• 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 turbine for a turbocharger, for relaxing a medium, comprising a turbine rotor having a turbine housing with an insert (13) extending radially outwardly adjacent rotor blades of the turbine rotor, the insert (13) having at an upstream end a first flange (16). and a second flange (17) at a downstream end, and wherein the insert (13) has an approximately constant thickness in a central portion (21) extending between the first flange (16) and the second flange (17) (D).
    公开号:CH714390A2
    申请号:CH01293/18
    申请日:2018-10-23
    公开日:2019-05-31
    发明作者:Braun Steffen；Klima Jiri；Hort Vladimir；Weisbrod Tobias；Haas Bernd；Niebuhr Johannes
    申请人:Man Energy Solutions Se；
    IPC主号:
    专利说明:

    Description [0001] The invention relates to a turbine and a turbocharger with a turbine.
    Fig. 1 shows the basic, known from the prior art, construction of a turbocharger. 1
    The turbocharger 1 has a turbine 2 for relaxing a first medium, in particular for the relaxation of exhaust gas of 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 wherein the bearing housing 9 is positioned between the turbine housing 4 and the compressor housing 5 and connected to both the turbine housing 4 and the compressor housing 5. Furthermore, FIG. 1 shows a compressor-side muffler 10.
    The turbine housing 4 of the turbine 2 comprises a Zuströmgehäuse 11 and a discharge housing 12. About the Zuströmgehäuse 11 can be supplied to the turbine rotor 5 in the region of the turbine 2 to relaxing first medium. Relaxed first medium flows away from the turbine 2 via the outflow housing 12 or via an exhaust pipe (not shown) in the region of the turbine rotor 5.
    The turbine housing 4 comprises in addition to the Zuströmgehäuse 11 and the outflow housing 12 an insert 13, wherein the insert 13 extends in particular in the region of the Zuströmgehäuses 11, adjacent to the turbine rotor 5 radially outwardly adjacent to blades 14 of the turbine rotor 5. The turbine housing further comprises a nozzle ring 15. The nozzle ring 15 is also referred to as Turbinenleitapparat.
    In operation, there may be a case of damage to the turbine 2. In this case, in particular fragments can be detached from the turbine rotor 5 and penetrate the turbine housing 4. This must be avoided. Therefore, it is already known from practice to equip a turbine 2 of a turbocharger 1 with a burst protection, for example an enclosure.
    There is a need to improve the burst protection by internal turbine measures to run, for example, an enclosure with less wall thickness, so as to realize cost and weight advantages.
    On this basis, the present invention seeks to provide a novel turbine and a novel turbocharger. This object is achieved by a turbine according to claim 1 and a turbocharger according to claim 10. According to the invention, the insert piece has an approximately constant thickness in a middle section which extends between the first flange and the second flange or in the region of the turbine wheel.
    The insert of the inventive turbine allows the turbine in case of damage kinetic energy of fragments of the turbine rotor defined intercept and break down, so that it is possible to implement other measures to containment security, such as an enclosure, simpler realization of cost and weight advantages and relieve adjacent structures.
    The thickness of the central portion of the insert is defined by the radial distance between a radially inner, flow-guiding wall of the insert and a radially outer wall of the insert, wherein the approximately constant thickness by a maximum ± 10% based on an average thickness the middle section changed. The average thickness of the central portion is preferably between 3% and 9% of a fitting diameter of the insert, the fitting diameter defined by a radial abutment surface formed on the first flange of the insert for a portion of the turbine housing. Hereby, the containment safety in the area of the turbine can be provided in a particularly advantageous manner, namely by providing cost and weight reductions.
    Preferred embodiments of the invention will become apparent from the dependent claims and the description below. Embodiments of the invention will be described, without being limited thereto, with reference to the drawings. Showing:
    1 shows a cross section through a turbocharger according to the prior art,
    2 shows a detail of a turbine according to the invention or of a turbocharger according to the invention,
    Fig. 3 shows a further detail of the inventive turbine or the inventive turbocharger.
    The present invention relates to a turbine and a turbocharger. The basic structure of a turbine and a turbocharger according to the prior art has already been described with reference to FIG. In the following, only details of a turbine according to the invention and of a turbocharger according to the invention will be discussed, by which the turbine differs from the prior art.
    2 and 3 show details of a turbine according to the invention of a turbocharger, FIG. 1 showing a section in the region of the insert 13, of the adjoining nozzle ring 15 and of the adjacent inflow housing 11 of the turbine housing 4.
    The insert 13 extends radially adjacent to the blades 14 of the turbine rotor 5 and at least partially limits a flow channel of the turbine. 2
    The insert 13 has a first flange 16 at an upstream end and a second flange 17 at a downstream end.
    At the first flange 16, the insert 13 comes to a portion 18 of the Zuströmgehäuses 11 of the turbine housing 4 to the plant, wherein on this flange 16 on the one hand an axial abutment surface 16a and on the other hand, a radial abutment surface 16b is formed for the portion 18 of the Zuströmgehäuses 11. The radial contact surface 16b in the region of this upstream flange 16 defines a so-called dowel diameter dp of the insert 13.
    At the opposite, downstream end of the second flange 17 of the insert 13 is formed, via which the insert 17 at the downstream end of the same with a further portion 19 of the inflow housing 11 of the turbine 2 cooperates, which is shown in FIG of the inflow housing 11, which forms a flange, and the second flange 17 of the insert 13 extend a plurality of screws 20 which press when tightening the flange 16 at the upstream end of the insert 13 against the portion 18 of the inflow housing 11, namely in the axial direction with the axial abutment surface 16a.
    Between the first flange 16 at the upstream end and the second flange 17 at the downstream end of the insert 13, a central portion 21 of the insert 13 is formed, this central portion 21 of the insert 13 is characterized by an approximately constant thickness D. This thickness D is defined by the radial distance between a radially inner, flow-carrying wall 13 a of the insert 13 and a radially outer wall 13 b of the insert 13.
    An approximately constant thickness D of this portion 21 of the insert 13 means that in the region of the portion 21, the thickness D, based on an average thickness of the central portion 21, by a maximum of ± 10% changed, preferably by a maximum of ± 7% , more preferably by a maximum of ± 5%.
    The approximately constant thickness changes particularly preferably by a maximum of ± 2 mm, based on the average thickness of the central portion 21st
    The average thickness is defined by an average of all the thicknesses of the central portion 21 along the axial extent thereof.
    The average thickness of the central portion 21 is in particular between 3% and 9%, preferably between 4% and 8%, particularly preferably between 5% and 7%, of the fitting diameter dp.
    The insert 13 is preferably a cast component that is already precast to final contour. Only in the region of the radially inner, flow-carrying wall 13a, a processing of the insert 13 is provided, which preferably takes place by turning.
    With the invention, in the event of damage by the insert 13, the kinetic energy of fragments of the turbine rotor 5 defined breakdown. Other containment safety measures can thus be made simpler, easier and less expensive. Furthermore, an optimum gap can be set between the insert 13 and the turbine rotor 5. In operation, there is no risk that the insert 13 due to thermal expansion in the direction of the turbine rotor 5 moves and reduces this gap.
    This results in improved thermal properties of the turbocharger through the defined wall thickness. By means of small and therefore flexible wall thicknesses, the stress due to the thermal expansion on the components is absorbed by elastically flexible deformation. The result is a more favorable flange load between the flange bearing housing / Turbinenzuströmgehäuse and an increase in efficiency through optimal smaller gap between the nozzle ring and insert.
    Another positive effect of the invention is that a break-off of the flange (flange bearing housing Turbinenzuströmgehäuse) is prevented in that the wall thickness is not only defined radially, but also in the transition region above the radial region. As a result, the force acting on this flange is held within the defined range.
    DESCRIPTION OF SYMBOLS Turbocharger 2 Turbine 3 Compressor 4 Turbine housing 5 Turbine rotor 6 Compressor housing 7 Compressor rotor 8 Shaft 9 Bearing housing 10 Silencer 11 Inflow housing 12 Outflow housing 13 Insert 13a Wall 13b Wall 14 Blade 15 Nozzle ring 16 Flange 16a Plating surface 16b Plating surface 17 Flange 18 Section 19 Section 20 screw 21 section
    权利要求:
    Claims (10)
    [1]
    A turbine for a turbocharger, for relaxing a medium, with a turbine rotor (5), with a turbine housing (4), with an insert (13) extending radially outwardly adjacent to blades (14) of the turbine rotor (5), wherein the insert (13) has a first flange (16) at an upstream end and a second flange (17) at a downstream end, characterized in that the insert (13) is located in a central portion (21) extending between the first flange (16) and the second flange (17) has an approximately constant thickness (D).
    [2]
    2. Turbine according to claim 1, characterized in that the thickness (D) by the radial distance between a radially inner, flow-carrying wall (13 a) and a radially outer wall (13 b) is defined.
    [3]
    3. Turbine according to claim 1 or 2, characterized in that the approximately constant thickness (D) between the first flange (16) and the second flange (17) by a maximum of ± 10% based on an average thickness of the central portion (21 ) changed.
    [4]
    4. Turbine according to one of claims 1 to 3, characterized in that the approximately constant thickness (D) between the first flange (16) and the second flange (17) by a maximum ± 2 mm based on an average thickness of the central portion (21) changed.
    [5]
    5. Turbine according to claim 3 or 4, characterized in that the average thickness of the central portion (21) between 3% and 9% of a fitting diameter (dp) of the insert piece (13).
    [6]
    6. Turbine according to claim 5, characterized in that the average thickness between 4% and 8% of the fitting diameter (dp) is.
    [7]
    7. Turbine according to claim 6, characterized in that the average thickness between 5% and 7% of the pass diameter (dp) is.
    [8]
    8. Turbine according to one of claims 5 to 7, characterized in that the fitting diameter (dp) by a at the first flange (16) of the insert (13) formed radial contact surface (16b) for a portion (18) of the turbine housing is defined.
    [9]
    9. Turbine according to one of claims 1 to 8, characterized in that the insert piece (13) via screws (20) extending through a flange (19) of a Zuströmgehäuses (11) of the turbine housing (4) and the second flange (17 ) of the insert (13), is bolted to the upstream housing (11) at the downstream end of the insert (13).
    [10]
    10. Turbocharger, comprising a turbine (2) for relaxing a first medium, with a compressor (3) for compressing a second medium, characterized in that the turbine (2) is designed according to one of claims 1 to 10.
    类似技术:
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    同族专利:
    公开号 | 公开日
    US20190153898A1|2019-05-23|
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    KR20190059246A|2019-05-30|
    US10876427B2|2020-12-29|
    CN109812302A|2019-05-28|
    DE102017127628A1|2019-05-23|
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    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    DE102017127628.9A|DE102017127628A1|2017-11-22|2017-11-22|Turbine and turbocharger|
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