• 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:
    Radial compressor (10), with a compressor rotor (11) having rotor blades (12); with a compressor housing (13) which receives a diffuser (14) having guide vanes (15); wherein the diffuser (14) delimits, at least in sections, a flow channel leading away from the rotor blades (12) of the compressor rotor (11) in the radial direction; the guide vanes (15) of the diffuser (14) having a flow inlet edge (16), a flow outlet edge (17) and flow-guiding sides (18, 19) extending between the flow inlet edge (16) and the flow outlet edge (17); the guide vanes (15) of the diffuser (14) engaging a support body (20) of the diffuser and protruding into the flow channel delimited at least in sections by the diffuser (14); wherein the guide vanes (15) of the diffuser (14) merge into the support body (20) of the diffuser (14) with the formation of a curvature region (21) defined on the flow side; and wherein at each position of the curved area (21), i.e. in the area of the flow inlet edge (16), in the area of the flow outlet edge (17) and in the area of the flow-guiding sides (18) extending between the flow inlet edge (16) and the flow outlet edge (17) , 19), in each case a radius of curvature (R) defined on the flow side is formed. Fig. 1
    公开号:CH713406B1
    申请号:CH01443/17
    申请日:2017-11-27
    公开日:2021-05-31
    发明作者:Benetschik Hannes；Eduard Wilkosz Benjamin；Heinz Christoph；Lesser Andreas
    申请人:Man Energy Solutions Se；
    IPC主号:
    专利说明:

    The invention relates to a radial compressor and a turbocharger.
    Turbochargers have a compressor and a turbine. A first medium, in particular exhaust gas from an internal combustion engine, is expanded in the turbine of a turbocharger, with the energy obtained in the compressor of the turbocharger being used to compress a second medium, in particular charge air for the internal combustion engine. The present invention relates to a radial compressor of a turbocharger and a turbocharger with a radial compressor.
    A radial compressor of a turbocharger has a compressor housing and a compressor rotor. The compressor rotor of the centrifugal compressor is axially flown against and radially discharged, the compressor rotor carrying rotor blades. The compressor housing typically accommodates an insert and a diffuser, the insert at least partially delimiting a flow channel leading to the rotor blades of the rotor and the diffuser delimiting a flow channel of the radial compressor leading away from the rotor blades.
    A radial compressor with a diffuser is known from EP 1 340 920 B1, the diffuser of the radial compressor disclosed there having guide vanes. The guide vanes of the diffuser engage a support body of the diffuser that is designed as a plate.
    Proceeding from this, the present invention is based on the object of creating a new type of centrifugal compressor which has an extended pumping stability limit, and a turbocharger with such a centrifugal compressor. This object is achieved by a radial compressor according to claim 1. According to the invention, the guide vanes of the diffuser merge into the support body of the diffuser with the formation of a curvature area defined on the flow side, a flow-side defined at each position of the curvature area, i.e. in the area of the flow inlet edge, in the area of the flow outlet edge and in areas between the flow inlet edge and the flow outlet edge Radius of curvature is formed. This allows the pump stability limit of the centrifugal compressor to be extended.
    According to a first advantageous development, a constant radius of curvature is formed at each position of the region of curvature. A ratio of the respective radius of curvature to the radial diameter of the compressor rotor is preferably greater than or equal to 0.015, preferably greater than or equal to 0.02, particularly preferably greater than or equal to 0.025. A ratio of the respective minimum radius of curvature to the axial height of the respective guide vane of the diffuser is preferably less than or equal to 1. This advantageously allows the pumping stability limit of the radial compressor to be extended.
    According to a second alternative advantageous development, a variable radius of curvature, which varies between a minimum radius of curvature and a maximum radius of curvature, is formed at each position of the region of curvature. A ratio of the respective maximum radius of curvature to the radial diameter of the compressor rotor is preferably greater than or equal to 0.015, preferably greater than or equal to 0.02, particularly preferably greater than or equal to 0.025. A ratio of the respective minimum radius of curvature to the axial height of the respective guide vane of the diffuser is preferably less than or equal to 1. This can also advantageously extend the pumping stability limit of the radial compressor.
    The turbocharger according to the invention is defined in claim 13.
    Preferred developments of the invention emerge 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. 1 shows an axial section through a radial compressor according to the invention; Fig. 2 shows a detail of Fig. 1; Fig. 3 shows an alternative detail of Fig. 1; and FIG. 4 shows an axial section through a further radial compressor according to the invention.
    The invention relates to a radial compressor and a turbocharger with a radial compressor. The person skilled in the art addressed here is familiar with the basic structure of a turbocharger. It should be noted at this point that a turbocharger has a compressor and a turbine. A first medium, in particular exhaust gas, is expanded in the turbine of the turbocharger. The energy gained during the expansion of the first medium is used in the compressor to compress a second medium, in particular charge air.
    1 shows a schematic cross section through a first radial compressor 10, the radial compressor 10 having a compressor rotor 11 with rotor blades 12 and a compressor housing 13. The compressor housing 13 accommodates a diffuser 14 with guide vanes 15, the diffuser 14, downstream of the compressor rotor 11, delimiting a flow channel extending in the radial direction and extending or leading away from the rotor blades 12 of the compressor rotor 11 in sections.
    A medium to be compressed in the radial compressor flows into the compressor rotor 11 in the axial direction and flows away from the same in the radial direction, namely via the diffuser 14 with the guide vanes 15.
    Each guide vane 15 of the diffuser 14 has a flow inlet edge 16, a flow outlet edge 17 and flow-guiding sides 18, 19 extending between the flow inlet edge 16 and the flow outlet edge 17.
    The guide vanes 15 of the diffuser 14 engage a plate-like support body 20 of the diffuser 14, the diffuser 14 being fastened to the compressor housing 13 via the support body 20. Starting from the support body 20, the guide vanes 15 of the diffuser 15 extend into the flow channel of the radial compressor 10, which extends in the radial direction, downstream of the compressor rotor 11.
    For the purposes of the present invention, the guide vanes 15 of the diffuser 14 merge into the support body 20 of the diffuser 14 with the formation of a curvature region 21 defined on the flow side.
    This curvature region 21 defined on the flow side runs around the respective guide vane 15 of the diffuser 14 in the transition region to the support body 20 of the diffuser 14, so that accordingly this curvature region 21 both in the region of the flow inlet edge 16 of the respective guide vane 15 and in the region of the flow outlet edge 17 of the respective guide vane 15 and in the area of the flow-guiding sides 18 and 19 of the respective guide vane 15 running between the flow inlet edge 16 and the flow outlet edge 17.
    A defined radius of curvature R is formed at each position of the area of curvature 21, i.e. in the area of the flow inlet edge 16, in the area of the flow outlet edge 17 and in the area of the flow-guiding sides 18, 19 extending between the flow inlet edge 16 and the flow outlet edge 17. In the exemplary embodiment in FIG. 1, this radius of curvature R is constant at every position of the region of curvature 21; furthermore, in the exemplary embodiment of FIG.
    It is particularly provided that a ratio R / D of the radius of curvature R to the radial diameter D of the compressor rotor 11 is greater than or equal to 0.015, preferably greater than or equal to 0.02, particularly preferably greater than or equal to 0.25.
    A ratio R / H between the respective radius of curvature R and the axial height H of the respective guide vane 15 of the diffuser 14 is less than or equal to 1.
    The inventive centrifugal compressor 10 with the flow-side defined curvature region 21 between the guide vanes 15 of the diffuser 14 and the support body 20 of the same ensures an extended pumping stability limit of the centrifugal compressor, especially in the full load range. In this way, an increase in the usable map width can be achieved. In this way, an expanded engine operating range can be covered and / or an increase in the boost pressure can be achieved.
    Furthermore, the expansion of the pumping stability limit enables a more robust functionality of the radial compressor in the event of a transient load change, for example in the event of an acceleration of the turbocharger.
    Fig. 2 shows a detail from the radial compressor 10 of Fig. 1 in the area of a guide vane 15 of the diffuser 14, namely in the transition area or curvature area 21 between the guide vane 15 of the diffuser 14 and the support body 20 of the diffuser 14. As already 1, 2 at each position of the curvature area 21, i.e. in the area of the flow inlet edge 16, in the area of the flow outlet edge 17, and in the area of the flow-guiding sides 18, 19 running between the flow inlet edge 16 and the flow outlet edge 17 the same defined, constant radius of curvature R is formed.
    In contrast, Fig. 4 shows a schematic cross section through a centrifugal compressor 10, in which a flow-side defined, constant radius of curvature is formed at each position of the curvature region 21, but the constant radius of curvature formed at each position of the curvature region 21 starting from the flow inlet edge 16 in the direction of the flow outlet edge 17 changed, in particular reduced.
    Fig. 4 shows that in the area of the flow inlet edge 16 of the constant radius of curvature R2 and in the area of the flow outlet edge 17 the constant radius of curvature R1 is formed in the curvature area 21, starting from the flow inlet edge 16 in the direction of the flow outlet edge 17 in the area of A further constant radius of curvature is formed at each position on the flow-guiding sides 18, 19, which, starting from the radius R2 at the flow inlet edge 16, decreases in the direction of the radius R1 at the flow outlet edge 17.
    For each of these radii of curvature, that is to say also for the radii of curvature R2 and R1, the ratios R / D and R / H given above, which were described with reference to FIG. 1, apply.
    Then, when, as shown in Fig. 1, 2 and 4, a constant radius of curvature R, R1 and R2 is formed at each position of the curvature region 21, the guide vane 15 goes into the support body 20 of the diffuser 14 to form a Circle segment, especially a 1⁄4 circle segment.
    According to an alternative embodiment of a radial compressor 10 it is provided that at each position of the curvature region 21 defined on the flow side, a flow-side defined radius of curvature is formed, which varies or merges between a minimum radius of curvature RMIN and a maximum radius of curvature RMAX. This is shown in FIG. 3.
    So in the embodiment of Fig. 3, the radius of curvature R adjacent to the respective guide vane 15 is smaller than adjacent to the support body 20. In this case, the curvature region 21 between a guide vane 15 and the support body 20 is not formed in the sense of a segment of a circle, but rather in the sense of an ellipse segment or the like. In the variant of FIG. 3, a ratio RMAX / D of the respective maximum radius of curvature RMAX to the radial diameter D of the compressor rotor 11 is greater than or equal to 0.015, preferably greater than or equal to 0.02, particularly preferably greater than or equal to 0.025. Furthermore, the ratio RMIN / H of the respective minimum radius of curvature RMIN to the axial height H of the respective guide vane 15 of the diffuser 14 is less than or equal to 1.
    It should be mentioned at this point that the invention also includes the reverse case, which is the minimum radius of curvature on the housing and the maximum radius of curvature on the blade.
    In the variant of FIG. 3 it can be provided that at each position of the curvature region 21, that is in the region of the flow inlet edge 16, the flow outlet edge 17 and the flow-guiding surfaces 18, 19 extending between the flow inlet edge 16 and the flow outlet edge 17, respectively the same variable radius of curvature is formed, so that the same minimum radius of curvature RMIN, the maximum radius of curvature RMAX and the same transition between the same are formed at each position of the curvature region 21.
    However, it is also possible that the maximum radius of curvature RMAX formed at each position of the curvature region 21 changes, in particular, decreases, starting from the flow inlet edge in the direction of the flow outlet edge 17. It is also possible that the minimum radius of curvature RMIN, starting from the flow inlet edge 16 in the direction of the flow outlet edge 17, also changes, in particular decreases.
    It is therefore within the meaning of the present invention to propose a radial compressor 10 for a turbocharger and a turbocharger with such a radial compressor 10, the diffuser guide vanes 15 with a flow-side defined curvature region 21 in a support body 20 of the diffuser 14, whereby the stability limit of the centrifugal compressor can be increased, especially in the full load range. As a result, the usable map width can be increased, as a result of which an expanded engine operating range and / or an increase in the boost pressure can be achieved. The expansion of the pumping stability limit also increases the robust functionality of the compressor in the event of a transient load change. In the event of damage to the compressor rotor 11, the support plate 20 of the diffuser 14 can function as a bursting ring and absorb forces and moments, thus increasing the containment security of the compressor 10. The area of curvature 21, via which the respective diffuser guide vane 14 merges into the carrier body 20 of the diffuser 14, is located on the same side of the flow channel extending in the radial direction as the carrier body 20 of the diffuser 14 . Separate compensation components for providing such a meridian adjustment can be dispensed with. This minimizes the number of components and reduces the tolerance chain.
    In this respect, the invention can be used both on diffuser blades that are integrated into the turbocharger housing and on variants designed as an insert.
    List of reference symbols
    10 radial compressor 11 compressor rotor 12 rotor blade 13 compressor housing 14 diffuser 15 guide vane 16 flow inlet edge 17 flow outlet edge 18 page 19 page 20 support body 21 curvature area D diameter H axial height R curvature radius R1 curvature radius R2 curvature radius RMINminimal curvature radius RMAXmaximal radius
    权利要求:
    Claims (13)
    [1]
    1. centrifugal compressor (10),with a compressor rotor (11) having rotor blades (12);with a compressor housing (13) which receives a diffuser (14) having guide vanes (15);wherein the diffuser (14) delimits, at least in sections, a flow channel leading away from the rotor blades (12) of the compressor rotor (11) in the radial direction;the guide vanes (15) of the diffuser (14) having a flow inlet edge (16), a flow outlet edge (17) and flow-guiding sides (18, 19) extending between the flow inlet edge (16) and the flow outlet edge (17);the guide vanes (15) of the diffuser (14) engaging a support body (20) of the diffuser and protruding into the flow channel delimited at least in sections by the diffuser (14);characterized in thatthe guide vanes (15) of the diffuser (14) merge into the support body (20) of the diffuser (14) with the formation of a curvature region (21) defined on the flow side;at every position of the area of curvature (21), i.e. in the area of the flow inlet edge (16), in the area of the flow outlet edge (17) and in the area of the flow-guiding sides (18, 19) extending between the flow inlet edge (16) and the flow outlet edge (17) ) a radius of curvature defined on the flow side is formed in each case.
    [2]
    2. Radial compressor according to claim 1, characterized in that a constant radius of curvature (R, R1, R2) is formed at each position of the region of curvature (21).
    [3]
    3. Radial compressor according to claim 2, characterized in that a ratio (R / D; R1 / D, R2 / D) of the respective radius of curvature (R, R1, R2) to the radial diameter (D) of the compressor rotor (12) is greater than or equal to 0.015 , preferably greater than or equal to 0.02, particularly preferably greater than or equal to 0.025.
    [4]
    4. Radial compressor according to claim 2 or 3, characterized in that the ratio (R / H, R1 / H, R2 / H) of the respective radius of curvature (R, R1, R2) to the axial height (H) of the respective guide vane (15) of the diffuser (14) is less than or equal to 1.
    [5]
    5. Radial compressor according to one of claims 2 to 4, characterized in that at each position of the area of curvature (21), i.e. in the area of the flow inlet edge (16), in the area of the flow outlet edge (17) and in the area between the flow inlet edge (16) and the flow-guiding sides (18, 19) running along the flow outlet edge (17) have the same defined, constant radius of curvature (R).
    [6]
    6. Radial compressor according to one of claims 2 to 4, characterized in that the defined, constant radius of curvature (R1, R2) formed at each position of the region of curvature (21) extends from the flow inlet edge (16) in the direction of the flow outlet edge (17) changed, especially decreased.
    [7]
    7. Radial compressor according to claim 1, characterized in that a variable radius of curvature is formed at each position of the region of curvature (21) which varies between a minimum radius of curvature (RMIN) and a maximum radius of curvature (RMAX).
    [8]
    8. Radial compressor according to claim 7, characterized in that a ratio (RMAX / D) of the respective maximum radius of curvature (RMAX) to the radial diameter (D) of the compressor rotor (12) is greater than or equal to 0.015, preferably greater than or equal to 0.02, particularly preferred is greater than or equal to 0.025.
    [9]
    9. Radial compressor according to claim 7 or 8, characterized in that a ratio (RMIN / H) of the respective minimum radius of curvature (RMIN) to the axial height (H) of the respective guide vane (15) of the diffuser (14) is less than or equal to 1.
    [10]
    10. Radial compressor according to one of claims 7 to 9, characterized in that at each position of the area of curvature (21), i.e. in the area of the flow inlet edge (16), in the area of the flow outlet edge (17) and in the area between the flow inlet edge (16, 17) and the flow-guiding sides (18, 19) running along the flow outlet edge have the same variable radius of curvature.
    [11]
    11. Radial compressor according to one of claims 7 to 9, characterized in that the maximum radius of curvature (RMAX) formed at each position of the curvature region (21) and / or the minimum radius of curvature (RMIN) formed at each position of the curvature region (21) starting from the flow inlet edge changed in the direction of the flow outlet edge, in particular reduced.
    [12]
    12. Radial compressor according to one of the preceding claims, characterized in that the guide vanes (15) of the diffuser (14) are designed to be integrated on or in the compressor housing (13).
    [13]
    13. Turbocharger,with a turbine for the expansion of a first medium,with a compressor designed as a radial compressor (10) for compressing a second medium using energy gained in the turbine when the first medium is expanded,wherein the turbine has a turbine housing and a turbine rotor,wherein the radial compressor (10) has a compressor housing (11) and a compressor rotor coupled to the turbine rotor via a shaft,characterized in thatthe radial compressor (10) is designed according to one of claims 1 to 12.
    类似技术:
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    同族专利:
    公开号 | 公开日
    KR20180088575A|2018-08-06|
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    CN108361226A|2018-08-03|
    JP2018119549A|2018-08-02|
    DE102017101590A1|2018-08-02|
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    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    DE102017101590.6A|DE102017101590A1|2017-01-27|2017-01-27|Centrifugal compressor and turbocharger|
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