• 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 (21), with a compressor rotor (22), with a compressor housing (23), which has a radially outer spiral housing section (24) and a radially inner insert section (25), with a main flow channel (26) for supplying a medium to be compressed in Direction towards the compressor rotor, with a circulation chamber (27) arranged radially outside of the main flow channel (26), which is delimited from the main flow channel (26) by a contoured wall (28) which is connected to the main flow channel (26) via circulation openings (29, 30). and which is connected to the insert section (25) via struts (31) extending in the circulation chamber (37), the main flow channel (26) being separated from the contour wall (28) and upstream from the contour wall (28) from an upstream section ( 32) of the liner portion (25), and with an upstream of the compressor housing (23) arranged suction member (34) which having a radially outer portion (34b) adjacent to the volute portion (24) and having a radially inner portion (34a) adjacent to the upstream portion (32) of the liner portion (25). Adjacent surfaces of the radially inner portion (34a) of the suction member (34) and the upstream portion (32) of the liner portion (25) lie on a cylindrical surface.
    公开号:CH714850B1
    申请号:CH00193/19
    申请日:2019-02-14
    公开日:2022-01-31
    发明作者:Strauss Matthias；Löwlein Oswald；Spengler Sebastian；Thaser Boris
    申请人:Man Energy Solutions Se；
    IPC主号:
    专利说明:

    The invention relates to a centrifugal compressor according to the preamble of claim 1.
    Fig. 1 shows the basic structure known from the prior art of a turbocharger 1. The turbocharger 1 has a turbine 2 for expanding a first medium, in particular for expanding exhaust gas from an internal combustion engine. Furthermore, a turbocharger 1 has a compressor 3 for compressing a second medium, in particular charge air, using energy obtained in the turbine 2 during the expansion of the first medium. The turbine 2 has a turbine housing 4 and a turbine rotor 5. The compressor 3 has a compressor housing 6 and a compressor rotor 7. The compressor rotor 7 is coupled to the turbine rotor 5 via a shaft 8, which is mounted in a bearing housing 9, the Bearing housing 9 is positioned between the turbine housing 4 and the compressor housing 6 and is connected to both the turbine housing 4 and the compressor housing 6 . 1 also shows a compressor-side silencer 10.
    shown compressor 3 of the turbocharger 1 is designed as a radial compressor. The compressor housing 6 of the radial compressor has a radially outer spiral housing section 11 and a radially inner insert section 12. A main flow channel 13 of the radial compressor 3, which is delimited radially on the outside by the compressor housing 6, is used to supply the medium to be compressed in the direction of the compressor rotor 7. Outside the main flow channel 13, namely radially outside, a circulation chamber 14 is formed.
    The circulation chamber 14 is delimited from the main flow channel 13 by a contoured wall 15 . The circulation chamber 14 is connected to the main flow channel 13 via circulation openings 16 , 17 . Contour wall 15 is connected to insert portion 12 via struts not shown in FIG. According to FIG. 1 , the main flow channel 13 is bounded upstream of the contour wall 15 by an upstream portion of the insert portion 12 .
    According to FIG. 1, the muffler 10 is positioned upstream of the compressor housing 6 and provides a suction element 18 on the outlet side. The suction element 18 adjoins the volute section 11 with a radially outer section 18a and the upstream section of the insert section 12 with a radially inner section 18b. In the centrifugal compressor shown in FIG. 1, a flange connection 20 is implemented between the radially outer section 18a of the intake element 18 and the volute housing section 11 using a clamp 19 .
    Then, if during operation of the centrifugal compressor 3, the compressor rotor 7 of the same should break, fragments of the compressor rotor 7 can hit the insert piece section 12 and move it in the direction of the suction element 18. In this case, forces are then exerted on the suction element 18 which can lead to the connection 20 between the compressor housing 6 and the suction element 18 failing.
    There is a need for a centrifugal compressor in which there is no risk of failure of a connection between the suction element and the compressor housing in the event of a compressor rotor failure.
    Proceeding from this, the invention is based on the object of creating a new type of radial compressor.
    [0009] This object is achieved by a centrifugal compressor according to claim 1. According to the present invention, abutting surfaces of the radially inner portion of the suction member and the upstream portion of the liner portion lie on a cylindrical surface. Should the compressor rotor of the compressor fail and should fragments of the compressor rotor hit the insert section, the upstream section of the insert section can move in a defined manner into the suction element, so that there is no risk of forces that act on the insert section in the event of damage, to a failure of the joint area between the volute section of the compressor casing and the suction member.
    According to an advantageous development, the respective surface of the radially inner section of the suction element faces radially inward and the adjoining surface of the upstream section of the insert piece section faces radially outward, with the upstream section of the insert piece section being radially inward in relation to the radially inner section of the suction element is positioned. This configuration is particularly preferred in order to enable a defined movement of the upstream section of the insert section into the suction element in the event of damage to the compressor rotor when fragments of the compressor rotor strike the insert section.
    According to an advantageous development, the struts, via which the contour wall is connected to the insert piece section, engage on a section of the insert piece section which is offset radially outwards compared to the upstream section of the insert piece section and is connected to the upstream section of the insert piece section via a is connected in the radial direction extending portion. A clearance is formed between this radially extending portion of the liner portion and the radially inner portion of the suction member. A defined displacement path of the upstream section of the insert piece section into the suction element is defined by the free space.
    According to an advantageous development, an undercut or a material recess is formed on the upstream portion of the insert portion, specifically at the axial position of the clearance. This undercut or material recess prevents the upstream section of the insert piece section from tilting in the intake element when the upstream section of the insert piece section moves into the intake element in the event of damage to the compressor rotor.
    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 perspective cross section through a turbocharger known from the prior art; 2: a schematic meridian section through a centrifugal compressor according to the invention.
    Fig. 2 shows a meridian section through a radial compressor 21 according to the invention, which is designed in particular as a radial compressor of an exhaust gas turbocharger.
    The centrifugal compressor 21 has a compressor rotor 22 which is arranged in a compressor housing 23 . The compressor housing 23 has a radially outer spiral housing section 24 and a radially inner insert section 25, which is formed by two segments 25a, 25b in the exemplary embodiment shown. The two segments 25a, 25b of the insert section 25, which are designed as separate assemblies in the exemplary embodiment shown, can also be designed in one piece.
    The centrifugal compressor 21 has a main flow channel 26 via which medium to be compressed can be guided in the direction of the compressor rotor 22 . A circulation chamber 27 is formed radially outside of the main flow channel 26 and is delimited from the main flow channel 26 by a contoured wall 28 . The circulation chamber 27 is connected to the main flow channel 26 via circulation openings 29 , 30 .
    Within the circulation chamber 27 there extend struts 31, via which the contoured wall 28 is connected to the insert section 25, specifically in Fig. 2 to the segment 25b of the insert section 25.
    The main flow channel 26 is therefore partially delimited by the contour wall 28 radially on the outside. Upstream of the contour wall 28 the main flow channel 26 is delimited by a downstream section 32 of the insert section 25 . Downstream of the contour wall 28 the main flow passage 26 is bounded by a downstream portion 33 of the liner portion 25 which is externally adjacent to the compressor rotor 22 .
    In Fig. 2, a suction element 34 is also shown, which is arranged upstream of the compressor housing 23. The suction element 34 has a radially inner section 34a and a radially outer section 34b. The radially outer section 34b of the intake element 34 adjoins the volute section 24 . The radially inner section 34a of the suction element 34 adjoins the upstream section 32 of the insert section 25, which is provided by the segment 25a of the insert section 25 in the exemplary embodiment shown.
    Between the flange-like, radially outer portion 34b of the intake element 34 and a flange 35 of the volute portion 24, a flange 36 is formed.
    In the centrifugal compressor 21 according to the invention, adjacent surfaces of the radially inner portion 34a of the suction element 34 and the upstream portion 32 of the insert portion 25 lie on a cylindrical surface. The respective surface of the radially inner section 34a of the intake element 34 lying on this cylinder surface faces radially inwards and the respective adjacent surface of the upstream section 32 of the insert piece section 25 lying on the cylinder surface faces radially outwards. The downstream portion 32 of the liner portion 25 is positioned radially inward relative to the radially inner portion 34 of the suction member 34 .
    Should the compressor rotor 22 break during operation and should fragments thereof strike the insert piece section 25, the insert piece section 25 can move in a defined manner with its upstream section 32 into the suction element 34, so that no forces are exerted on the suction element 34 that can lead to a failure of the flange connection 36.
    As already stated, the contour wall 28 is connected to the insert section 25 via the struts 31 which extend in the circulation space 27 . The struts 31 act on a section 37 of the insert section 25 which is offset radially outwards relative to the upstream section 32 of the insert section 25 and which is connected to the upstream section 32 via a section 38 extending in the radial direction. This radially outwardly offset section 37 of the insert section 25 is provided by the segment 25b of the insert section 25 in the exemplary embodiment in FIG. 2 . The section 38 extending in the radial direction, which connects the section 37 to the upstream section 32 of the insert section 25, is formed by the segment 25a of the insert section 25 in the exemplary embodiment shown. As already stated, the segments 25a, 25b, in contrast to FIG. 2, can also be made in one piece.
    Between this radially extending section 38 of the insert section 25, via which the upstream section 32 of the insert section 25 is connected to the section 37 of the insert section 25, which is offset radially outwards compared to the upstream section 32, and the radially inner section 34a of the A free space 39 is formed in the suction element 34, which forms a kind of deformation space and defines a possible axial retraction path of the upstream section 32 of the insert piece section 25 into the suction element 34. The clearance 39 provides axial freedom of movement for the upstream portion 32 of the liner portion 25 in the event of failure.
    In the embodiment shown, between the radially extending section 38 of the insert section 25, which connects the upstream section 32 of the insert section 25 with the radially outwardly offset section 37 thereof, and the radially inner section 34a of the suction element 34 in the upstream Section 32 of the insert section 25 introduced an undercut 40 or a material recess.
    The undercut 40 or material recess is on the axial position of the free space 39, which can also be referred to as the axial deformation space, arranged radially inward relative to the free space 39 and merges into it.
    The undercut 40 or material relief faces radially inwardly of the radially outward surface of the upstream portion 32 of the liner portion 25, which faces the radially inward surface of the radially inner portion 34a of the suction member 34. Should the insert section 25 move into the suction element 34 in the event of damage, this undercut 40 or material recess prevents the upstream section 32 of the insert section 25 from tilting in the suction element 34 .
    The undercut 40 is formed circumferentially on a radially outer surface of the upstream portion 32 of the insert portion 25. As shown in FIG.
    As already stated, in the exemplary embodiment shown, the insert piece section 25 is formed in several parts from the segments 25a, 25b. The same can also be made in one piece, in which case the segments 25a, 25b are made in one piece.
    In the exemplary embodiment of FIG. 2, the insert piece section 25 and the radially outer spiral housing section 24 of the compressor housing 23 are separated on the component side, and the same are therefore provided by separate components. It is possible for the insert section 25 to extend into the volute section 24 , in which case the volute section 24 is also formed in sections from the insert section 25 .
    With the invention it can be avoided that in the event of damage to the compressor rotor 22 and the resulting axial displacement of the insert section 25 in the direction of the suction element 34, failure of the flange connection 36 between the compressor housing 23, namely in the volute housing section 24 of the same, can be avoided. and the suction element 34 comes. In the event of damage, this flange connection 36 is not exposed to any direct load. The flange connection 36 can therefore be made slimmer and lighter in comparison to conventional centrifugal compressors.
    reference list
    1 turbocharger 2 turbine 3 compressor 4 turbine housing 5 turbine rotor 6 compressor housing 7 compressor rotor 8 shaft 9 bearing housing 10 silencer 11 volute housing section 12 insert section 13 main flow channel 14 circulation chamber 15 contour wall 16 circulation opening 17 circulation opening 18 intake element 18a radially outer section 18b radially inner section 19 clamp 20 flange connection 21 centrifugal compressor 22 compressor rotor 23 compressor casing 24 volute section 25 liner section 26 main flow passage 27 circulation chamber 28 contour wall 29 circulation opening 30 circulation opening 31 strut 32 upstream section 33 downstream section 34 suction element 34a radially inner section 34b radially outer section 35 flange 36 flange connection 37 section 38 section undercut
    权利要求:
    Claims (10)
    [1]
    1. Radial compressor (21), in particular radial compressor of an exhaust gas turbocharger,with a compressor rotor (22);a compressor casing (23) having a radially outer volute portion (24) and a radially inner liner portion (25);with a main flow channel (26) for supplying a medium to be compressed in the direction of the compressor rotor (22);with a circulation chamber (27) arranged radially outside of the main flow channel (26), which is delimited from the main flow channel (26) by a contoured wall (28), which is connected to the main flow channel (26) via circulation openings (29, 30), and which via struts (31) extending in the circulation chamber (37) is connected to the liner section (25), the main flow channel (26) being defined by the contour wall (28) and upstream of the contour wall (28) by an upstream portion (32) of the liner section ( 25) is limited;with a suction element (34) arranged upstream of the compressor housing (23), which has a radially outer section (34b) on the spiral housing section (24) and a radially inner section (34a) on the upstream section (32) of the insert section (25) adjacent,characterized in thatabutting surfaces of the radially inner portion (34a) of the suction member (34) and the upstream portion (32) of the liner portion (25) lie on a cylindrical surface.
    [2]
    Centrifugal compressor according to claim 1, characterized in that the respective surface of the radially inner portion (34a) of the suction member (34) faces radially inward and the adjacent surface of the upstream portion (32) of the insert portion (25) faces radially outward.
    [3]
    Centrifugal compressor according to claim 1 or 2, characterized in that the upstream portion (32) of the liner portion (25) is positioned radially inward relative to the radially inner portion (34a) of the suction member (34).
    [4]
    4. Centrifugal compressor according to one of Claims 1 to 3, characterized in that the struts (31) via which the contoured wall (28) is connected to the insert section (25) engage on a section (37) of the insert section (25) which is radially outwardly offset from the upstream portion (32) of the liner portion (25) and is connected to the upstream portion (32) of the liner portion (25) by a radially extending portion (38).
    [5]
    Centrifugal compressor according to claim 4, characterized in that a free space (39) is formed between this radially extending section (38) of the insert section (25) and the radially inner section (34a) of the suction element (34).
    [6]
    Centrifugal compressor according to one of Claims 1 to 5, characterized in that an undercut (40) or a material recess is formed on the upstream section (32) of the insert section (25).
    [7]
    Centrifugal compressor according to Claim 6, characterized in that the undercut (40) or material recess faces radially inwards with respect to the radially outwardly directed surface of the upstream section (32) of the insert section (25).
    [8]
    Centrifugal compressor according to any one of Claims 1 to 7, characterized in that the insert section (25) is made in one piece.
    [9]
    9. Centrifugal compressor according to one of Claims 1 to 7, characterized in that the insert section (25) is designed in several parts.
    [10]
    The centrifugal compressor according to any one of claims 1 to 9, characterized in that the insert portion (25) and the radially outer volute portion (24) of the stator-side compressor casing (23) are component-separated, the same being provided by separate components.
    类似技术:
    公开号 | 公开日 | 专利标题
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    EP3070270B1|2022-03-09|Stator vane for rotary machine having a sealing device, stator and flow engine
    DE112013002029T5|2015-03-05|Centrifugal oil seal and turbocharger with centrifugal oil seal
    EP2884054A1|2015-06-17|Variable guide vane with cone frustum in a bearing arrangement
    DE60217365T2|2007-05-16|SEALING METHOD AND DEVICE FOR THE WAVE OF A GAS TURBINE
    DE60217049T2|2007-07-12|Ölluftseparatorplug
    DE102007050916A1|2008-04-30|Stator arrangement for compressor of fluid conveying arrangement in gas turbine engine, has radial passage conduit formed in part of stator ring segment, where radial passage conduit is arranged adjacent to stator blade passage conduit
    EP0999349B1|2005-05-11|Axial turbine
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    DE102016115610A1|2018-03-01|A gas turbine and method for suspending a turbine vane segment of a gas turbine
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    DE102014106415A1|2015-11-12|compressor housing
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    EP3192966A1|2017-07-19|Rotor for an axial flow engine with axially aligned momentum flange and compressor
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    EP1992789A1|2008-11-19|Exhaust gas turbine casing comprising a support element
    EP3374602B1|2020-05-20|Arrangement for sealing a bearing casing and exhaust gas turbocharger comprising such arrangement
    CH714650A2|2019-08-15|Radial compressor.
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    同族专利:
    公开号 | 公开日
    US20190293086A1|2019-09-26|
    CH714850A2|2019-09-30|
    JP2019167960A|2019-10-03|
    RU2019108167A|2020-09-21|
    DE102018106971A1|2019-09-26|
    CN110296106A|2019-10-01|
    KR20190111778A|2019-10-02|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    DE19647605C2|1996-11-18|1999-03-11|Daimler Benz Ag|Exhaust gas turbocharger for internal combustion engines|
    DE10000418A1|2000-01-07|2001-08-09|Abb Turbo Systems Ag Baden|Compressor of an exhaust gas turbocharger|
    US7475539B2|2006-05-24|2009-01-13|Honeywell International, Inc.|Inclined rib ported shroud compressor housing|
    DE102010028975A1|2010-05-14|2012-03-29|Abb Turbo Systems Ag|Additional compressor housing|
    DE102012207727B4|2012-05-09|2019-04-18|Man Energy Solutions Se|centrifugal compressors|
    US20150159664A1|2012-06-18|2015-06-11|Borgwarner Inc.|Compressor cover for turbochargers|
    US9726185B2|2013-05-14|2017-08-08|Honeywell International Inc.|Centrifugal compressor with casing treatment for surge control|
    US10267214B2|2014-09-29|2019-04-23|Progress Rail Locomotive Inc.|Compressor inlet recirculation system for a turbocharger|
    US9951793B2|2016-06-01|2018-04-24|Borgwarner Inc.|Ported shroud geometry to reduce blade-pass noise|
    DE102016217528A1|2016-09-14|2018-03-15|Continental Automotive Gmbh|Turbocharger for an internal combustion engine|
    DE102017221717A1|2017-12-01|2019-06-06|Man Energy Solutions Se|centrifugal compressors|
    DE102018102704A1|2018-02-07|2019-08-08|Man Energy Solutions Se|centrifugal compressors|
    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    DE102018106971.5A|DE102018106971A1|2018-03-23|2018-03-23|centrifugal compressors|
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