• 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:
    A turbocharger having a turbine (2) for relaxing a first medium, with a compressor for compressing a second medium using energy recovered in the turbine (2) upon expansion of the first medium, the turbine (2) comprising a turbine housing and a turbine rotor (5), the compressor comprising a compressor housing and a compressor rotor (7) coupled to the turbine rotor (5) via a shaft (8), the turbine housing and the compressor housing each having a bearing housing (9) disposed therebetween the shaft (8) is mounted, the turbine housing having an inlet housing, a nozzle ring (15) with guide vanes (16) and an insert (13), and wherein the nozzle ring (15) via a projection (17) on the bearing housing (9) centered and guided radially.
    公开号:CH713305A2
    申请号:CH01340/17
    申请日:2017-11-07
    公开日:2018-06-29
    发明作者:Hossbach Björn
    申请人:Man Diesel & Turbo Se；
    IPC主号:
    专利说明:

    Description: The invention relates to a turbocharger.
    Fig. 1 shows the basic structure of a turbocharger 1 known from practice. A turbocharger 1 has a turbine 2 for relaxing a first medium, in particular for relaxing exhaust gas from an internal combustion engine, energy being obtained in the relaxation of the first medium , Furthermore, the turbocharger 1 comprises a compressor 3 for compressing a second medium, in particular charge air to be supplied from an internal combustion engine, using the energy obtained in the expansion of the first medium in the turbine 2.
    The turbine 1 has a turbine housing 4 and a turbine rotor 5. The compressor 3 has a compressor housing 6 and a compressor rotor 7. Turbine rotor 5 and compressor rotor 7 are coupled via a shaft 8 which is mounted in a bearing housing 9. The bearing housing 9 is connected on the one hand to the turbine housing 4 and on the other hand to the compressor housing 6.
    Fig. 1 also shows an optional muffler 10 which is connected to the compressor housing 6, wherein charge air is guided via the muffler 10.
    The turbine housing 4 comprises an inflow housing 11 and an outflow housing 12. Via the inflow housing 11, the first medium to be relaxed is supplied to the turbine rotor 5, here in the radial direction. The relaxed first medium can be discharged from the turbine rotor 5 via the outflow housing 12, here in the axial direction.
    As components of the turbine housing 4, FIG. 1 also shows an insert 13 and a nozzle ring 15. The insert 13 connects radially outside to blades 14 of the turbine rotor 5, and delimits a flow channel of the inflow housing 11 at least in sections. The nozzle ring 15 has guide vanes 16 which are positioned upstream of the turbine rotor 5 and which serve to guide the flow upstream of the turbine rotor 5.
    So far, the positioning of the insert and the nozzle ring has been difficult, in particular with regard to operational deformations in the area of the inflow housing 11 of the turbine housing 4. Thus, in known exhaust gas turbochargers, operational deformations in the area of the inflow housing 11 of the turbine housing 4 have an effect on the Positioning of insert and nozzle ring, as a result of which a gap between the rotor-side assemblies of the turbine 2 and the stator-side assemblies is subject to the same changes, which can excite the turbine rotor 5 to vibrate and, in extreme cases, lead to the blades 14 of the turbine rotor 5 being in the stator-side assemblies, in particular run into the insert 13 or rub against it.
    Based on this, the present invention seeks to provide a novel turbocharger. This object is achieved by a turbocharger according to claim 1. According to the invention, the nozzle ring is centered over a projection on the bearing housing and is guided radially.
    Characterized in that the nozzle ring is centered and guided radially over a projection on the bearing housing, the positioning of the nozzle ring is independent of the inflow housing of the turbine housing and thus also of operational deformations of the inflow housing.
    According to a development of the invention, the nozzle ring and the insert are made integrally and form a monolithic assembly. This development of the invention has the advantage that the insert, which forms a monolithic assembly together with the nozzle ring, is centered and guided radially over the projection of the nozzle ring on the bearing housing. Accordingly, the positioning of the insert is also independent of the inflow housing of the turbine housing and thus of operational deformations of the inflow housing.
    According to a further development of the invention, a portion of the inflow housing and a portion of the insert piece engage spring elements that press the nozzle ring and the insert piece axially in the direction of the bearing housing. The spring elements position the insert and the nozzle ring axially. The insert and nozzle ring, which preferably form a monolithic assembly, are pressed against the bearing housing and thus positioned in the axial direction via the spring elements which engage the insert and the inflow housing. The springs compensate for operational deformations in the area of the inflow housing.
    [0012] 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 restricted thereto. It shows
    1 shows a cross section through a turbocharger known from practice;
    2 shows a cross section through a turbocharger according to the invention in the region of the turbine of the turbocharger;
    3: a detail of the turbocharger according to the invention.
    [0013] The invention relates to a turbocharger.
    CH 713 305 A2 [0014] A turbocharger 1 has a turbine 2 for expanding a first medium, in particular for expanding exhaust gas from an internal combustion engine. Furthermore, a turbocharger 1 has a compressor 3 for compressing a second medium, in particular charge air, using energy obtained in the turbine 2 during the expansion of the first medium.
    The turbine 2 has a turbine housing 4 and a turbine rotor 5. The compressor 3 has a compressor housing 6 and a compressor rotor 7. The compressor rotor 7 is coupled to the turbine rotor 5 via a shaft 8 which is mounted in a bearing housing 9 is, the bearing housing 9 positioned between the turbine housing 4 and the compressor housing 5 and is connected to both the turbine housing 4 and the compressor housing 5.
    The turbine housing 4 has an inflow housing 11 and an outflow housing 12. About the inflow housing 11, which is connected to the bearing housing 9, the first medium to be relaxed can be guided in the radial direction on the turbine rotor 5. Relaxed, first medium can be discharged from the turbine rotor 5 in the axial direction via the outflow housing 12, which is connected to the inflow housing 11.
    The turbine housing 4 also has an insert 13 and a nozzle ring 15. The insert 13 limits sections of a flow channel for the first medium, the insert 13 connecting radially on the outside to the blades 14 of the turbine rotor 5. The nozzle ring 15, which comprises guide vanes 16, is positioned upstream of the turbine rotor 5, the guide vanes 16 serving to guide the flow of the first medium to be expanded upstream of the turbine rotor 5.
    In the sense of the present invention, the nozzle ring 15 is centered on the bearing housing 9 and guided radially via a projection 17 which is formed on a first cover ring 18 of the nozzle ring 15 facing the bearing housing 9. This projection 17 of the nozzle ring 15 engages in a corresponding groove 19 in the bearing housing 9. The centering and radial guidance of the nozzle ring 15 is therefore independent of the inflow housing 11 of the turbine housing 4 and thus independent of operational deformations of the inflow housing 11.
    According to an advantageous development of the invention, the nozzle ring 15 and the insert 13 are integrally formed and form a monolithic assembly according to FIG. 3. In this case, in addition to the first cover ring 18 facing the bearing housing 9, the nozzle ring 15 then comprises a second cover ring 20, the guide blades 16 of the nozzle ring 15 extending between the two cover rings 18, 20, which are spaced apart in the axial direction.
    The integral, monolithic design of the nozzle ring 15 and insert 13 not only centers and guides the nozzle ring on the bearing housing 9 radially, but rather also the insert 13 together with the nozzle ring 15.
    According to a further advantageous development of the invention engage on a section of the inflow housing 11 of the turbine housing 4 and on a section of the insert 13, in the embodiment shown in FIG. 2 on the second cover ring 20 of the nozzle ring 15, which together with the insert 13 forms a monolithic assembly, spring elements 21, which press the insert 13 and thus the nozzle ring 15 in the axial direction against the bearing housing 9, that is to say press the projection 17 on the first cover ring 18 of the nozzle ring 15 axially into the groove 19 of the bearing housing 9. Spring elements 21 accordingly position insert 13 and nozzle ring 15 in the axial direction.
    The spring elements 21 are guided on pin-like projections 22 of the inflow housing 11.
    2, a sealing element 23 is positioned downstream of the turbine rotor 5 between the insert 13 and an adjacent section of the inflow housing 11, around the insert 13, in particular the monolithic assembly consisting of insert 13 and nozzle ring 15, downstream of the rotor blades 14 of the turbine rotor 5 to seal against the inflow housing 11.
    According to a particularly preferred embodiment of the invention, insert 13 and nozzle ring 15 are accordingly designed as a monolithic assembly, this monolithic assembly being centered and guided radially over a projection 17 of the nozzle ring 15 on the bearing housing 9, and with spring elements 21 in this monolithic assembly Position the axial direction, namely press against the bearing housing 9 in the axial direction. Deformations of the inflow housing 11 of the turbine housing 4 caused by operation then have no influence on the positioning of the nozzle ring 15 and insert 13, so that an exact gap can then always be maintained, in particular between the rotor blades 14 of the turbine rotor 5 and the insert 13, as a result of which the rotor blades 14 touch of the turbine rotor 5 in the insert 13 is avoided.
    LIST OF REFERENCE NUMERALS [0025]
    turbocharger
    turbine
    compressor
    CH 713 305 A2
    turbine housing
    turbine rotor
    compressor housing
    compressor rotor
    wave
    bearing housing
    silencer
    inflow housing
    outflow housing
    insert
    blade
    nozzle ring
    vanes
    head Start
    cover ring
    groove
    cover ring
    spring element
    head Start
    sealing element
    权利要求:
    Claims (9)
    [1]
    claims
    1. Turbocharger (1), with a turbine (2) for expanding a first medium, with a compressor (3) for compressing a second medium using energy obtained in the turbine (2) when expanding the first medium, the turbine (2) has a turbine housing (4) and a turbine rotor (5), the compressor (3) having a compressor housing (6) and a compressor rotor (7) coupled to the turbine rotor (5) via a shaft (8), the The turbine housing (4) and the compressor housing (6) are each connected to a bearing housing (9) arranged between them, in which the shaft (8) is mounted, the turbine housing (4) being an inflow housing (10), a nozzle ring (15 ) with guide vanes (16) and an insert (13), characterized in that the nozzle ring (15) is centered and guided radially via a projection (17) on the bearing housing (9).
    [2]
    2. Turbocharger according to claim 1, characterized in that the projection (17) of the nozzle ring (15) engages in a groove (19) in the bearing housing (9).
    [3]
    3. Turbocharger according to claim 1 or 2, characterized in that the projection (17) of the nozzle ring (15) is formed on a first cover ring (18) of the nozzle ring (15).
    [4]
    4. Turbocharger according to claim 3, characterized in that the nozzle ring (15) has a second cover ring (20), guide vanes (16) of the nozzle ring (15) extending between the first cover ring (18) and the second cover ring (20) ,
    [5]
    5. Turbocharger according to one of claims 1 to 4, characterized in that the nozzle ring (15) and the insert (13) are made integrally.
    CH 713 305 A2
    [6]
    6. Turbocharger according to one of claims 1 to 5, characterized in that the nozzle ring (15) and the insert (13) are designed as a monolithic assembly.
    [7]
    7. Turbocharger according to one of claims 1 to 6, characterized in that on a section of the inflow housing (11) and on a section of the insert (13) act on spring elements (21) which insert (21) and the nozzle ring (15) push towards the bearing housing (9).
    [8]
    8. Turbocharger according to claim 7, characterized in that the spring elements (21) axially position the insert (13) and the nozzle ring (15).
    [9]
    9. Turbocharger according to one of claims 1 to 8, characterized in that a sealing element (23) is positioned downstream of the turbine rotor (5) between the inflow housing (11) and the insert (13).
    CH 713 305 A2
    SA νκ
    CH 713 305 A2
    CH 713 305 A2
    3.3
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    同族专利:
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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
    DE102016125189.5A|DE102016125189B4|2016-12-21|2016-12-21|turbocharger|
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