• 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, the turbine having a turbine housing and a turbine rotor (2), with a compressor for compressing a second medium using energy obtained in the turbine when the first medium expands, the compressor having a compressor housing and a compressor rotor coupled to the turbine rotor (2) via a shaft (3), with a bearing housing (1) arranged between the turbine housing and the compressor housing, both the turbine housing and the compressor housing being connected to the bearing housing (1), and wherein the bearing housing (1) is closed on a side facing the turbine by a sealing cover, which is adjoined by a sealing cover adjacent to the turbine rotor (2), the sealing and sealing cover being designed as a one-piece component (7).
    公开号:CH713777B1
    申请号:CH00495/18
    申请日:2018-04-17
    公开日:2022-02-15
    发明作者:Löwlein Oswald；Rössler Martin；Köhler Matthias
    申请人:Man Energy Solutions Se；
    IPC主号:
    专利说明:

    The invention relates to a turbocharger.
    A turbocharger has a compressor and a turbine. A first medium is expanded in the turbine and energy is obtained in the process, the energy obtained in the turbine being used to compress a second medium in the compressor. In an exhaust gas turbocharger, the first medium expanded in the turbine is exhaust gas from an internal combustion engine and the second medium compressed in the compressor is charge air to be supplied to an internal combustion engine.
    [0003] DE 20 2014 002 981 U1 discloses an exhaust gas turbocharger with a turbine designed as an axial turbine. It is also known from this prior art that a shaft, via which a turbine rotor is coupled to a compressor rotor, is rotatably mounted in a bearing housing, the bearing housing being closed by a sealing cover on a side facing the turbine rotor. Furthermore, an end cap is positioned between the sealing cap and the turbine rotor, the end cap together with the sealing cap delimiting a blocking air flow channel in sections in order to guide blocking air in the direction of the turbine rotor. Sealing air can be supplied from the compressor or an external source to the sealing air flow channel formed between the sealing cover and the end cover, specifically via sealing air channels that are introduced into the bearing housing and into the sealing cover.
    There is a need for a turbocharger that can be manufactured with less effort.
    Proceeding from this, the object of the present invention is to create a new type of turbocharger. This object is achieved by a turbocharger according to claim 1. According to the invention, the sealing cover and the end cover are designed as a one-piece component. In the turbocharger according to the invention, the sealing cover and the closing cover, which are arranged between the bearing housing and the turbine, are designed as a one-piece and therefore integral component. This considerably simplifies the production of a turbocharger. Functional parts that were previously designed as two separate components are combined to form a one-piece component. Accordingly, mechanical processing is only required on one component. A chain of tolerances between the sealing cover and end cover is eliminated. By designing the sealing cover and end cover as a one-piece component, not only can the manufacturing effort be reduced, but the available installation space can also be better utilized.
    According to an advantageous development of the invention, at least one guide channel for sealing air is introduced into this combined component. The sealing air can be optimally supplied to a sealing surface between the shaft or the turbine rotor and the one-piece component via the guide channel or each guide channel.
    [0007] A sealing air flow channel is preferably formed between a radially outer surface of the bearing housing and a radially inner surface of an internal exhaust gas diffuser, the radially outer surface of which delimits an exhaust gas diffuser channel in sections. Accordingly, no flow channel has to be integrated into the bearing housing to form the blocking air flow channel; rather, the flow channel is delimited by the radially outer contour of the bearing housing that is present anyway and the radially inner contour of the exhaust gas inner diffuser that is present anyway. In this way, too, the production costs for the turbocharger can be further reduced. However, it is still possible to supply the sealing air through holes in the bearing housing.
    Preferably, the one-piece component consisting of the sealing cover and end cap has at least one groove radially on the outside for receiving a sealing element, in order to seal the one-piece component consisting of the sealing cover and end cap in relation to the exhaust gas inner diffuser. These details allow an optimal sealing of the sealing air space to the exhaust gas space.
    According to an advantageous development of the invention, a sealing surface is formed radially inward on the one-piece component consisting of the sealing cover and end cap, which cooperates with sealing tips of a labyrinth seal on the turbine rotor side. This allows optimal sealing of the rotor, namely the interior of the bearing, from the exhaust gas.
    Preferred developments of the invention result 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 limited thereto. 1 shows a detail from a turbocharger according to the invention in the area of an axial turbine.
    The invention relates to a turbocharger. Fig. 1 shows a section of a turbocharger according to the invention in the area of a bearing housing 1 and a turbine rotor 2 of a turbine not shown in detail. The turbine rotor 2 is coupled via a shaft 3 to a compressor rotor of a compressor, not shown. 1 shows a bearing 4, via which the shaft 3, which couples the turbine rotor 2 to the compressor rotor (not shown), is mounted in the bearing housing 1.
    The bearing 4 is held on the bearing housing 1 via a bearing cap 5, the bearing cap 5 having radially inward sealing tips 6 which bear against a surface of the shaft 3 and together with this surface of the shaft 3 form a labyrinth seal.
    In the turbocharger according to the invention, a one-piece component 7 is positioned between the bearing housing 1 and the turbine rotor 2, which on the one hand provides the function of a sealing cover and on the other hand an end cover, which are designed as separate components in turbochargers known from practice.
    The bearing housing 1 is sealed on the side facing the turbine rotor 2 via the one-piece component 7 consisting of the sealing cover and end cover, in order to prevent oil from escaping from the bearing housing 1 in the direction of the turbine rotor 2, with the one-piece component 7 being Sealing cover and end cover at least one guide channel 8 for sealing air is introduced in order to supply sealing air to a sealing area 9, which is formed between a radially inner peripheral surface of the one-piece component 7 and a radially outer peripheral surface of a labyrinth ring arranged on the shaft 3 or a surface formed directly on the shaft The labyrinth ring or the turbine shaft has sealing tips on its radially outer surface, which form a sealing gap with the radially inner peripheral surface of the one-piece component 7 and together with this peripheral surface of the one-piece component 7 form a labyrinth seal in the sealing area 9 . The labyrinth disk 10 can be fixed to the shaft 3 via a nut 11 .
    As already mentioned, the sealing area 9 of the labyrinth seal can be acted upon by sealing air via the or each guide channel 8 integrated into the one-piece component 7, with preferably several such guide channels 8 for sealing air being introduced into the one-piece component 7 and distributed over the circumference end in an annular channel for even, annular distribution on the shaft.
    The or each guide duct 8 of the one-piece component 7 can be supplied with the sealing air from the compressor (not shown) or an external sealing air source via a sealing air flow duct 12, which in the exemplary embodiment shown flows on the one hand from a radially outer surface 13 of the bearing housing 1 and on the other hand from a radial inner surface 14 of an internal exhaust gas diffuser 15 adjoining the bearing housing 1 radially on the outside. The radially inner surface 14 of the exhaust gas inner diffuser 15 is therefore positioned radially outside of the radially outer surface 13 of the bearing housing 1, so that the sealing air flow channel 12 is formed between the surfaces 13, 14 of the bearing housing 1 and the exhaust gas inner diffuser 15, over which the guide channels 8 of the monolithic assembly 7 sealing air can be supplied from sealing cover and cover plate. In another version, the sealing air can also be introduced axially into the combined component through axial bores in the bearing housing and fed to the sealing point.
    As Fig. 1 shows, the exhaust gas inner diffuser 15 is supported on one end of the bearing housing 1 facing the turbine rotor 2 via projections 16 on the bearing housing 1, which at defined circumferential positions of the exhaust gas inner diffuser 13 project radially inwards in relation to the radially inner surface 14 of the same Project towards the bearing housing 1, wherein between such projections 16, the sealing air can flow in the direction of the guide channels 8 of the one-piece component 7. On a radially outer surface 21, the exhaust gas inner diffuser 15 delimits an exhaust gas flow channel 22 in order to discharge expanded exhaust gas from the turbine rotor 2.
    According to Fig. 1, the one-piece component 7 made up of sealing cover and end cap has at least one groove 17 radially on the outside, in the embodiment shown two grooves 17, in which a sealing element 18 is positioned so that the one-piece component 7 made up of sealing cover and end cap is opposite the exhaust gas inner diffuser 15, namely the radially inner surface 14 thereof, to seal against exhaust gas. These sealing elements 18 accommodated in the grooves 17 bear against a section 14a of the inner surface 14 of the exhaust gas inner diffuser 15 .
    A sealing element 19, preferably designed as a flat gasket, is arranged between the bearing housing 1 and the one-piece component 7 made up of the sealing cover and end cap, in order to seal against the flange surfaces of the bearing housing 1 and the one-piece component 7 that are in contact with one another in the axial direction against oil escaping from the interior of the bearing.
    Although not shown in Fig. 1, the one-piece component 7 made up of sealing cover and end cover can have a sealing element, for example sealing tips of a labyrinth seal, on an axial end face which faces the turbine rotor 2, in order to seal the exhaust gas 20 between the turbine rotor 2 and the one-piece component 7 consisting of the sealing cover and end cover as far outward as possible in order to generate a piston surface on the rotor which causes thrust equalization. This is optionally performed if necessary.
    In the turbocharger according to the invention, the sealing cover and cover plate, which have hitherto been designed as separate components, are therefore designed as a one-piece component. Accordingly, previously separate components are integrated into one component, which simplifies the manufacturing and assembly costs. A tolerance chain that previously existed between the separate components is eliminated. Available installation space is better utilized. Fewer parts have to be manufactured. In addition to the assembly effort, manufacturing costs are also reduced. The sealing air flow is ensured via guide channels introduced into the one-piece component.
    In the embodiment shown, the guide channels 8 extend from radially outside to radially inside such that the guide channels 8 are at least partially inclined relative to the radial direction. In this way, sealing air can be guided optimally to the sealing area 9 while ensuring a compact design. The guide channels 8 open into an annular channel which distributes the sealing air evenly over the circumference of the labyrinth seal.
    The guide channels 8 of the one-piece component 7 can be drilled, milled or cast guide channels 8 .
    reference list
    1 bearing housing 2 turbine rotor 3 shaft 4 bearing 5 bearing cap 6 sealing tip 7 one-piece component 8 guide channel 9 labyrinth seal 10 labyrinth disk 11 nut 12 sealing air flow channel 13 surface 14 surface 15 exhaust gas inner diffuser 16 projection 17 groove 18 seal 19 seal 20 axial gap 21 surface 22 exhaust gas flow channel
    权利要求:
    Claims (8)
    [1]
    1. turbocharger,with a turbine for expanding a first medium, the turbine having a turbine housing and a turbine rotor (2),with a compressor for compressing a second medium using energy obtained in the turbine when the first medium expands, the compressor having a compressor housing and a compressor rotor coupled to the turbine rotor (2) via a shaft (3),with a bearing housing (1) arranged between the turbine housing and the compressor housing, both the turbine housing and the compressor housing being connected to the bearing housing (1), and the bearing housing (1) being supported by a one-piece component (7 ) is closed, which forms a sealing and closing cover adjoining the turbine rotor (2).
    [2]
    2. Turbocharger according to Claim 1, characterized in that at least one guide channel (8) for sealing air is introduced into the one-piece component (7).
    [3]
    3. Turbocharger according to Claim 1, characterized in that a plurality of guide channels (8) for sealing air are introduced into the one-piece component (7) and are distributed over the circumference of the component (7).
    [4]
    4. Turbocharger according to one of Claims 1 to 3, characterized in that a sealing surface which interacts with sealing tips of a labyrinth on the turbine rotor side is formed radially on the inside of the one-piece component (7).
    [5]
    5. Turbocharger according to one of claims 2 to 4, characterized in that between a radially outer surface (13) of the bearing housing (1) and a radially inner surface (14) of an exhaust gas inner diffuser (15), which radially outwardly delimits an exhaust gas diffuser channel in sections Sealing air flow channel (12) is formed, the sealing air to the or each guide channel (8) of the one-piece component (7) leads.
    [6]
    6. Turbocharger according to Claim 5, characterized in that the one-piece component (7) has at least one groove (17) radially on the outside for receiving a sealing element (18) in order to seal the one-piece component (7) with respect to the exhaust gas inner diffuser (15).
    [7]
    7. Turbocharger according to one of Claims 1 to 6, characterized in that sealing tips of a labyrinth seal or their mating surface are formed on an axial end face of the one-piece component (7) facing the turbine rotor (2).
    [8]
    8. Turbocharger according to any one of Claims 1 to 7, characterized in that the turbine is an axial turbine.
    类似技术:
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    DE102015014613A1|2016-07-21|Sealing arrangement of a shaft on a housing element of an exhaust gas turbocharger
    DE102015009900A1|2017-02-02|Method for testing an exhaust gas turbocharger and method for testing an internal combustion engine
    同族专利:
    公开号 | 公开日
    DE102017208117A1|2018-11-15|
    KR20180125381A|2018-11-23|
    CN108868914A|2018-11-23|
    JP2018193993A|2018-12-06|
    CH713777A2|2018-11-15|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US2925215A|1957-06-20|1960-02-16|United Aircraft Corp|Lubrication system|
    DE102013203455A1|2013-02-28|2014-08-28|Abb Turbo Systems Ag|Partition wall for sealing the rear space of a centrifugal compressor|
    JP6195308B2|2014-06-25|2017-09-13|三菱重工業株式会社|Axial-flow turbine labyrinth seal device and exhaust gas turbocharger equipped with the same|
    GB2522498B|2014-07-17|2016-02-10|Napier Turbochargers Ltd|Turbocharger|
    JP6242833B2|2015-03-23|2017-12-06|三菱重工業株式会社|Exhaust turbine turbocharger|
    CN204804889U|2015-06-25|2015-11-25|重庆德蚨乐机械制造有限公司|Booster and turbine apparatus thereof|
    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    DE102017208117.1A|DE102017208117A1|2017-05-15|2017-05-15|turbocharger|
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