• 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 turbine rotor, with a rotor base body (2), with rotor blades (3) formed integrally on the rotor base body (2), the rotor blades (3) being designed without outer shroud, the rotor blades (3) having a defined curvature region (4) with a defined, constant or variable radius of curvature rf merge into the rotor base body (2). For a first group of first rotor blades (3), the following relationship applies to the radius of curvature of the region of curvature (4) of the first rotor blades (3): 2.5% r f1 * 100 / l 10%, where r f1 is the constant or variable radius of curvature of the curvature region of the first rotor blades and I is the length of the first rotor blades at a flow trailing edge. On a second group of second rotor blades (3), the radius of curvature r f2 of the region of curvature (4) of the second rotor blades (3) deviates in a defined manner on the damping side from the radius of curvature r f1 of the region of curvature (4) of the first rotor blades (3). Fig. 5
    公开号:CH716356A2
    申请号:CH00621/20
    申请日:2020-05-26
    公开日:2020-12-30
    发明作者:Bornhorn Alfons；Rost Stefan；Leitenmeier Christoph；Figaschewsky Felix；Bernd Beirow；Kühhorn Arnold
    申请人:Man Energy Solutions Se；
    IPC主号:
    专利说明:

    The invention relates to a turbocharger turbine rotor and a turbocharger with such a turbocharger turbine rotor.
    Turbochargers have a turbine and a compressor. The turbine of a turbocharger is used to expand a first medium, in particular exhaust gas from an internal combustion engine. The compressor is used to compress a second medium, in particular charge air to be supplied by the internal combustion engine, the compressor using energy that is 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 rotor and a compressor housing.
    The turbine rotor of the turbine and the compressor rotor of the compressor 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.
    From DE 20 2012 009 739 U1 it is already known to design a turbine rotor of a turbocharger as an integrally cast component, in which thus the rotor blades of the turbine rotor are integrally formed on the main rotor body of the same. Such turbine rotors with blades integrally formed on the base body are also referred to as blisk (blade integrated disk).
    [0006] Such integrally bladed rotors have hitherto been known primarily from aircraft engine construction. In aircraft engines, critical operating points of an aircraft engine, that is to say operating points in the natural frequency range, are passed through as quickly as possible and the engine is operated specifically below or above such a critical operating point. The use of integrally bladed turbine rotors is therefore not critical in aircraft engines.
    In turbochargers, on the other hand, an integrally bladed turbine rotor must be designed for all load cases; in particular, continuous operation in a critical load range must also be taken into account, since the turbocharger is an assembly of an internal combustion engine and is operated depending on the operating point of the internal combustion engine. It is therefore necessary to design integrally bladed turbine rotors of turbochargers to be resonance-proof.
    In the turbocharger turbine rotor of DE 10 2012 009 739 U1, this is ensured in that the integrally bladed turbine rotor has an outer shroud, via which the rotor blades are connected to one another at a radially outer end. However, such an outer shroud is located in the flow area of the exhaust gas to be expanded and has a negative effect on the flow behavior. In particular, the efficiency of a turbocharger is impaired as a result. There is therefore a need for a turbine rotor for a turbocharger that is designed to be resistant to resonance even without a disruptive outer shroud, and that can therefore also be operated continuously in the critical operating point of the natural frequency range.
    Proceeding from this, the present invention is based on the object of creating a novel turbocharger turbine rotor and a turbocharger with such a turbocharger turbine rotor. This object is achieved by a turbocharger turbine rotor according to claim 1.
    The turbocharger turbine rotor according to the invention has a rotor base body and rotor blades which are formed integrally on the rotor base body, the rotor blades being configured without an outer shroud. The rotor blades merge with the rotor base body with the formation of a defined area of curvature with a defined, constant or variable radius of curvature rfin. For a first group of first rotor blades, the following relationship applies to the radius of curvature of the region of curvature of the first rotor blades: 2.5% ≤ rf1 * 100 / l ≤ 10%, where rf1 is the constant or variable radius of curvature of the region of curvature of the first rotor blades and I is the length of the first rotor blades is at a flow exit edge (6). On a second group of second rotor blades, the radius of curvature rf2 of the region of curvature of the second rotor blades deviates in a defined manner on the damping side from the radius of curvature rf1 of the region of curvature of the first rotor blades. The first group of first blades includes a plurality of first blades. The second group of second blades includes at least one second blade.
    In the inventive, integrally bladed turbocharger turbine rotor, an outer shroud is dispensed with. The rotor blades of the integrally bladed turbocharger turbine rotor according to the invention merge into the rotor base body with the formation of a defined region of curvature. On the or every second rotor blade, the constant or variable radius of curvature of the respective region of curvature deviates in a defined manner on the damping side from the constant or variable radius of curvature of the region of curvature of the first rotor blades. The deviation of the radius of curvature on the or every second rotor blade from the radius of curvature of the first rotor blades, which is defined on the damping side, sets a targeted frequency detuning between the individual rotor blades of the turbocharger turbine rotor. In this way, so-called vibration-side node diameters and vibration amplitudes can be manipulated in a targeted manner in order to set optimal damping of the turbocharger turbine rotor. From a structural dynamics point of view, optimal phase positions can be set on adjacent rotor blades.
    When the radius of curvature rf1 on the first rotor blades is constant, the following preferably applies to the radius of curvature rf2 of the curvature region of the respective second rotor blade: 120% rf2 / rf1 300%. In particular, if the radius of curvature rf1 on the first rotor blades is constant, the radius of curvature rf2 on the respective second rotor blade is also constant. This is preferred to ensure optimal damping properties of an integrally bladed turbocharger turbine rotor without an outer shroud.
    When the radius of curvature rf1 on the first rotor blades is variable, the following preferably applies to the radius of curvature rf2 of the curvature region of the respective second rotor blade: 130% rf2 / rf1 400%. In particular, if the radius of curvature rf1 on the first rotor blades is variable, the radius of curvature rf2 on the respective second rotor blade is also variable. This is preferred to ensure optimal damping properties of an integrally bladed turbocharger turbine rotor without an outer shroud.
    According to a further development of the invention, the number of second moving blades is between 15% and 60% of the total number of moving blades made up of first moving blades and second moving blades. This allows the damping behavior of the integrally bladed turbocharger turbine rotor without the outer shroud to be optimally adjusted.
    The turbocharger according to the invention is defined in claim 12.
    Preferred developments of the invention emerge from the subclaims 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 perspective view of a turbocharger turbine rotor according to the invention of an axial turbine; FIG. 2 shows the detail II of FIG. 1; 3 shows a perspective view of a turbocharger turbine rotor according to the invention of a radial turbine; FIG. 4 shows detail IV from FIG. 3; FIG. FIG. 5 shows a detail of FIG. 2 or 4.
    The invention relates to a turbocharger turbine rotor and a turbocharger with such a turbocharger turbine rotor.
    A turbocharger has a turbine and a compressor. The turbine is used to expand the pressure of a first medium, in particular the expansion of exhaust gas from an internal combustion engine, with energy being obtained when the first medium is expanded. The compressor of the turbocharger is used to compress a second medium, in particular the compression of charge air, using the energy obtained in the turbine.
    The turbine of the turbocharger has a turbine housing and a turbine rotor rotatably mounted in the turbine housing. The compressor of the turbocharger has a compressor housing and a compressor rotor rotatably mounted in the compressor housing. The turbine rotor and compressor rotor of the turbocharger are coupled via a shaft which is rotatably mounted in a bearing housing, the bearing housing being connected to both the turbine housing and the compressor housing.
    The invention relates to details of the turbine rotor of a turbocharger.
    1 shows a perspective view of a turbocharger turbine rotor 1, which has a rotor base body 2 and rotor blades 3 formed integrally on the rotor base body 2. FIG. 2 shows the detail II of FIG. 1. Because of the axial flow direction in the turbocharger turbine rotor, this design is referred to as a turbocharger axial turbine rotor. The direction of flow through the turbocharger axial turbine rotor is visualized in FIGS. 1, 2 by an arrow S.
    3 shows a perspective view of a turbocharger turbine rotor 1 which is acted upon from an inflow directed radially to the rotor axis. The turbocharger turbine rotor 1 of FIG. 3 also has a rotor base body 2 and rotor blades 3 formed integrally on the rotor base body 2. FIG. 4 shows detail IV of FIG. 3. The turbocharger turbine rotor of this design is referred to as a turbocharger radial turbine rotor. The direction of flow through the turbocharger radial turbine rotor is again visualized by an arrow S in FIGS.
    The rotor blades 3 of the respective turbocharger turbine rotor 1 merge on the inside with the formation of a defined curvature region 4 in the rotor base body 2, this curvature region 4 also being referred to as fillet. On the outside, the rotor blades 3 are designed without a shroud.
    The areas of curvature 4 of the rotor blades, with which the rotor blades 3 merge into the rotor base body 2, are characterized by a radius of curvature rf. See FIG. 5. This radius of curvature rf can be a constant radius of curvature rf or also a variable radius of curvature rf.
    The rotor blades 3 have a defined length I in the radial direction at a flow outlet edge 6, with all the rotor blades 3 preferably having the identical length I in the radial direction at the flow outlet edge 6.
    The rotor blades 3 form a first group of first rotor blades and a second group of second rotor blades 3. The first group of first rotor blades comprises a plurality of rotor blades 3 and the second group of second rotor blades comprises at least one rotor blade 3.
    The following relationship (1) applies to the first group of first rotor blades 3 for the radius of curvature rf of the region of curvature 4 of the first rotor blades 3, which is referred to as rf1: where rf1 is the constant or variable radius of curvature of the region of curvature of the first rotor blades, I is the length of the first rotor blades is at a flow trailing edge 6.
    On the second group of second rotor blades 3, the radius of curvature rf of the region of curvature 4 of the second rotor blades 3, which is referred to as rf2, deviates from the radius of curvature rf1 of the region of curvature 4 of the first rotor blades 3 on the damping side, namely in a damping-optimized manner, in order to provide a targeted frequency detuning between the To provide rotor blades 3 of the turbocharger turbine rotor 1 with optimal vibration damping properties of the turbocharger turbine rotor 1, so that the same can be operated continuously at all operating points. The radius of curvature rf2 of the curvature region 4 of the respective second rotor blade 3 deviates from the radius of curvature rf1 of the curvature region 4 of the first rotor blades 3 in such a way that the radius of curvature rf2 of the curvature region 4 of the respective second rotor blades 3 does not have the above relationship (1) for the radius of curvature 4 of the first curvature region rf1 of the first rotor blades 3 3 fulfilled.
    The number of second rotor blades of the second group is between 15% and 60% of the total number of first and second rotor blades 3 of the first and second group.
    Each blade 3 has a flow inlet edge 5, the flow outlet edge 6, as well as between the flow inlet edge 5 and the flow outlet edge 6 extending flow-guiding sides or surfaces 7, 8, one of these flow-guiding surfaces as the suction side and the other of these flow-guiding surfaces is designed as a pressure side. The flow inlet edge 5, the flow outlet edge 6 and these flow-guiding surfaces 7, 8 extend into the curvature region 4 of the respective rotor blade 3.
    A radius of curvature rf is formed at each position of the area of curvature 4, i.e. in the area of the flow inlet edge 5, in the area of the flow outlet edge 6 and in the areas of the flow-guiding surfaces 7, 8 extending between the flow inlet edge 5 and the flow outlet edge 6.
    In the case of a rotor blade with a constant radius of curvature, the radius of curvature is the same at every position of the region of curvature 4, i.e. in the region of the flow inlet edge 5, in the region of the flow outlet edge 6 and in regions of the sides 7 and 8 extending between the flow inlet edge and the flow outlet edge . In this case, a constant radius of curvature then extends around the entire region of curvature 4. This type of radius of curvature is referred to as the constant radius of curvature of the respective rotor blade.
    In a rotor blade with a variable radius of curvature, the radius of curvature is different in the area of a flow inlet edge 5 and / or in the area of the flow outlet edge 6 and / or in the areas of the sides 7 and 8 extending between the flow inlet edge and the flow outlet edge. In this case, the radius of curvature changes starting from the respective flow inlet edge 5 in the direction of the respective flow outlet edge 6. This type of radius of curvature is referred to as the variable radius of curvature of the respective rotor blade.
    Regardless of whether the first rotor blades 3 of the first group have a constant or variable radius of curvature in the respective curvature region 4, the relationship (1) applies to the radius of curvature of the first rotor blades 3 at every position of the curvature region, that is:
    When the radius of curvature rf1 on the first rotor blades 3 in the region of curvature 4 is constant, the following relationship (2) preferably applies to the radius of curvature rf2 of the region of curvature 4 of the respective second rotor blade 3:
    If the radius of curvature rf1 on the first rotor blades is constant, the radius of curvature rf2 on the or every second rotor blade is preferably also constant.
    If the radius of curvature rf1 on the first rotor blades is variable, the following relationship (3) preferably applies to the radius of curvature rf2 of the curvature region 4 of the respective second rotor blade 3:
    If the radius of curvature rf1 on the first rotor blades is variable, the radius of curvature rf2 on the or every second rotor blade is preferably also variable.
    With the present invention, a turbocharger turbine rotor for a turbocharger can be provided, which is designed as an outer shroudless, integrally bladed turbine rotor and has a resonance-resistant blading, so that the turbine, namely the turbocharger turbine rotor, safely with optimal in all operating points Damping properties can be operated.
    A turbocharger according to the invention has a turbine for expanding a first medium and with a compressor for compressing a second medium using energy obtained in the turbine when the first medium is expanded. The turbine has a turbine housing and a turbine rotor through which there is a flow. The compressor has a compressor housing and a compressor rotor which is coupled to the turbine rotor via a shaft. The turbine housing and the compressor housing are each connected to a bearing housing arranged between the same and in which the shaft is supported. The turbine rotor is designed according to the invention as described above. The turbine rotor can be an axial turbine rotor or a radial turbine rotor.
    List of reference symbols
    1 turbine rotor 2 rotor base 3 rotor blade 4 curvature region 5 flow inlet edge 6 flow outlet edge 7 surface 8 surface
    权利要求:
    Claims (14)
    [1]
    1. Turbocharger turbine rotor (1),with a rotor base body (2),with rotor blades (3) formed integrally on the rotor base body (2), the rotor blades (3) being formed without an outer shroud,the rotor blades (3) passing over the rotor base body (2) with the formation of a defined region of curvature (4) with a defined, constant or variable radius of curvature rfin,the following relationship applies to a first group of first rotor blades (3) for the radius of curvature of the region of curvature (4) of the first rotor blades (3):2.5% ≤ rf1 * 100 / l ≤ 10%,where rf1 is the constant or variable radius of curvature of the region of curvature of the first rotor blades and I is the length of the first rotor blades at a flow trailing edge (6),wherein on a second group of second rotor blades (3) the radius of curvature rf2 of the region of curvature (4) of the second rotor blades (3) deviates in a defined manner on the damping side from the radius of curvature rf1 of the region of curvature (4) of the first rotor blades (3).
    [2]
    2. Turbocharger turbine rotor according to claim 1, characterized in that the radius of curvature rf2 of the region of curvature (4) of the respective second rotor blade (3) deviates from the radius of curvature rf1 of the region of curvature (4) of the first rotor blades (3) in such a way that the radius of curvature rf2 of the region of curvature (4 ) of the respective second rotor blades (3) does not satisfy the relationship for the radius of curvature rf1 of the curvature region (4) of the first rotor blades (3).
    [3]
    3. Turbocharger turbine rotor according to claim 1 or 2, characterized in that on the respective second rotor blade (3) the radius of curvature rf2 of the curvature region (4) of the second rotor blades (3) from the radius of curvature rf1 of the curvature region (4) of the first rotor blades (3) optimizes the damping deviates.
    [4]
    4. Turbocharger turbine rotor according to one of claims 1 to 3, characterized in that when the radius of curvature rf1 on the first rotor blades is constant, the following applies to the radius of curvature rf2 of the respective second rotor blade (3): 120% ≤ rf2 * 100 / rf1 ≤ 300%.
    [5]
    5. Turbocharger turbine rotor according to claim 4, characterized in that when the radius of curvature rf1an the first rotor blades is constant, the radius of curvature rf2an the respective second rotor blade is constant.
    [6]
    6. Turbocharger turbine rotor according to claim 4 or 5, characterized in that in the case of a rotor blade with a constant radius of curvature at each position of the curvature region (4), that is in the region of a flow inlet edge (5), in the region of the flow outlet edge (6) and in regions of sides (7, 8) extending between the flow inlet edge and the flow outlet edge, the radius of curvature is the same.
    [7]
    7. Turbocharger turbine rotor according to one of claims 1 to 3, characterized in that when the radius of curvature rf1 on the first rotor blades is variable, the following applies to the radius of curvature rf2 of the respective second rotor blade (3): 130% ≤ rf2 * 100 / rf1 ≤ 400%.
    [8]
    8. Turbocharger turbine rotor according to claim 7, characterized in that when the radius of curvature rf1 on the first rotor blades is variable, the radius of curvature rf2 on the respective second rotor blade is also variable.
    [9]
    9. Turbocharger turbine rotor according to claim 7 or 8, characterized in that in the case of a rotor blade with a variable radius of curvature in the area of a flow inlet edge (5) and / or in the area of the flow outlet edge (6) and / or in areas between the flow inlet edge and the Flow outlet edge extending sides (7, 8) the radius of curvature is different.
    [10]
    10. Turbocharger turbine rotor according to one of claims 1 to 9, characterized in that the first group of first rotor blades comprises a plurality of rotor blades and the second group of second rotor blades comprises at least one rotor blade.
    [11]
    11. Turbocharger turbine rotor according to one of claims 1 to 10, characterized in that the number of second rotor blades is between 15% and 60% of the total number of rotor blades.
    [12]
    12. 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 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 and the compressor housing are each connected to a bearing housing arranged between the same and in which the shaft is mounted, characterized in thatthe turbine rotor (1) is designed according to one of claims 1 to 11.
    [13]
    13. Turbocharger according to claim 12, characterized in that the turbine rotor is an axial turbine rotor.
    [14]
    14. Turbocharger according to claim 12, characterized in that the turbine rotor is a radial turbine rotor.
    类似技术:
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    同族专利:
    公开号 | 公开日
    RU2020120979A|2021-12-27|
    KR20210001951A|2021-01-06|
    CN112145238A|2020-12-29|
    US20200408143A1|2020-12-31|
    DE102019117298A1|2020-12-31|
    JP2021006713A|2021-01-21|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    JP4946901B2|2008-02-07|2012-06-06|トヨタ自動車株式会社|Impeller structure|
    EP2184442A1|2008-11-11|2010-05-12|ALSTOM Technology Ltd|Airfoil fillet|
    US9988909B2|2011-04-25|2018-06-05|Honeywell International, Inc.|Hub features for turbocharger wheel|
    DE112013001568T5|2012-04-23|2014-12-04|Borgwarner Inc.|Turbine hub with surface discontinuity and turbocharger with it|
    DE202012009739U1|2012-10-12|2012-11-05|Abb Turbo Systems Ag|Integrally cast turbine wheel|
    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    DE102019117298.5A|DE102019117298A1|2019-06-27|2019-06-27|Turbocharger turbine rotor and turbocharger|
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