• 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:
    Centrifugal compressor (10), with an impeller (11) on the rotor side; with a stator-side housing (13); with a feed flow channel (16) via which the medium to be compressed can be fed to the impeller (11) in the axial direction; with a diffuser (17) via which the compressed medium can be guided in the radial direction away from the impeller (11) and in the direction of a spiral housing section (15) of the housing (13); wherein the diffuser (17) has an increasing flow cross section radially on the outside in a transition region to the spiral housing section (15).
    公开号:CH714392B1
    申请号:CH01352/18
    申请日:2018-11-05
    公开日:2021-12-15
    发明作者:Lesser Andreas；Heinz Christoph；Benetschik Hannes
    申请人:Man Energy Solutions Se；
    IPC主号:
    专利说明:

    The invention relates to a radial compressor according to the preamble of claim 1. The invention also relates to a turbocharger with a radial compressor.
    A radial compressor of an exhaust gas turbocharger according to the preamble of claim 1 is known from EP 1 340 920 B1 and EP 2 194 277 A1. This prior art shows a centrifugal compressor with an impeller on the rotor side, with a housing on the stator side, with a feed flow duct, via which the medium to be compressed can be fed to the impeller in the axial direction, and with a diffuser, via which the compressed medium can flow away from the impeller in the radial direction and guidable toward a volute portion of the casing. According to EP 1 340 920 B1 and EP 2 194 277 A1, the diffusers are bladed diffusers that have guide vanes. Bladeless diffusers are also known.
    There is a need to improve the efficiency of a centrifugal compressor.
    Proceeding from this, the invention is based on the object of creating a novel centrifugal compressor.
    [0005] This object is achieved by a centrifugal compressor according to claim 1. According to the invention, the diffuser has an increasing flow cross section radially on the outside in a transition area to the spiral housing section.
    The inventive design of the diffuser in the transition area to the volute section improved filling of a so-called spiral braid beginning of the volute section can be achieved. As a result, the efficiency of the centrifugal compressor can ultimately be improved.
    According to an advantageous development, the diffuser is delimited by axially opposite walls extending in the radial direction, seen in the meridian section, namely by a first wall, which merges into a wall of the housing delimiting the feed flow channel radially on the outside, and by a second wall, where on the first wall, radially on the outside, in the transition area to the spiral housing section, a shoulder that increases the flow cross section of the diffuser is formed. In this way, the efficiency of the radial compressor can be increased particularly advantageously with a simple design.
    According to an advantageous further development, the shoulder is defined by a wall section which is inclined relative to the first wall, seen in the meridian section, which is inclined relative to the first wall of the housing, which extends in the radial direction, by an angle of a maximum of 45° and/or which is at the earliest at 80° % of the radial extent of the diffuser begins. This development also serves to increase the efficiency of the centrifugal compressor.
    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 limited thereto. 1 shows a schematic meridian section through a radial compressor according to the invention.
    Figure 1 shows a partial cross section through a preferred embodiment of a centrifugal compressor 10 according to the invention.
    A centrifugal compressor 10 has a rotor-side impeller 11 with a plurality of blades 12.
    Furthermore, a centrifugal compressor 10 has a stator-side housing 13. From the stator-side housing 13, seen in the flow direction of a medium to be compressed, an intake section 14 arranged upstream of the impeller 11 and a volute housing section 15 arranged downstream of the impeller 11 are shown. The intake section 14 defines at least in sections an inflow flow channel 16, via which medium to be compressed in the radial compressor 10 can be supplied to the impeller 11 of the radial compressor 10 for compression.
    In the area of the impeller 11, compressed medium can be supplied to the volute casing section 15 via a stator-side diffuser 17 of the centrifugal compressor 10, the diffuser 17 being designed as a bladed diffuser with guide vanes 18 in the exemplary embodiment of FIG. Seen in the meridian section of Fig. 1, the medium to be compressed flows in the axial direction A through the feed flow channel 16. The compressed medium flows in the radial direction R through the diffuser 17 in the direction of the spiral housing section 15. The spiral housing section 15 defines a spiral flow channel 23.
    The diffuser 17 has seen in meridian section in the radial direction R on the outside in a transition area to the spiral housing section 15 and thus in the transition area to the spiral flow channel 23 on an increasing flow cross section. This improves the filling of the so-called beginning of the spiral braid of the spiral flow channel 23 of the spiral housing 15, which ultimately increases the efficiency of the centrifugal compressor 10.
    The beginning of the spiral braid of the spiral flow channel 23 of the spiral housing 15 is that peripheral section of the spiral flow channel 23 in which the same has the smallest flow cross section in the meridian section.
    The diffuser 17 is delimited by opposite walls 19, 20, seen in a meridian section in the axial direction A, and extending in the radial direction R, namely by a first wall 19, which extends into a wall of the housing 13 delimiting the feed flow channel 16 radially on the outside, viz of the intake section 14, and of a second wall 20, which is adjoined by a bearing housing of the turbocharger.
    According to Fig. 1, a shoulder 21 that increases the flow cross section of the diffuser 17 is formed radially on the outside of the first wall 19 in the transition area to the spiral housing section 15 and thus in the transition area to the spiral flow channel 23 Wall section 22 is defined.
    The shoulder 21 and thus the enlarging flow cross-section of the diffuser 17 defining the wall portion 22 is inclined relative to the extending in the radial direction R first wall 19 by an angle α of at most 45 °.
    The angle α is preferably in a range between 45° and 10°, particularly preferably in an angular range between 45° and 20°.
    The wall section 22 defining the shoulder 21 begins at the earliest at 80% of the radial extent of the diffuser 17. In the case of a bladed diffuser 17 with guide vanes 18, the shoulder 21 begins downstream of the guide vanes 18 of the diffuser 17.
    The shoulder 21 of the diffuser 17 and thus the enlarged flow cross section of the diffuser 17 are provided in the transition area to the spiral housing 13 and thus in the transition area to the spiral flow channel 23 at least in the area of the beginning of the spiral braid.
    Preferably, the shoulder 21 of the diffuser 17 and thus the enlarged flow cross section of the diffuser 17 in the transition area to the spiral housing 13 and thus in the transition area to the spiral flow channel 23 runs around in the circumferential direction.
    The invention further relates to a turbocharger with such a centrifugal compressor 10. The centrifugal compressor 10 is used to compress a medium, such as charge air, using energy from the expansion of another medium, such as exhaust gas, in a turbine of the turbocharger is obtained. While the centrifugal compressor includes an impeller 11 and the housing 13, the turbine also includes an impeller and a housing, which are not shown in FIG. The impeller 11 of the centrifugal compressor 10 is coupled to the impeller of the turbine via a shaft which is mounted in a bearing housing of the turbocharger. The wall 20 of the diffuser 17 adjoins the bearing housing or is even provided by the bearing housing.
    With the invention, the efficiency of a radial compressor 10 and thus also the efficiency of a turbocharger having the radial compressor 10 can be increased.
    Reference List
    10 centrifugal compressor 11 impeller 12 blade 13 casing 14 suction section 15 volute section 16 feed flow passage 17 diffuser 18 vane 19 wall 20 wall 21 shoulder 22 wall section 23 spiral flow passage A axial direction R radial direction
    权利要求:
    Claims (10)
    [1]
    1. centrifugal compressor (10) for a turbocharger,with a rotor-side impeller (11);with a stator-side housing (13);with a feed flow channel (16) via which the medium to be compressed can be fed to the impeller (11) in the axial direction;with a diffuser (17) via which the compressed medium can be guided in the radial direction away from the impeller (11) and in the direction of a spiral housing section (15) of the housing (13);characterized in thatthe diffuser (17) has an increasing flow cross section radially on the outside in a transition area to the spiral housing section (15).
    [2]
    Centrifugal compressor according to claim 1, characterized in that the diffuser (17) is delimited by the walls (19, 20) which are axially opposite to one another and extend in the radial direction, namely by a first wall (19) which extends into a the feed flow channel (16) transitions radially outwardly defining wall of the housing (13), and of a second wall (20).
    [3]
    3. Centrifugal compressor according to claim 2, characterized in that a shoulder (21) increasing the flow cross-section of the diffuser (17) is formed radially on the outside on the first wall (19) in the transition area to the spiral housing section (15).
    [4]
    Centrifugal compressor according to Claim 3, characterized in that the shoulder (21) is defined by a wall portion (22) inclined relative to the first wall (19), as seen in meridian section.
    [5]
    Centrifugal compressor according to Claim 4, characterized in that the wall section (22) defining the shoulder (21) is inclined at an angle of at most 45° with respect to the first wall (19) extending in the radial direction.
    [6]
    Centrifugal compressor according to claim 4 or 5, characterized in that the wall portion (22) defining the shoulder (21) is inclined at an angle of between 45° and 10° with respect to the radially extending first wall (19).
    [7]
    Centrifugal compressor according to any one of Claims 4 to 6, characterized in that the wall portion (22) defining the shoulder (21) is inclined at an angle of between 45° and 20° with respect to the radially extending first wall (19).
    [8]
    Centrifugal compressor according to any one of Claims 4 to 7, characterized in that the wall section (22) defining the shoulder (21) is formed downstream of guide vanes (18) of the diffuser (17).
    [9]
    9. Centrifugal compressor according to one of claims 4 to 8, characterized in that the wall section (22) defining the shoulder (21) begins at 80% of the radial extension of the diffuser (17) at the earliest.
    [10]
    10. turbocharger,with a turbine for expanding a first medium;with a centrifugal compressor (10) according to one of Claims 1 to 9 for compressing a second medium using the energy obtained during the expansion of the first medium.
    类似技术:
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    EP3848590A1|2021-07-14|Discharge section of a compressor, compressor comprising such a discharge section and turbocharger comprising said compressor
    EP2781692A1|2014-09-24|Diffuser and fluid flow engine with the diffuser
    WO2022022780A1|2022-02-03|Guide vane arrangement for a turbomachine, compressor module, and turbomachine
    EP2068002A1|2009-06-10|Compressor casing
    同族专利:
    公开号 | 公开日
    KR20190060710A|2019-06-03|
    CN109931295A|2019-06-25|
    US10823178B2|2020-11-03|
    CH714392A2|2019-05-31|
    US20190162191A1|2019-05-30|
    DE102017127758A1|2019-05-29|
    JP2019094902A|2019-06-20|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    BE473291A|1946-05-10|
    US3997281A|1975-01-22|1976-12-14|Atkinson Robert P|Vaned diffuser and method|
    JP3153409B2|1994-03-18|2001-04-09|株式会社日立製作所|Manufacturing method of centrifugal compressor|
    US6168375B1|1998-10-01|2001-01-02|Alliedsignal Inc.|Spring-loaded vaned diffuser|
    JP2002005089A|2000-06-20|2002-01-09|Mitsubishi Heavy Ind Ltd|Turbo-compressor and refrigeration equipment provided with the same|
    US6669436B2|2002-02-28|2003-12-30|Dresser-Rand Company|Gas compression apparatus and method with noise attenuation|
    US6695579B2|2002-06-20|2004-02-24|The Boeing Company|Diffuser having a variable blade height|
    AU2002368156A1|2002-08-13|2004-02-25|Honeywell International, Inc.|Compressor|
    US20070196206A1|2006-02-17|2007-08-23|Honeywell International, Inc.|Pressure load compressor diffuser|
    US7918215B2|2006-05-08|2011-04-05|Honeywell International Inc.|Compressor stage assembly lock|
    JP2008075536A|2006-09-21|2008-04-03|Mitsubishi Heavy Ind Ltd|Centrifugal compressor|
    US8328535B2|2007-02-14|2012-12-11|Borgwarner Inc.|Diffuser restraint system and method|
    DE102007034236A1|2007-07-23|2009-02-05|Continental Automotive Gmbh|Centrifugal compressor with a diffuser for use with a turbocharger|
    EP2194277A1|2008-12-05|2010-06-09|ABB Turbo Systems AG|Compressor stabiliser|
    JP5535562B2|2009-09-16|2014-07-02|三菱重工業株式会社|Discharge scroll and turbo machine|
    DE102011005025A1|2011-03-03|2012-09-06|Siemens Aktiengesellschaft|Resonator silencer for a radial flow machine, in particular for a centrifugal compressor|
    EP2871369B1|2012-07-06|2019-01-09|Toyota Jidosha Kabushiki Kaisha|Compressor for supercharger of internal combustion engine|
    WO2014203379A1|2013-06-20|2014-12-24|三菱重工業株式会社|Centrifugal compressor|
    EP3032108B8|2013-08-06|2020-06-17|IHI Corporation|Centrifugal compressor and turbocharger|
    EP3060810B1|2013-10-21|2020-02-05|Williams International Co., L.L.C.|Turbomachine diffuser|
    US10066639B2|2015-03-09|2018-09-04|Caterpillar Inc.|Compressor assembly having a vaneless space|
    JP6785946B2|2017-03-28|2020-11-18|三菱重工エンジン＆ターボチャージャ株式会社|Centrifugal compressor and turbocharger|DE102015219556A1|2015-10-08|2017-04-13|Rolls-Royce Deutschland Ltd & Co Kg|Diffuser for radial compressor, centrifugal compressor and turbo machine with centrifugal compressor|
    US11098730B2|2019-04-12|2021-08-24|Rolls-Royce Corporation|Deswirler assembly for a centrifugal compressor|
    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    DE102017127758.7A|DE102017127758A1|2017-11-24|2017-11-24|Centrifugal compressor and turbocharger|
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