• 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 (1) for expanding a first medium, with a compressor for compressing a second medium using the energy obtained in the turbine during the expansion of the first medium, the turbine (1) having a turbine housing (3) and a Turbine rotor (6), the compressor having a compressor housing and a compressor rotor coupled to the turbine rotor (6) via a shaft (7), the turbine housing (3) and the compressor housing each having a bearing housing (2) arranged between them, in which the shaft (7) is mounted, the turbine housing (3) having a turbine inflow housing (4) and receiving an insert (5) and a nozzle ring (9) with guide vanes (11), the nozzle ring (9) on a first cover ring (12) of the same is connected via first fastening means (13) to a flange (14) of the bearing housing (2), wherein on the flange (14) of the bearing housing (2) with which the the first cover ring (12) of the nozzle ring (9) is connected, a plurality of radially outwardly extending projections (15) are formed distributed over the circumference, the first fastening means (13) being the projections (15) of the flange (14) of the bearing housing ( 2) penetrate and engage with the first cover ring (12) of the nozzle ring (9).
    公开号:CH713774B1
    申请号:CH00355/18
    申请日:2018-03-20
    公开日:2021-06-15
    发明作者:Hossbacht Björn；Uhlenbrock Santiago
    申请人:Man Energy Solutions Se；
    IPC主号:
    专利说明:

    The invention relates to a turbocharger.
    A turbocharger has a turbine and a compressor. A first medium, in particular exhaust gas, is expanded in the turbine of a turbocharger and energy is obtained in the process. A second medium, in particular charge air, is compressed in the compressor of the turbocharger using the energy obtained in the turbine when the first medium is expanded. The turbine of a turbocharger has a turbine housing and a turbine rotor. The compressor of the turbocharger has a compressor housing and a compressor rotor. The turbine rotor and compressor rotor are coupled via a shaft which is mounted in a bearing housing, the bearing housing being connected on the one hand to the turbine housing and on the other hand to the compressor housing.
    It is also known from practice that the turbine housing of a turbocharger has a turbine inflow housing through which the first medium to be relaxed can be fed to the turbine rotor. The turbine housing receives an insert and a nozzle ring. The expanded first medium can be discharged from the turbine via the insert, the insert extending radially outwardly adjacent to the rotor blades of the turbine rotor. The nozzle ring, which is also referred to as a turbine guide device or guide grille or guide device, has guide vanes which are positioned upstream of the turbine rotor, viewed in the direction of flow of the first medium, and via which the first medium to be expanded is guided upstream of the turbine rotor.
    In turbochargers known from practice, the turbine inflow housing is typically connected to the bearing housing via a clamping claw connection, the nozzle ring is also attached via the clamping claw connection, namely in that a flange of the nozzle ring is clamped between flanges or fastening sections of the bearing housing and turbine inflow housing .
    In turbochargers known from practice, the nozzle ring and the turbine inflow housing are therefore mounted on the bearing housing together or as a function of one another.
    In operation, the nozzle ring is subject to thermally induced deformation. In turbochargers known from practice, this means that the connection of the nozzle ring, bearing housing and turbine inflow housing is also subjected to deformation, which on the one hand causes wear on this connection and on the other hand reduces the sealing effect in the area of this connection. This is a disadvantage. There is therefore a need to more reliably attach the nozzle ring to the bearing housing of the turbocharger.
    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. According to the invention, the nozzle ring is connected on a first cover ring of the same via first fastening means to a flange of the bearing housing, with a plurality of radially outwardly extending projections being formed on the flange of the bearing housing to which the first cover ring of the nozzle ring is connected, distributed over the circumference, wherein the first fastening means penetrate the projections of the flange of the bearing housing and are in engagement with the first cover ring of the nozzle ring.
    The connection of the nozzle ring with the flange of the bearing housing via the first fastening means, which act on the projections of the flange of the bearing housing, allows a reliable fastening of the nozzle ring on the bearing housing. Stresses, in particular tangential stresses, in the flange of the bearing housing are reduced, in particular by virtue of the fact that the projections of the flange of the bearing housing can deform more quickly and thus more evenly together with the nozzle ring as a result of temperature.
    Preferably, the first fastening means extend in the axial direction, starting from the bearing housing in the direction of the turbine housing, through the projections of the flange of the bearing housing into the first cover ring of the nozzle ring. This allows a particularly advantageous assembly of the nozzle ring on the bearing housing.
    According to a development of the invention, the nozzle ring is connected to a second cover ring of the same via second fastening means with a flange of the insert, wherein the second fastening means penetrate the flange of the insert and are in engagement with the second cover ring of the nozzle ring, preferably such that the second fastening means extend in the axial direction starting from the turbine housing in the direction of the bearing housing through the flange of the insert into the second cover ring of the nozzle ring. These features allow a particularly advantageous assembly of the insert on the nozzle ring.
    According to a development of the invention, the turbine inflow housing is fastened independently of the nozzle ring via separate fastening means on the bearing housing. This is preferred in order to ensure a good sealing effect of the connection between the turbine inflow housing and the bearing housing and thus to avoid undesired leakage of the first medium to be expanded in the turbine into the environment.
    Preferred developments of the invention emerge from the dependent patent 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 in the axial direction through a turbocharger according to the invention in the area of a turbine and a bearing housing; FIG. 2: a perspective view of the arrangement of FIG. 1 with an insert piece only partially shown and also only partially shown turbine inlet housing; FIG. FIG. 3: the arrangement of FIG. 2 with the nozzle ring likewise only partially shown.
    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.
    1 to 3 show different views of a section of a turbocharger in the area of a turbine 1 and a bearing housing 2. The turbine 1 comprises a turbine housing 3 and a turbine rotor 6. A compressor, not shown, of the turbocharger has a compressor housing and a Compressor rotor, the turbine rotor 6 being coupled to the compressor rotor (not shown) via a shaft 7 which is rotatably supported in the bearing housing 2. The turbine 1 of the turbocharger is designed as a radial turbine. For the purposes of this invention, radial turbines are also to be understood as so-called mixed flow turbines, in which the gas flows in in the radial direction, but not only exactly perpendicular to the shaft 7, but at an angle to the shaft 7.
    The turbine housing 3 comprises a turbine inflow housing 4, which is double-walled in the exemplary embodiment shown and forms a cooling channel 10 for cooling the turbine inflow housing 4. The first medium to be expanded, preferably hot exhaust gas, can be fed to the turbine rotor 6 via the turbine inflow housing 4.
    The turbine housing 3 receives an insert 5 and a nozzle ring 9. The nozzle ring 9 has guide vanes 11 which serve to guide the flow of the first medium to be expanded upstream of the turbine rotor 6. The turbine rotor 6 is bladed with rotor blades 8, which are accordingly positioned downstream of the guide blades 11 of the nozzle ring 9 as seen in the flow direction of the exhaust gas. Downstream of the nozzle ring 9, the insert 5 defines the flow channel for the first medium, radially outwardly adjacent to the rotor blades 8 of the turbine rotor 6, wherein the first medium expanded in the turbine 1 can be discharged from the turbine 1 via the insert 5.
    In the turbocharger according to the invention, the nozzle ring 9 is connected to a first cover ring 12 of the same via first fastening means 13 with a flange 14 of the bearing housing 2, on the flange 14 of the bearing housing 2, with which the first cover ring 12 of the nozzle ring 9 is connected, A plurality of radially outwardly extending projections 15 are formed distributed over the circumference thereof.
    These projections 15 can also be referred to as tabs or rosettes. The first fastening means 13 penetrate these tab-like or rosette-like projections 15 of the flange 14 of the bearing housing 2 and engage the first cover ring 12 of the nozzle ring 9.
    1, seen in the axial direction, the first fastening means 13 extend from the bearing housing 2 in the direction of the turbine housing 3 through the projections 15 of the flange 14 of the bearing housing 2 into the first cover ring 12 of the nozzle ring 11. The first fastening means 13 are preferably designed as threaded bolts which have an external thread on those sections that extend into the first cover ring 12 of the nozzle ring 9, these external threads then with corresponding internal threads in threaded bores 16 of the first cover ring 12 of the nozzle ring 9 are engaged. On opposite sections of these threaded bolts, which protrude in the axial direction from the flange 14 or the projections 15 formed on the flange 14 of the bearing housing 2, an external thread is also formed which cooperates with corresponding nuts 24 in order to securely and easily attach the nozzle ring 9 Mount the bearing housing 2. The nuts 24 are supported on the flange 14 of the bearing housing 2 via sleeves 25. The sections of the threaded bolts which extend through the tab-like or rosette-like projections 15 of the flange 14 of the bearing housing 2 and are arranged between the sections of the threaded bolts carrying the external threads are preferably threadless.
    The nozzle ring 9 is connected to a second cover ring 17 opposite the first cover ring 12 via second fastening means 18 with a flange 19 of the insert, the second fastening means 18 penetrating the flange 19 of the insert 15 and with the second cover ring 17 of the nozzle ring 9 are engaged. The second fastening means 19, which in turn are preferably threaded bolts, extend in the axial direction starting from the turbine housing 3 in the direction of the bearing housing 2 through the flange 19 of the insert 5 into the second cover ring 17 of the nozzle ring 9.
    So while the first fastening means 13, which are used to fasten the nozzle ring 9 on the bearing housing 2, seen in the axial direction, extending from the bearing housing 2 in the direction of the turbine housing into the first cover ring 12 of the nozzle ring 9, the second fastening means extend 18 rotated by approximately 180 ° or in the opposite axial direction starting from the insert 5 or starting from the turbine housing 3 in the direction of the bearing housing 2 into the second cover ring 17 of the nozzle ring 9.
    As already stated, the second fastening means 18 are in turn preferably via threaded bolts which have external threads on opposite sections, namely a first external thread on first sections which engage in corresponding threaded bores 20 of the second cover ring 17 of the nozzle ring 9, and further external threads on opposite second sections which interact with a nut 26 in order to fasten the insert 5 to the nozzle ring 9. These nuts 26 are supported on the flange 19 of the insert 5 via sleeves 27. Between these sections of the threaded bolts which carry the external thread, the same are preferably designed without a thread at sections which extend through the flange 19 of the insert piece 5.
    The turbine inflow housing 4 of the turbine housing 3 is attached independently of the nozzle ring 9 and independently of the insert 5 on the bearing housing 2, in the embodiment shown in FIGS Clamping ring 23 engages.
    In contrast to such a clamping ring 23, the adjacent flanges 21, 22 of the bearing housing 2 and the turbine inflow housing 4 can also be connected to one another via a clamping claw connection and / or screw connections.
    In the turbocharger according to the invention, therefore, the fastening of the nozzle ring 9 on the bearing housing 2 takes place via first fastening means 13, which cooperate on the one hand with the flange 14 of the bearing housing 2 and on the other hand with the first cover ring 12 of the nozzle ring 9, in the region of the flange 14 of the Bearing housing 2, the radial projections 15 of the flange 14, which can also be referred to as tabs or rosettes, penetrate. These projections 15 can expand together with the nozzle ring 9, as a result of which stresses in the connection between the bearing housing 2 and the nozzle ring 9 are minimized. The insert 5 is fastened to the nozzle ring 9 by means of second fastening means 18. The turbine inflow housing 4 is mounted on the bearing housing 2 independently of this. For assembly, the insert 5 is first mounted on the nozzle ring 9 via the second fastening means 18, the preassembled unit consisting of the insert 5 and the nozzle ring 9 being fastened to the bearing housing 2 via the first fastening means 13. Subsequently, the turbine inflow housing 4 can be mounted on the bearing housing 2.
    List of reference symbols
    1 turbine 2 bearing housing 3 turbine housing 4 turbine inflow housing 5 insert 6 turbine rotor 7 shaft 8 rotor blade 9 nozzle ring 10 channel 11 guide vane 12 cover ring 13 fastening means 14 flange 15 projection 16 threaded hole 17 cover ring 18 fastening means 19 flange 20 threaded hole 21 flange 22 flange 23 fastening means 24 Nut 25 sleeve 26 nut 27 sleeve
    权利要求:
    Claims (6)
    [1]
    1. turbocharger,with a turbine (1) for the expansion of a first medium,with a compressor for compressing a second medium using the energy gained in the turbine during the expansion of the first medium,wherein the turbine (1) has a turbine housing (3) and a turbine rotor (6),wherein the compressor has a compressor housing and a compressor rotor coupled to the turbine rotor (6) via a shaft (7),wherein the turbine housing (3) and the compressor housing are each connected to a bearing housing (2) arranged between them and in which the shaft (7) is mounted,wherein the turbine housing (3) has a turbine inflow housing (4) and receives an insert (5) and a nozzle ring (9) with guide vanes (11), characterized in thatthe nozzle ring (9) is connected to a first cover ring (12) of the same via first fastening means (13) with a flange (14) of the bearing housing (2), the flange (14) of the bearing housing (2) with which the first Cover ring (12) of the nozzle ring (9) is connected, several radially outwardly extending projections (15) are formed distributed over the circumference, the first fastening means (13) being the projections (15) of the flange (14) of the bearing housing (2 ) penetrate and are in engagement with the first cover ring (12) of the nozzle ring (9).
    [2]
    2. Turbocharger according to claim 1, characterized in that the first fastening means (13) are seen in the axial direction starting from the bearing housing (2) in the direction of the turbine housing (3) through the projections (15) of the flange (14) of the bearing housing (2) extend through into the first cover ring (12) of the nozzle ring (9).
    [3]
    3. Turbocharger according to claim 1 or 2, characterized in that the nozzle ring (9) is connected to a second cover ring (17) of the same via second fastening means (18) with a flange (19) of the insert piece (5), the second fastening means ( 18) penetrate the flange (19) of the insert (5) and engage with the second cover ring (17) of the nozzle ring (9).
    [4]
    4. Turbocharger according to claim 3, characterized in that the second fastening means (18) in the axial direction starting from the turbine housing (3) in the direction of the bearing housing (2) seen through the flange (19) of the insert (5) into the second cover ring (17) of the nozzle ring (9) extend into it.
    [5]
    5. Turbocharger according to one of Claims 1 to 4, characterized in that the turbine inflow housing (4) is fastened to the bearing housing (2) via a separate fastening means (23) independently of the nozzle ring (9).
    [6]
    Turbocharger according to one of Claims 1 to 5, characterized in that the turbine is a radial turbine.
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    同族专利:
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    US10519808B2|2019-12-31|
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    DE102017105756A1|2017-03-17|2018-09-20|Man Diesel & Turbo Se|turbocharger|DE102017103980A1|2017-02-27|2018-08-30|Man Diesel & Turbo Se|turbocharger|
    DE102017215539A1|2017-09-05|2019-03-07|Man Diesel & Turbo Se|turbocharger|
    DE102018107304A1|2018-03-27|2019-10-02|Man Energy Solutions Se|turbocharger|
    法律状态:
    2018-11-30| 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
    DE102017207540.6A|DE102017207540A1|2017-05-04|2017-05-04|turbocharger|
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