• 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:
    A radial compressor (10) having a rotor rotor (14) having rotor blades, and having a compressor housing (11) accommodating a diffuser (13), the diffuser (13) at least partially defining a flow channel leading away from the blades of the compressor rotor (14) the diffuser (13) exclusively supporting blades (16).
    公开号:CH714854A2
    申请号:CH00222/19
    申请日:2019-02-21
    公开日:2019-09-30
    发明作者:Klima Jiri；Rezanina Jan
    申请人:Man Energy Solutions Se；
    IPC主号:
    专利说明:

    E. Blum & Co. AG Patent and Trademark Attorneys VSP, Vorderberg 11 8044 Zurich (CH)
    CH 714 854 A2
    Description: The invention relates to a radial compressor and a turbocharger.
    Turbochargers have a compressor and a turbine. A first medium is expanded in the turbine of a turbocharger, in which case the energy obtained is used in the compressor of the turbocharger to compress a second medium. 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 radial rotor has an axial flow and a radial flow out of the compressor rotor, the compressor rotor carrying rotor blades. The compressor housing receives an insert and a diffuser, the insert delimiting at least in sections a flow channel leading to the rotor blades of the compressor rotor and the diffuser a flow channel of the radial compressor leading away from the rotor blades of the compressor rotor.
    [0004] EP 1 340 920 B1 discloses a radial compressor with a diffuser, the diffuser of the radial compressor disclosed there having diffuser guide vanes. Such diffuser guide vanes of a diffuser of a radial compressor decisively determine the flow channel leading away from the guide vanes of the compressor rotor. Seen over the circumference of the diffuser, a relatively high number of diffuser guide vanes is arranged, namely at least 16 diffuser guide vanes, which accordingly extend at a small circumferential distance from one another and have a relatively large length between a leading edge and a trailing edge.
    Proceeding from this, the present invention has for its object to provide a novel radial compressor and a turbocharger with such a radial compressor.
    This object is achieved by a radial compressor according to claim 1. According to the invention, the diffuser has exclusively support blades. The diffuser according to the invention has no diffuser guide vanes, but rather only support vanes. In contrast to diffuser guide vanes, the support blades do not significantly determine the flow channel leading away from the rotor blades of the compressor rotor. The support blades essentially serve only to improve the fixation of the diffuser in the radial compressor. The flow of the compressed medium is hardly influenced by the support blades. Such a diffuser makes it possible to combine the advantages of diffusers that have been blasted with diffuser guide vanes with the advantages of vaneless diffusers. In particular, the so-called characteristic map of the radial compressor is not restricted.
    According to an advantageous development, the diffuser has 3 to 10 support blades, preferably between 3 to 7 support blades, distributed over its circumference. Such a small number of support blades is preferred in order to maintain the advantages of bladeless diffusers.
    According to an advantageous development, the radially inner edges of the support blades lie on a diameter d3, the following applying to the diameter d3 on which the radially inner edges of the support blades lie: 1.2 * d2 <d3 <1.35 * d2, where d2 is an outer diameter of the compressor rotor of the radial compressor. These details also serve to maintain the advantages of bladeless diffusers.
    According to an advantageous development, radially outer edges of the support blades lie on one diameter. For a length L of the support blades determined by the distance between the radially inner edges and the radially outer edges, the following applies: 0.1 * d2 <L <0.3 * d2, where d2 is the outer diameter of the compressor rotor of the radial compressor. With such a length of the support blades, the advantages of bladeless diffusers can be maintained.
    [0010] The turbocharger according to the invention is defined in claim 9.
    Preferred further 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 restricted to this. It shows:
    1 shows an axial section through a detail of a radial compressor;
    2 is a view of a diffuser of the radial compressor in the viewing direction II of FIG. 1st
    The invention relates to a radial compressor and a turbocharger with a radial compressor.
    The basic structure of a turbocharger is familiar to the expert addressed here. At this point it should be noted that a turbocharger has a compressor and a turbine. A first medium, in particular exhaust gas, is expanded in the turbine of the turbocharger and energy is thereby obtained. The energy gained in the expansion of the first medium in the turbine is used in the compressor of the turbocharger in order to compress a second medium, in particular charge air.
    The present invention relates to a turbocharger and a radial compressor for a turbocharger, wherein a radial compressor flows from the medium to be compressed in the axial direction and flows from the compressed medium in the radial direction.
    CH 714 854 A2 [0015] The turbine (not shown) of a turbocharger has a turbine rotor and a turbine housing. The compressor, namely the radial compressor 10, has a compressor housing 11 and a compressor rotor 14. The turbine rotor and compressor rotor 14 are coupled via a shaft (not shown) which is mounted in a bearing housing 15. The bearing housing 15 is connected on the one hand to the turbine housing of the turbine and on the other hand to the compressor housing 11 of the radial compressor 10.
    1 further shows an insert 12 and a diffuser 13. The insert 12 delimits a flow channel leading to the rotor blades of the compressor rotor 14 and the diffuser 13 delimits a flow channel leading away from the rotor blades of the compressor rotor 14 in each case at least in sections.
    The diffuser 13 of the radial compressor 10 according to the invention does not have any diffuser guide vanes which decisively define the flow of the medium downstream of the compressor rotor 14, but only via support vanes 16 which serve for the simplified assembly and installation of the diffuser 13 in the compressor housing 11.
    About 3 and 10 support blades 16, preferably between 3 and 7 support blades 16, particularly preferably between 4 and 6 support blades 16, are distributed over the circumference of the diffuser 13. As can be seen in FIG. 2, in the preferred exemplary embodiment shown, 5 support blades 16 are distributed over the circumference of the diffuser 13.
    A relatively large distance is formed between the individual support blades 16, in particular, seen in the radial direction, there is no overlap between adjacent support blades 16. The support blades 16 therefore hardly influence a flow of the compressed medium downstream of the blades 14 of the compressor rotor 14. The distance between immediately adjacent support blades 16 in the circumferential direction is at least 10 °, preferably at least 20 °, particularly preferably at least 30 °. Viewed in the radial direction and in the circumferential direction, none of the support blades 16 then extend in this angular range. Accordingly, the flow of the compressed medium can flow past the support blades 16 unimpeded and not deflected in this angular range.
    Radially inner edges 17 of the support blades 16, which are also referred to as leading edges, lie on a circle or a circular contour with the diameter d3. For this diameter d3, on which the radially inner edges 17 of the support blades 16 lie, the following applies: 1.2 * d2 <d3 <1.35 * d2. where d2 is the outer diameter of the compressor rotor 14 of the radial compressor.
    In addition to the radially inner edges 17, the support blades 16 also have radially outer edges 18, which are also referred to as trailing edges. A distance between the radially inner edges 17 and the radially outer edges 18 determines a length L of the support blades 16. For the length L the following applies: 0.1 * d2 <L <0.3 * d2, where d2 in turn is the outer diameter of the compressor rotor 14 is.
    The radially outer edges 18 lie on a circular contour with the diameter d4. For this diameter d4, on which the radially outer edges 18 of the support blades 16 lie, the following applies: 1.4 * d2 <d4 <1.55 * d2, where d2 in turn is the outside diameter of the compressor rotor 14 of the radial compressor 10.
    With the present invention, a radial compressor 10 or a turbocharger with a radial compressor 10 is accordingly proposed, wherein the diffuser 13 of the radial compressor 10 has support blades 16 which have a relatively small length L, which have a relatively small radial extent caused by the difference d4-d3 is defined, and which, when viewed in the circumferential direction, also have a relatively large distance. In this way, the advantages of bladeless diffusers can be maintained. The diffuser 13 can easily be mounted in the compressor housing 11.
    Reference symbol list [0024]
    centrifugal compressors
    compressor housing
    insert
    diffuser
    compressor rotor
    bearing housing
    stay vane
    权利要求:
    Claims (9)
    [1]
    CH 714 854 A2
    claims
    1. Radial compressor (10), with a rotor having a compressor rotor (14);
    a compressor housing (11) accommodating a diffuser (13), the diffuser (13) delimiting at least in sections a flow channel leading away from the rotor blades of the compressor rotor (14); characterized in that the diffuser (13) has exclusively support blades (16).
    [2]
    2. A radial compressor according to claim 1, characterized in that the diffuser (13) has 3 to 10 support blades (16) distributed over its circumference.
    [3]
    3. A radial compressor according to claim 1 or 2, characterized in that the diffuser (13) has 3 to 7 support blades (16) distributed over its circumference.
    [4]
    4. Radial compressor according to one of claims 1 to 3, characterized in that radially inner edges (17) of the support blades (16) lie on a circular contour with a diameter (d3).
    [5]
    5. A radial compressor according to claim 4, characterized in that for the diameter (d3) on which the radially inner edges (17) of the support blades (16) lie: 1.2 * d2 <d3 <1.35 * d2, where d2 is an outer diameter of a compressor rotor (14) of the radial compressor.
    [6]
    6. Radial compressor according to one of claims 1 to 5, characterized in that radially outer edges (18) of the support blades (16) lie on a circular contour with a diameter (d4).
    [7]
    7. A radial compressor according to claim 4, characterized in that for the diameter (d4) on which the radially outer edges (18) of the support blades (16) lie: 1.4 * d2 <d4 <1.55 * d2, where d2 is an outer diameter of a compressor rotor (14) of the radial compressor
    [8]
    8. A radial compressor according to one of claims 3 to 4, characterized in that for a length (L) of the support blades (16) determined by the distance between radially inner edges (17) and radially outer edges (18): 0.1 * d2 <L <0.3 * d2, where d2 is an outer diameter of a compressor rotor (14) of the radial compressor.
    [9]
    9. turbocharger,
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    同族专利:
    公开号 | 公开日
    DE102018107264A1|2019-10-02|
    US20190301487A1|2019-10-03|
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    RU2019108603A|2020-09-28|
    KR20190113553A|2019-10-08|
    CN110307180A|2019-10-08|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US6669436B2|2002-02-28|2003-12-30|Dresser-Rand Company|Gas compression apparatus and method with noise attenuation|
    ITMI20022661A1|2002-12-17|2004-06-18|Nuovo Pignone Spa|IMPROVED DIFFUSER FOR A CENTRIFUGAL COMPRESSOR.|
    EP1860325A1|2006-05-26|2007-11-28|ABB Turbo Systems AG|Diffuser|
    US8328535B2|2007-02-14|2012-12-11|Borgwarner Inc.|Diffuser restraint system and method|
    US8100643B2|2009-04-30|2012-01-24|Pratt & Whitney Canada Corp.|Centrifugal compressor vane diffuser wall contouring|
    EP2549122A4|2010-03-18|2013-12-18|Toyota Motor Co Ltd|Centrifugal compressor and turbo supercharger|
    US8511981B2|2010-07-19|2013-08-20|Cameron International Corporation|Diffuser having detachable vanes with positive lock|
    EP2690291B1|2011-03-23|2015-08-05|Toyota Jidosha Kabushiki Kaisha|Centrifugal compressor|
    CN102562673A|2012-01-03|2012-07-11|大同北方天力增压技术有限公司|Date-pit-shaped vane diffuser for centrifugal air compressor of turbocharger|
    CN103244461B|2012-02-14|2016-03-30|珠海格力电器股份有限公司|Low denseness vane diffuser and manufacture method thereof|
    DE102014012764A1|2014-09-02|2016-03-03|Man Diesel & Turbo Se|Radial compressor stage|
    DE102015012225A1|2015-09-18|2016-04-14|Daimler Ag|Guide for a compressor of an exhaust gas turbocharger|
    DE102015016486A1|2015-12-17|2017-06-22|Man Diesel & Turbo Se|Radial turbine, turbocharger and insert for a turbine housing of the radial turbine|
    DE102016201256A1|2016-01-28|2017-08-03|Siemens Aktiengesellschaft|Turbomachine with bladed diffuser|
    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    DE102018107264.3A|DE102018107264A1|2018-03-27|2018-03-27|Centrifugal compressor and turbocharger|
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