In the embodiment of FIGS. 1 and 2, a single ring 11 is positioned between the flange 10 of the bearing housing 2 and the second section 9 of the respective segment 5a of the fastening device 5, this ring 11 having an axial width B and a radial height H. In order to prevent the ring 11 from tilting as a result of frictional forces acting on the ring, the ratio B: H 0.25. The ring 11 preferably consists of a material with a hardness of at least 40 HRC or of a hardened material with a surface hardness of at least 40 HRC. This serves to minimize wear when a relative movement occurs between the fastening device 5 and the bearing housing 2.
    In the embodiment of FIGS. 1 and 2, in which a single ring 11 is arranged between the flange 10 of the bearing housing 2 and the second section 9 of the fastening device 5 or the segments 5a of the fastening device 5, the ring 11 has a thermal expansion coefficient, which corresponds approximately to the thermal expansion coefficient or the thermal expansion coefficient of the bearing housing 2. As a result, relative movements between the ring 11 and the bearing housing 2 are minimized, and relative movements take place between the ring 11 and the segments 5 a of the fastening device 5.
    The abutting surfaces of the ring 11 and the second section 9 of the segments 5a of the fastening device 5 have surface hardnesses of preferably more than 40 HRC, the surface of the second section 9 of the segments 5a of the fastening device 5 facing the ring 11 has the above described contoured curvature with the radius of curvature R, whereby a low-wear mounting of the bearing housing 2 on the turbine housing 1, namely on the turbine inflow housing, is possible overall.
    The ring 11 of the embodiment of FIGS. 1 and 2 is preferably slotted at a circumferential position to form an open ring, so that the same can simply be screwed or threaded onto the flange 10 of the bearing housing 2. This is particularly necessary when the flange of the bearing housing 2, which is not shown and interacting with the compressor housing, has a larger diameter than the flange 10 of the bearing housing 2 shown, which interacts with the turbine inflow housing 1. The ring 10 of FIGS first side on the flange 10 of the bearing housing 2 and with a second side on the second section 9 of the segments 5a of the fastening device 5.
    A particularly preferred embodiment of a turbocharger is shown in FIGS. 3 and 4, the embodiment of FIGS. 3 and 4 differing from the embodiment of FIGS. 1 and 2 primarily in that in the embodiment of FIGS the flange 10 of the bearing housing 2 and the second section 9 of the fastening device 5 or the second section 9 of the segments 5a of the fastening device 5 is not a single ring 11, but here in Fig. 3 and 4 two rings 12 and 13 are axially one behind the other arranged. A first ring 12 rests with a first side on the flange 10 of the bearing housing 2, whereas a second ring 13 rests on a first side on the second section 9 of the fastening device 5 or the segments 5a of the fastening device 5. Furthermore, the two rings 12 and 13 rest against one another with the second sides facing one another.
    The first ring 12 preferably has a coefficient of thermal expansion which corresponds to the coefficient of thermal expansion of the bearing housing 2. The second ring 13 preferably has a different coefficient of thermal expansion. This makes it possible to displace a relative movement, which can develop during operation, between the two rings 12, 13. This allows a particularly low-wear connection between the bearing housing 2 and the turbine inflow housing 1.
    Also in the embodiment of FIGS. 3 and 4, the second section 9 of the fastening device 5 or the segments 5a of the fastening device 5 is curved contoured on the side facing the second ring 13 and thus the flange 10 of the bearing housing 2, namely as described in connection with FIGS. 1 and 2, with a defined radius of curvature R. In this regard, reference is made to the above statements. The arrangement of the two rings 12 and 13 has an axial width B and a radial height H, with a ratio B: H <0.25.
    The two rings 12, 13 are preferably made of a material with a hardness of at least 40 HRC or of a hardened material with a surface hardness of at least 40 HRC.
    The first ring 12, which rests with its first side on the flange 10 of the bearing housing 2, is preferably slotted at a single circumferential position, so that the same in turn can simply be threaded onto the bearing housing 2, namely the flange 10 thereof, as a unit . The second ring 13, on the other hand, is preferably slotted to form several ring segments at several circumferential positions, preferably in such a way that the number and thus the circumferential extent of the ring segments of the second ring 13 corresponds to the number and thus the circumferential extent of the segments 5a of the fastening device 5.
    Between each segment 5a of the fastening device 5 and the flange 10 of the bearing housing 2, an individual ring segment of the second ring 13 is preferably positioned, with all ring segments of the second ring segment 13 on the first ring, slotted at a circumferential position, designed as an open ring 12 are present. By segmenting the second ring 13, thermal stresses can be reduced in the circumferential direction. A sliding movement is then divided between several series-connected sliding surfaces of the ring segments of the ring 13, as a result of which a frictional force acting on the fastening device 5 is reduced.
    Another exemplary embodiment of a turbocharger according to the invention is shown in FIG. 5, FIG. 5 representing an alternative to the exemplary embodiments in FIGS. 1 to 4. In the exemplary embodiment in FIG. 5, it is provided that the bearing housing 2 is designed in at least two parts and has a base body 14 to which a separate flange 15 is connected. The base body 14 is made of a conventional metallic material, whereas the separate flange 15, which is attached to the base body 14, is made of a material that has a hardness of at least 40 HRC, or that of a hardened material with a surface hardness of at least 40 HRC is manufactured. As a result, adapted friction coefficients are provided between the flange 15 of the bearing housing 2 and the fastening device 5, namely the segments 5a thereof, in the region of the second sections 9 thereof, in order to minimize wear on the connection between the bearing housing 2 or the turbine inflow housing 1. It is also provided in FIG. 5 that the second section 9 of the fastening device 5 or the second section 9 of the segments 5a of the fastening device 5 is curved convexly outward with a defined radius of curvature R on the side facing the flange 15 of the bearing housing 2 . With regard to these features, reference is made to the above statements on the exemplary embodiment in FIGS. 1 and 2 and the exemplary embodiment in FIGS. 3 and 4.
    The main difference to the embodiment of FIG. 5 and the embodiment of FIGS. 1 to 4 is therefore that in FIG. 5 no ring is provided which is positioned between the flange 10 of the bearing housing 2 and the fastening device 5 Rather, here the flange 15 of the bearing housing 2 is made as a separate assembly from a hard or hardened, metallic material.
    Fig. 5 can be seen that this made of a hard or hardened material, separate flange 15 is screwed onto the base body 14 of the bearing housing 2, for this purpose an internal thread 16 on the flange 15 with an external thread 17 on the base body 14 of the bearing housing 2 cooperates. Such a screw connection is preferred because it represents a form fit and is therefore insensitive to thermal expansion and manufacturing tolerances. According to FIG. 5 it is provided that the screw connection between the flange 15 of the bearing housing 2 and the base body 14 of the bearing housing 2 is secured by means of at least one securing element 18 which extends in the radial direction and is designed as a cylindrical pin in the exemplary embodiment shown.
    Another embodiment of a turbocharger according to the invention is shown in FIG. 6. In the embodiment of FIG the fastening device 5 or the respective segment 5a of the fastening device 5 cooperates on the second section 9 of the same, is hardened. 6 shows a coating 19 applied to this surface of the flange 10 of the bearing housing 2 in order to harden the bearing housing 2 on this surface of the flange 10, this coating being applied, for example, by a melting or spraying process such as laser cladding. As an alternative to a coating, the material of the bearing housing 2 can also be hardened using a hardening process such as laser hardening or nitriding.
    In all variants of an exhaust gas turbocharger according to the invention, a particularly advantageous connection between the turbine inflow housing 1 and the bearing housing 2 can be provided, which connection is low-wear. The embodiment of FIGS. 3 and 4 is particularly preferred, in which two rings 12 and 13 are arranged axially one behind the other between the flange 10 of the bearing housing 2 and the sections 9 of the segments 5a of the fastening device 5 covering the flange 10 of the bearing housing 2. This design is not only structurally simple, but also allows operational relative movements to be shifted between the two rings 12 and 13, so that neither the fastening device 5 nor the bearing housing 2 are exposed to wear, which means that there is no risk of a leakage flow of the first medium to be expanded in the turbine reaches the environment or the connection between the turbine inflow housing 1 and the bearing housing 2 is broken.
    List of reference symbols
    1 turbine inflow housing 2 bearing housing 3 nozzle ring 4 sealing cover 5 fastening device 5a segment 6 flange 7 section 8 fastening means 8a screw 8b nut 9 section 10 flange 11 ring 12 ring 13 ring 14 base body 15 flange 16 thread 17 thread 18 locking element 19 coating
    权利要求:
    Claims (17)
    [1]
    1. turbocharger,with a turbine for the expansion of a first medium,with a compressor for compressing a second medium using the energy gained in the turbine when the first medium is expanded,wherein the turbine has a turbine housing (1) and a turbine rotor,wherein the compressor has a compressor housing and a compressor rotor coupled to the turbine rotor via a shaft,wherein the turbine housing (1) and the compressor housing are connected to a bearing housing (2) arranged between the same and in which the shaft is mounted,wherein the turbine housing (1) and the bearing housing (2) are connected via a fastening device (5) such that the fastening device is mounted on a flange (6) of the turbine housing (1) with a first section (7) and with a second section (9) covers a flange (10; 15) of the bearing housing (2) at least in sections,characterized in thatthe fastening device (5) has a curved contour on a surface of the second section (9) facing the flange (10; 15) of the bearing housing (2).
    [2]
    2. Turbocharger according to claim 1, characterized in that a radius of curvature of the curved surface of the flange (10; 15) of the bearing housing (2) facing second section (9) of the fastening device (5) between 5 times and 20 times the corresponds to the axial thickness of the fastening device (5) in the region of the second section (9) and / or first section (7).
    [3]
    3. Turbocharger according to claim 2, characterized in that the fastening device (5) consists of a material with a hardness of at least 40 HRC or of a hardened material with a surface hardness in the area of the curved surface of at least 40 HRC.
    [4]
    4. Turbocharger according to one of claims 1 to 3, characterized in that at least one ring (11; 23, 13) is arranged between the second section (9) of the fastening device (5) and the flange (10) of the bearing housing (2).
    [5]
    5. Turbocharger according to claim 4, characterized in that between the second section (9) of the fastening device (5) and the flange (10) of the bearing housing (2) a single ring (11) is arranged, which has a first side on the flange (10) of the bearing housing (2) and with a second side against the second section (9) of the fastening device (5).
    [6]
    A turbocharger according to claim 4 or 5, characterized in that the ring (11) has a coefficient of thermal expansion which corresponds to the coefficient of thermal expansion of the bearing housing (2).
    [7]
    7. Turbocharger according to claim 4, characterized in that two rings (12, 13) are arranged between the second section (9) of the fastening device (5) and the flange (10) of the bearing housing (2), a first ring (12) rests with a first side on the flange (10) of the bearing housing (2), a second ring (13) rests with a first side on the second section (9) of the fastening device (5), the two rings (12, 13) ) rest against each other with two sides.
    [8]
    8. Turbocharger according to claim 7, characterized in that the first ring (12) has a thermal expansion coefficient which corresponds to the thermal expansion coefficient of the bearing housing (2), and that the second ring (13) has a different thermal expansion coefficient.
    [9]
    9. Turbocharger according to one of claims 4 to 8, characterized in that the at least one ring (11) or the two rings (12, 13) together has an axial width B and a radial height H, with a ratio B: H ≤ 0 , 25 is.
    [10]
    10. Turbocharger according to one of claims 4 to 9, characterized in that the or each ring (11, 12, 13) consists of a material with a hardness of at least 40 HRC or of a hardened material with a surface hardness of at least 40 HRC,
    [11]
    11. Turbocharger according to one of claims 4 to 10, characterized in that the or each ring (11, 12, 13) is slotted in at least one circumferential position.
    [12]
    A turbocharger according to claim 7 and claim 11, characterized in that the first ring (12) is slotted to form an open ring at a single circumferential position, and that the second ring (13) is slotted to form a plurality of ring segments at a plurality of circumferential positions
    [13]
    A turbocharger according to claim 4 and claim 11, characterized in that the or each ring (11) is slotted at a single circumferential position to form an open ring.
    [14]
    14. Turbocharger according to one of claims 1 to 3, characterized in that the flange (10) designed as an integral assembly of the bearing housing (2) is hardened on a surface facing the second section (9) of the fastening device (5) and on this surface a Has a surface hardness of at least 40 HRC.
    [15]
    15. Turbocharger according to one of claims 1 to 3, characterized in that the flange (15) of the bearing housing (2) is designed as a separate assembly of the bearing housing, made of a hard or hardened material with a surface hardness of at least 40 HRC and is threaded on a base body (14) of the bearing housing (2) is mounted.
    [16]
    16. Turbocharger according to one of claims 1 to 15, characterized in that the fastening device (5) is segmented in the circumferential direction, each segment (5a) of the fastening device (5) with the respective first section (7) of the same via a maximum of two fastening means (8 ) is mounted on the flange (6) of the turbine housing (1).
    [17]
    17. Turbocharger according to claim 16 and claim 12, characterized in that the circumferential segment width of the segments (5a) of the fastening device (5) corresponds to the circumferential segment width of the ring segments of the second ring (13), so that between the first ring (12) and each segment ( 5a) of the fastening device (5) a corresponding ring segment of the second ring (13) is arranged in each case.
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    同族专利:
    公开号 | 公开日
    US10954963B2|2021-03-23|
    DE102016117960A1|2018-03-29|
    JP2018048632A|2018-03-29|
    CN107869365A|2018-04-03|
    CH712978A2|2018-03-29|
    KR20180033065A|2018-04-02|
    US20180087531A1|2018-03-29|
    JP6827897B2|2021-02-10|
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    DE102017207540A1|2017-05-04|2018-11-08|Man Diesel & Turbo Se|turbocharger|
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    法律状态:
    2018-07-31| PFA| Name/firm changed|Owner name: MAN ENERGY SOLUTIONS SE, DE Free format text: FORMER OWNER: MAN DIESEL AND TURBO SE, DE |
    优先权:
    申请号 | 申请日 | 专利标题
    DE102016117960.4A|DE102016117960A1|2016-09-23|2016-09-23|turbocharger|
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