• 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 impeller (10), with a hub-like base body (11), the flow-guiding surface (13) of which has a contour that increases in the radial direction from a flow inlet end (14) in the direction of a flow outlet end (15); with rotor blades arranged on the hub-like base body (11), namely first rotor blades (12a) and second rotor blades (12b), the first rotor blades (12a) being longer than the second rotor blades (12b), wherein between each two adjacent first rotor blades ( 12a) a second rotor blade (12b) is arranged in each case. Characterized by third rotor blades (12c) which are shorter than the second rotor blades (12b), a third rotor blade (12c) being arranged between each adjacent first and second rotor blade (12a, 12b).
    公开号:CH716947A2
    申请号:CH01375/20
    申请日:2020-10-27
    公开日:2021-06-15
    发明作者:Klima Jiri；Behnke Klaus
    申请人:Man Energy Solutions Se；
    IPC主号:
    专利说明:

    The invention relates to a radial compressor impeller according to the preamble of claim 1.
    From DE 10 2012 207 727 B4 a radial compressor impeller with a hub-like base body and rotor blades arranged on the hub-like base body is known. The hub-like base body provides a flow-guiding surface of the compressor impeller which enlarges in the radial direction from a flow inlet end of the radial compressor impeller in the direction of a flow outlet end of the radial compressor impeller. First rotor blades and second rotor blades are arranged on the hub-like base body, the first rotor blades being longer than the second rotor blades when viewed in the axial direction and in the radial direction, and a second rotor blade being arranged between each two adjacent first rotor blades. The first rotor blades are also referred to as so-called main blades and the second rotor blades are also referred to as so-called splitter blades.
    During operation, the radial compressor impeller can heat up. There is a need to limit the heating of the centrifugal compressor impeller. There is also a need to improve the aerodynamic properties of the radial compressor impeller, that is to say the flow guidance properties of the same.
    Proceeding from this, the invention is based on the object of creating a novel radial compressor impeller. This object is achieved by a radial compressor impeller according to claim 1.
    The radial compressor impeller according to the invention has third rotor blades which are made shorter than the second rotor blades, a third rotor blade being arranged between each adjacent first and second rotor blades.
    With the third rotor blades, which are made shorter in the axial direction and in the radial direction than the second rotor blades, heat can be given off to the flow to be guided by the radial compressor impeller in the region of the flow outlet end of the radial compressor impeller. This can limit the heating of the radial compressor impeller during operation.
    [0007] Furthermore, the aerodynamic properties of the radial compressor impeller can be improved via the third rotor blades, in particular in partial load operation of the radial compressor impeller, with regard to improved flow guidance in the area of the flow outlet end.
    According to an advantageous development, flow inlet edges of the second rotor blades are arranged downstream of flow inlet edges of the first rotor blades, seen in the flow direction, flow inlet edges of the third rotor blades being arranged downstream of the flow inlet edges of the second rotor blades, as viewed in the flow direction.
    According to an advantageous development, the flow outlet end of the hub-like base body has an outlet radius, the flow inlet edges of the third rotor blade being arranged in a range between 60% and 85% of the outlet radius. Flow trailing edges of the third rotor blade are preferably arranged in a region between 90% and 100% of the exit radius.
    When the third rotor blades, based on the outlet radius of the radial compressor impeller, are positioned in the area defined above, heat from the radial compressor impeller can be given off particularly advantageously to the flow to be conducted in the area of the flow outlet end of the radial compressor impeller. A particularly advantageous flow guidance is then possible in the partial load range of the radial compressor impeller.
    According to an advantageous development, the radial compressor impeller consists of an aluminum alloy or a magnesium alloy. The invention is used particularly advantageously in radial compressor impellers which are formed from an aluminum alloy or magnesium alloy.
    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 front view of a radial compressor impeller according to the invention; 2 shows a perspective rear view of the radial compressor impeller according to the invention; 3 shows a front view of the radial compressor impeller according to the invention; 4 shows a side view of the radial compressor impeller according to the invention.
    1 to 4 show different views of a radial compressor impeller 10, the radial compressor impeller 10 having a hub-like base body 11 and a plurality of rotor blades 12 arranged on the hub-like base body 11.
    The hub-like base body 12 provides a flow-guiding surface 13 for the radial compressor impeller 10, which increases in size from a flow inlet end 14 in the direction of a flow outlet end 15 of the radial compressor impeller 10 in the radial direction R. The rotor blades 12 are formed on this flow-guiding surface 13 and extend away from this flow-guiding surface 13 in the radial direction R and in the axial direction A. These rotor blades 12 are curved in the circumferential direction and provide further flow-guiding surfaces of the radial compressor impeller 10.
    On the hub-like base body 11 different blades 12 are formed, namely first blades 12a, second blades 12b and third blades 12c.
    The first rotor blades 12a, viewed in the axial direction A and / or in the radial direction R, are longer than the second rotor blades 12b. A second rotor blade 12b is arranged between each two adjacent first rotor blades 12a.
    The third rotor blades 12c, viewed in the axial direction A and / or in the radial direction R, are designed to be shorter than the second rotor blades 12b. A third rotor blade 12c is arranged between each adjacent first and second rotor blades 12a, 12b.
    According to the invention, the radial compressor impeller 10 accordingly has three different types of rotor blades 12a, 12b and 12c. The first rotor blades 12a and the second rotor blades 12b are basically known from the prior art. In addition, the third rotor blades 12c are used which, viewed in the radial direction and in the axial direction, each have the shortest extension of the three different rotor blade types 12a, 12b and 12c.
    The third rotor blades 12c are arranged adjacent to the flow outlet end 15 of the radial compressor impeller 10.
    The third rotor blades 12c on the one hand take on a cooling function in order to give off heat from the radial compressor impeller 10 to the flow to be guided and compressed by the same in the region of the flow outlet end 15. On the other hand, the third rotor blades 12c assume a flow guiding function which is particularly advantageous in part load operation in order to provide improved flow guidance and therefore improved aerodynamic properties of the radial compressor impeller 10 in part load operation.
    Each of the rotor blades 12a, 12b and 12c has a flow inlet edge 16a, 16b, 16c and a flow outlet edge 17a, 17b, 17c.
    The flow inlet edges 16b of the second rotor blades 12b are arranged downstream of the flow inlet edges 16a of the first rotor blades 12a, viewed in the axial direction and in the flow direction. The flow inlet edges 16c of the third rotor blades 12c are arranged downstream of the flow inlet edges 16b of the second rotor blades 12b, viewed in the axial direction and in the flow direction.
    In the exemplary embodiment shown, all flow outlet edges 17a, 17b and 17c of all rotor blades 12a, 12b and 12c are arranged at the same position in the radial direction and in the flow direction. It is also possible for the flow outlet edges 17c of the third rotor blades 12c to be arranged upstream of the flow outlet edges 17a, 17b of the first and second rotor blades 12a, 12c, viewed in the radial direction and in the flow direction.
    The flow outlet end 15 of the hub-like base body 11 and thus of the radial compressor impeller 10 is characterized by an outlet radius. The flow inlet edges 16c of the third rotor blades 12c are arranged in a region between 60% and 85% of this outlet radius. The flow exit edges 17c of the third rotor blades 12c are arranged in a region between 90% and 100% of this exit radius.
    Accordingly, the third rotor blades 12c extend in a range between 60% and 100%, in particular in a range between 85% and 100% or in a range between 60% and 90% or also in a range between 85% and 90 % of this exit radius.
    As already stated, the third rotor blades 12c can optimally transfer heat from the radial compressor impeller 10 to the flow to be compressed.
    In particular, the radial compressor impeller 10 including the rotor blades 12a, 12b, 12c is made of an aluminum alloy or a magnesium alloy.
    List of reference symbols
    Radial compressor impeller 11 base body 12a rotor blade 12b rotor blade 12c rotor blade 13 surface 14 flow inlet end 15 flow outlet end 16a flow inlet edge 16b flow inlet edge 16c flow inlet edge 17a flow outlet edge 17b flow outlet edge 17c flow outlet edge
    权利要求:
    Claims (9)
    [1]
    1. centrifugal compressor impeller (10),with a hub-like base body (11), the flow-guiding surface (13) of which has a contour that increases in the radial direction from a flow inlet end (14) in the direction of a flow outlet end (15);with rotor blades arranged on the hub-like base body (11), namely first rotor blades (12a) and second rotor blades (12b),wherein the first rotor blades (12a) are made longer than the second rotor blades (12b),wherein a second rotor blade (12b) is arranged between each two adjacent first rotor blades (12a), characterized bythird rotor blades (12c) which are shorter than the second rotor blades (12b),a third rotor blade (12c) is arranged between each adjacent first and second rotor blades (12a, 12b).
    [2]
    2. Radial compressor impeller according to claim 1, characterized in that the third rotor blades (12c) are arranged adjacent to the flow outlet end (15).
    [3]
    3. Radial compressor impeller according to claim 1 or 2, characterized in thatFlow inlet edges (16b) of the second rotor blades (12b) are arranged downstream of flow inlet edges (16a) of the first rotor blades (12a) as seen in the axial direction and in the flow direction,Flow inlet edges (16c) of the third rotor blades (12c) are arranged downstream of the flow inlet edges (16b) of the second rotor blades (12b) as seen in the axial direction and in the flow direction.
    [4]
    4. Radial compressor impeller according to claim 3, characterized in thatthe flow outlet end (15) of the hub-like base body (11) has an outlet radius,the flow inlet edges (16c) of the third rotor blade (12c) are arranged in a region between 60% and 85% of the outlet radius.
    [5]
    5. Radial compressor impeller according to claim 4, characterized in thatFlow outlet edges (17c) of the third rotor blade (12c) are arranged in a region between 90% and 100% of the outlet radius.
    [6]
    6. Radial compressor impeller according to claim 5, characterized in that the flow outlet edges (17c) of the third rotor blades (12c) are arranged in the radial direction and in the flow direction at the same position as the flow outlet edges (17a, 17b) of the first and second rotor blades (12a, 12b) ).
    [7]
    7. Radial compressor impeller according to claim 5, characterized in that the flow outlet edges (17c) of the third rotor blades (12c) are arranged in the radial direction and in the flow direction upstream of the flow outlet edges (17a, 17b) of the first and second rotor blades (12a, 12b).
    [8]
    8. Radial compressor impeller according to one of claims 1 to 7, characterized in that the same consists of an aluminum alloy.
    [9]
    9. Radial compressor impeller according to one of claims 1 to 7, characterized in that it consists of a magnesium alloy.
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    同族专利:
    公开号 | 公开日
    JP2021088989A|2021-06-10|
    CN112901552A|2021-06-04|
    DE102019132861A1|2021-06-10|
    US20210164488A1|2021-06-03|
    KR20210070211A|2021-06-14|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    FR2230229A5|1973-05-16|1974-12-13|Onera |
    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    DE102019132861.6A|DE102019132861A1|2019-12-03|2019-12-03|Centrifugal compressor impeller|
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