• 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), in particular radial compressor of an exhaust gas turbocharger, with an impeller (11); with a fixed housing (13); with a main flow channel (14) defined by the housing (13) for supplying a medium to be compressed in the direction of the impeller (11); and a secondary flow chamber (15) arranged radially outside the main flow channel (14), which is delimited from the main flow channel (14) by a contour wall (16) and which communicates with the main flow channel via a secondary flow opening (18) in the region of the impeller (11) Main flow channel (14) is connected. Seen in the meridian section, the secondary flow opening (18), via which the secondary flow chamber (15) in the region of the impeller (11) is connected to the main flow channel (14), is tilted or inclined relative to a radial direction.
    公开号:CH714389A2
    申请号:CH01272/18
    申请日:2018-10-18
    公开日:2019-05-31
    发明作者:Benetschik Hannes；Heinz Christoph
    申请人:Man Energy Solutions Se；
    IPC主号:
    专利说明:

    Description: [0001] The invention relates to a radial compressor according to the preamble of claim 1.
    From EP 2 194 277 A1 a radial compressor of an exhaust gas turbocharger according to the preamble of claim 1 is known. Thus, EP 2 194 272 A1 shows a radial compressor with a rotating impeller and a fixed housing. The housing defines a main flow passage to guide medium to be compressed toward the impeller. Outside the main flow channel, a secondary flow chamber is arranged, which is delimited by a contour wall of the main flow channel. According to EP 2 194 277 A1, the secondary flow chamber extends from a suction region of the main flow channel to a secondary flow opening in the region of the impeller. In the region of the impeller, the secondary flow chamber is connected to the main flow channel via the secondary flow opening. Within the secondary flow chamber are struts connecting the contour wall defining the main flow channel from the secondary flow chamber to the housing. According to EP 2 194 272 A1, the secondary flow opening, via which the secondary flow chamber is connected to the main flow channel in the region of the impeller, extends in the radial direction in the meridian section.
    About such a secondary flow chamber, which is connected to the main flow channel, can already improve the map stability and thus the performance of a centrifugal compressor to some extent.
    With increasing throttling of the centrifugal compressor to be compacted in the compressor working fluid already in the inlet region of the impeller experiences a sufficient pressure build-up, so that the working medium via the secondary flow chamber opposite to the flow direction in the main flow channel recirculated, in this way in a recirculation mode the aerodynamic stability can be achieved at reduced flow rates of the compressor.
    If there are high demands on the throughput of the radial compressor, a pressure gradient arises in the inlet region of the impeller, which has the result that the working medium flows via the secondary flow chamber in a direction which replaces in the flow direction through the main flow channel, so that then the Secondary flow chamber is not flowed through in the recirculation mode, but in a bypass mode. This can then realize high flow rates of the centrifugal compressor.
    There is a need to further improve the map stability of a centrifugal compressor. In particular, there is a need to increase the stable working range in the direction of further reduced delivery rates as well as the absorption capacity of the centrifugal compressor.
    On this basis, it is an object of the invention to provide a novel radial compressor. This object is achieved by a radial compressor according to claim 1. According to the invention, viewed in the meridian section, the secondary flow opening, via which the secondary flow chamber is connected to the main flow channel in the region of the impeller, is inclined or inclined relative to a radial direction. With these measures, the stability of the working range of the centrifugal compressor can be further improved. In particular, the work area can be increased in terms of further reduced delivery rates and in terms of the swallowing capacity.
    According to an advantageous development closes in the meridian section, the secondary flow opening, via which the secondary flow chamber is connected in the region of the impeller with the main flow channel, with the radial direction an angle between 10 ° and 80 °, preferably an angle between 10 ° and 70 °, more preferably an angle between 20 ° and 70 °, most preferably an angle between 20 ° and 60 °, a. With these angular ranges in which the secondary flow opening, as seen in the meridian section, is inclined with respect to the radial direction, the stable working range of the centrifugal compressor can be extended particularly preferably, in particular to provide further reduced delivery rates and to expand the absorption capacity.
    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 schematic meridian section through a radial compressor according to the invention.
    Fig. 1 shows a fragmentary cross section through a preferred embodiment of an inventive radial compressor 10th
    A radial compressor 10 has a rotating impeller 11 with a plurality of blades 12. Further, a radial compressor 10 has a fixed housing 13. The housing 13 of the centrifugal compressor 10 defines a main flow channel 14 for medium to be compressed to the main flow channel 14 to To cause compacting medium in the direction of the impeller 11. Outside the main flow channel 14, the housing 13 defines a secondary flow chamber 15. A contour wall 16, which is also referred to as a ring land, delimits the main flow channel 14 from the secondary flow chamber 15.
    The secondary flow chamber 15 extends from a portion upstream of the impeller 11 into the region of the impeller 11. Thus, FIG. 1 shows that upstream of the impeller 11, a first secondary flow opening 17 is formed, via which the secondary flow chamber 15 is connected to the main flow channel 14 upstream of the impeller 11 in the flow direction of the medium to be compressed. A second secondary flow opening 18 is formed in the region of the impeller 11, via which the secondary flow chamber 15 is connected to the main flow passage 14 in the region of the impeller 11.
    Within the secondary flow chamber 15 struts 19 extend over the struts 19, the contour wall 16 is connected to the housing 13.
    The one secondary flow opening 18, via which the secondary flow chamber 15 is connected in the region of the impeller 11 with the main flow channel 14, according to the invention seen in the meridian section opposite to a radial direction R obliquely.
    As seen in the meridian section, the secondary flow opening 18, via which the secondary flow chamber 15 in the region of the impeller 11 is connected to the main flow channel 14, encloses an angle a with the radial direction R. This angle a is between 10 ° and 80 °, preferably between 10 ° and 70 °, more preferably between 20 ° and 70 °, most preferably between 20 ° and 60 °.
    In a particularly preferred embodiment of the invention, the angle a is 25 ° ± 15 °, preferably 25 ° ± 10 °, preferably 25 ° ± 5 °.
    By the inventive design of the secondary flow port 18 through which the secondary flow chamber 15 is connected in the region of the impeller with the main flow channel 15, the following advantages can be achieved.
    When approaching the surge line of the centrifugal compressor, a recirculation of the medium to be compressed in the radial compressor in the region of the secondary flow chamber 15 is favored. In Fig. 1, an arrow I visualizes the recirculation of the working fluid through the secondary flow chamber 15, starting from the secondary flow port 18 in the region of the impeller 11 in the direction of the secondary flow port 17 upstream of the impeller 11 opposite to the flow direction of the main flow shown in Fig. 1st visualized by the arrow III.
    When approaching the intake limit or blocking limit of the centrifugal compressor, a bypass flow is promoted by the secondary flow chamber 15, wherein such a bypass flow is visualized in Fig. 1 by the arrow II. This bypass flow II is used to provide high flow rates in the area of the limit and / or absorption limit and is directed from the secondary flow opening 17 upstream of the impeller 11 in the direction of the secondary flow opening 18 in the region of the impeller 11. This bypass flow II can be fed to the main flow with almost no throttling effects. Accordingly, not only the surge limit, but also the swallow limit or blocking limit can be extended.
    As a result, ultimately, the working range of the centrifugal compressor can be considerably expanded. In a turbocharger which uses the radial compressor according to the invention, the efficiency can be increased. Furthermore, a faster load response response can be realized.
    Transition contours of the secondary flow opening 18 in the region of the impeller 11 to the housing 13 and the contour wall 16 may be executed sharp-edged or rounded.
    The secondary flow opening 18 is preferably designed as a peripheral circumferential slot.
    [0023] 10 Radial Compressor 11 impeller 12 blade 13 housing 14 main flow channel 15 secondary flow chamber 16 contour wall 17 secondary flow port 18 secondary flow port 19 strut
    权利要求:
    Claims (6)
    [1]
    1. Radial compressor (10), in particular radial compressor of an exhaust gas turbocharger, with a rotating impeller (11); with a fixed housing (13); with a main flow channel (14) defined by the housing (13) for supplying a medium to be compressed in the direction of the impeller (11); with a secondary flow chamber (15) arranged radially outside the main flow channel (14), which is delimited by a contour wall (16) from the main flow channel (14) and which communicates with the main flow channel via a secondary flow opening (18) in the region of the impeller (11) with the main flow channel (14) is connected; characterized in that seen in the meridian section, the secondary flow opening (18), via which the secondary flow chamber (15) in the region of the impeller (11) is connected to the main flow channel (14) is inclined or inclined with respect to a radial direction.
    [2]
    2. Radial compressor according to claim 1, characterized in that seen in the meridian section, the secondary flow opening (18) through which the secondary flow chamber (15) in the region of the impeller (11) is connected to the main flow channel (14), with the radial direction an angle between 10th ° and 80 ° includes.
    [3]
    3. Radial compressor according to claim 2, characterized in that seen in the meridian section, the secondary flow opening (18) with the radial direction forms an angle between 10 ° and 70 °.
    [4]
    4. Radial compressor according to claim 3, characterized in that seen in the meridian section, the secondary flow opening (18) with the radial direction forms an angle between 20 ° and 70 °.
    [5]
    5. Radial compressor according to claim 4, characterized in that seen in the meridian section, the secondary flow opening (18) with the radial direction forms an angle between 20 ° and 60 °.
    [6]
    6. Radial compressor according to one of claims 1 to 5, characterized in that the secondary flow chamber (15) with the main flow channel (14) seen in the flow direction of the medium to be compressed upstream of the impeller (11) via a further secondary flow opening (17) with the main flow channel ( 14) is connected.
    类似技术:
    公开号 | 公开日 | 专利标题
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    WO2005106207A1|2005-11-10|Compressor blade and compressor
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    CH714432A2|2019-06-14|Radial compressor.
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    WO2019063384A1|2019-04-04|Diffuser for a compressor
    DE102009024568A1|2010-12-09|compressor impeller
    DE112016003653T5|2018-05-17|Bearing structure and turbocharger
    DE102015111462B3|2016-09-22|Compressor with return flow channel and adjustable pilot vanes
    DE102009043230A1|2011-05-26|Radial compressor diffuser
    DE112017003318T5|2019-03-21|centrifugal compressors
    DE3344309A1|1984-06-14|ROTATIONAL COMPRESSOR
    DE202018101699U1|2019-07-02|Turbine with adjusting ring
    DE102017118950A1|2019-02-21|Diffuser for a centrifugal compressor
    EP3109407A1|2016-12-28|Stator device for a turbo engine with a housing device and multiple guide vanes
    DE102012203801A1|2013-09-12|Centrifugal compressor for combustion engine, has projection portion provided along axial extension of recess portion, so that inner diameter reduction of wheel receiving space is realized based on inner diameter of receiving space
    DE102021204349A1|2021-12-02|Centrifugal compressor and centrifugal compressor scroll casing
    EP0280850B1|1990-12-27|Radial-type centrifugal machine with a disc diffusor
    同族专利:
    公开号 | 公开日
    US20190154041A1|2019-05-23|
    CN109812453A|2019-05-28|
    DE102017127421A1|2019-05-23|
    KR20190058324A|2019-05-29|
    CH714389B1|2021-12-15|
    JP2019094897A|2019-06-20|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US6231301B1|1998-12-10|2001-05-15|United Technologies Corporation|Casing treatment for a fluid compressor|
    IT1392215B1|2008-12-03|2012-02-22|Idromeccanica Bertolini S P A|HEAD FOR PUMPS AND PROCEDURE FOR THE IMPLEMENTATION OF THAT HEAD|
    EP2194277A1|2008-12-05|2010-06-09|ABB Turbo Systems AG|Compressor stabiliser|
    JP5479021B2|2009-10-16|2014-04-23|三菱重工業株式会社|Exhaust turbocharger compressor|
    DE102011108195A1|2011-07-20|2013-01-24|Ihi Charging Systems International Gmbh|Turbine for an exhaust gas turbocharger|
    US10233834B2|2013-07-24|2019-03-19|Borgwarner Inc.|Turbocharger combining axial flow turbine with a compressor stage utilizing active casing treatment|
    DE112014005032T5|2013-12-06|2016-08-11|Borgwarner Inc.|Compressor air return with reduced noise|
    US20150198163A1|2014-01-15|2015-07-16|Honeywell International Inc.|Turbocharger With Twin Parallel Compressor Impellers And Having Center Housing Features For Conditioning Flow In The Rear Impeller|
    JP6497183B2|2014-07-16|2019-04-10|トヨタ自動車株式会社|Centrifugal compressor|
    WO2016151689A1|2015-03-20|2016-09-29|三菱重工業株式会社|Centrifugal compressor and supercharger comprising same|
    US9951793B2|2016-06-01|2018-04-24|Borgwarner Inc.|Ported shroud geometry to reduce blade-pass noise|
    US10316859B2|2017-05-12|2019-06-11|Borgwarner Inc.|Turbocharger having improved ported shroud compressor housing|
    US10935035B2|2017-10-26|2021-03-02|Hanwha Power Systems Co., Ltd|Closed impeller with self-recirculation casing treatment|DE102018211119A1|2018-07-05|2020-01-09|Audi Ag|Drive device with an exhaust gas turbocharger|
    JP2020139420A|2019-02-27|2020-09-03|三菱重工業株式会社|Centrifugal compressor and turbocharger|
    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    DE102017127421.9A|DE102017127421A1|2017-11-21|2017-11-21|centrifugal compressors|
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