• 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:
    The invention relates to a compressor for a turbocharger comprising at least the following: A compressor housing (10) having an air inlet for receiving air to be compressed in the compressor and an air outlet for discharging compressed air in the compressor, an axially extending drive shaft rotatably supported in the compressor housing (10) and rotatably driven by a drive engaging therewith, a compressor impeller (40) mounted in the compressor housing (10) relative to an air flow path between the air inlet and the air outlet and on the drive shaft (30). a radially extending diffuser passage (14) is provided in the compressor housing (10) having a first radial wall (22) and a second radial wall (24), a compressor spiral (15) extending across the air passage in the air flow path Diffuser passage (14) to the compressor impeller (40) connects and opens into the air outlet , a separate paddle - free Nachleitapparat, which in the radial diffuser passage (14) and arranged on the first radial wall (22) of the diffuser passage (14) is fixed, wherein between the separate paddle - free Nachleitapparat and a second axial radial wall opposite this (24) Diffuser passage (14) an axial clear width (a) is present. The separate blade-less Nachleitapparat is formed as an annular disc (60), which in the region of its radially inner diameter comprises a coaxial with the drive shaft and the second radial wall (24) of the diffuser passage (14) facing away first tube piece (32) which a certain axial extent (b) has. A radially inner peripheral surface of the first tube piece (32) is radially opposite a portion (13) of the compressor housing (10) and the axial clearance (a) is smaller than the axial extent (b) of the first tube piece (32).
    公开号:CH713634A2
    申请号:CH00207/18
    申请日:2018-02-20
    公开日:2018-09-28
    发明作者:Denkel Harald
    申请人:Man Energy Solutions Se；
    IPC主号:
    专利说明:

    description
    PRIOR ART [0001] The invention is based on a compressor for a turbocharger according to claim 1.
    Radial compressors as described for example in WO 2014/012 725 A1 usually have an inlet channel through which the fluid flows, an impeller which serves to drive or compress the fluid, and an outlet channel through which the compressed fluid leaves the radial compressor. Radial compressors are located in the outlet duct, i.e. in the direction of flow behind the compressor impeller, which is formed by a diffuser passage, often by means of a simple parallel-walled flow channel, a so-called diverter. It is used to delay the flow behind the impeller and thus build up pressure by converting kinetic to potential energy before it is further decelerated and rectified in a ring channel (compressor spiral). In some cases, fixed, usually profiled guide vanes are built into this diffuser passage, which serve to change the characteristic curve of the compressor. In these cases, one speaks frequently of a bladed diffuser or follow-up device. These guide vanes are usually a component together with a diffuser wall and their blunt end press against the opposite housing wall. The aerodynamically disadvantageous gaps, which lead to so-called gap losses, between the guide vane and the housing can be reduced in this way. Radial compressors are also known in the prior art, in which these guide vanes can be rotated or rotated for the purpose of controlling or regulating the compressor.
    In addition, compressors are known from the prior art with so-called. with guide devices without guide vanes, in which a separate body is inserted in the diffuser passage behind the compressor impeller. Shoveless guide vanes have the disadvantage that they cannot be jammed in the housing via guide vanes and therefore connecting elements such as Screws are used to attach such a shovel-less guide to the housing. If the connecting elements fail, however, it is possible for the bladeless guide device to come into contact with the compressor impeller and thus cause serious damage to the compressor.
    The present invention is therefore based on the object of developing a compressor with a shovelless follow-up device in such a way that it has greater functional reliability. Furthermore, a turbocharger with such a compressor should also be made available.
    This object is achieved according to the invention by the features of claim 1 and claim 9. Advantageous developments of the invention are the subject of the attached dependent claims.
    Disclosure of the Invention The invention relates to a compressor for a turbocharger, comprising at least the following: a compressor housing having an air inlet for receiving air to be compressed in the compressor and having an air outlet for discharging air compressed in the compressor, which is in an axial direction Directionally extending drive shaft, which is rotatably mounted in the compressor housing and can be driven in rotation by a drive engaging thereon, a compressor impeller which is arranged in the compressor housing with respect to an air flow path between the air inlet and the air outlet and on the drive shaft, a radially extending diffuser passage in the compressor housing, which has a first radial wall and a second radial wall, a compressor spiral, which connects as an air passage in the air flow path via the diffuser passage to the compressor impeller and opens into the air outlet, a separate blade Open guide device, which is arranged in the radial diffuser passage and is fastened to the first radial wall of the diffuser passage, an axial clear width being present between the separate bladeless guide device and an axially opposite second radial wall of the diffuser passage.
    According to the invention it is provided that the separate paddle-free follow-up device is designed as an annular disk which, in the region of its radially inner diameter, comprises a first tube piece which is coaxial with the drive shaft and points away from the second radial wall of the diffuser passage and which has a certain axial extent has, wherein a radially inner peripheral surface of the first pipe section radially opposite a portion of the compressor housing and wherein the axial clear width is smaller than the axial extent of the first pipe section. The first piece of pipe in particular encloses the drive shaft and the compressor impeller.
    Because a radially inner circumferential surface of the first pipe section is radially opposite a section of the compressor housing and, moreover, the axial clear width between the separate bladeless guide device and the axially opposite second radial wall of the diffuser passage is smaller than the axial extent of the first pipe section, is ensured that in the event of an unintentional detachment of the separate shovel-free guide device from the first radial wall of the diffuser passage, the separate shovel-free guide device cannot come into contact with the compressor wheel. This is because the first pipe section of the separate, blade-less guide device strikes the radially opposite section of the compressor housing or the second radial wall of the diffuser passage, but the remaining axial clear width in the diffuser passage is too narrow to allow axial and / or radial movement of the separate paddle-less guide, which could bring it into contact with the compressor wheel.
    CH 713 634 A2 Therefore, according to the invention, by the axial extension of the first pipe section, a geometry of the separate shovelless follow-up apparatus is created which, viewed in the axial direction, is too large in relation to the inside width of the diffuser passage to be axial and / or to allow radial movement of the separate paddle-less follower sufficient to contact the compressor wheel when its connection to the compressor housing has inadvertently disengaged. The invention thus solves the problem described at the outset that failure of the connection between the separate bladeless guide device and the compressor housing can damage the compressor. Overall, this increases the functional reliability of the compressor.
    The measures listed in the dependent claims advantageous refinements and improvements of the invention specified in the independent claims are possible.
    [0011] The first radial wall of the diffuser passage particularly preferably forms part of the compressor spiral.
    According to a development, the washer has a second, different from the first pipe section, the second pipe section, which is coaxial with the drive shaft, points away from the second radial wall of the diffuser passage and which centers the ring disk at a step of the compressor scroll. In particular, the second pipe section can be centered on a radially inner step of the second radial wall of the diffuser passage. In particular, the second pipe section can have a larger inner diameter than the first pipe section.
    At least the first piece of pipe can be formed in one piece with the washer, and the second piece of pipe is also formed, for example, in one piece with the tubular washer.
    According to a particularly preferred embodiment, a radially inner diameter of the first pipe section is radially opposite an insert, which is inserted into the compressor housing on the air inlet side and radially surrounds the compressor impeller. This insert then forms part of the compressor housing, for example.
    In particular, connecting elements such as e.g. Screws are provided, by means of which the shovel-free follow-up device or the annular disk is detachably fastened to the first radial wall of the diffuser passage.
    According to a preferred development, the axial clear width between the separate bladeless guide device or the annular disk and the axially opposite second radial wall of the diffuser passage can be at least largely constant with respect to the radial extent.
    The invention also relates to a turbocharger, in particular an exhaust gas turbocharger with a compressor as described above.
    The turbocharger is preferably characterized by a turbine which has a turbine housing and a turbine impeller which forms the drive for the drive shaft and which is arranged in the turbine housing on the drive shaft. The turbine housing is preferably connected to the compressor housing.
    Drawing The invention is described below using an exemplary embodiment with reference to the accompanying drawings. Show it:
    Figure 1 is a sectional view of a turbocharger with a compressor according to a preferred embodiment of the invention.
    FIG. 2 shows an enlarged section from the compressor of FIG. 1.
    DESCRIPTION OF THE EXEMPLARY EMBODIMENT As shown in FIG. 1, a turbocharger has a turbine 2 driven here, for example, by exhaust gas from an internal combustion engine, and a compressor 1 driven by the turbine 2. In other words, the turbocharger shown in FIG. 1 is an exhaust gas turbocharger.
    The compressor 1 has a compressor housing 10 with an air inlet 11 for receiving air to be compressed in the compressor 1 and an air outlet 12 for discharging air compressed in the compressor 1, a drive shaft 30 which is rotatably mounted in the compressor housing 10 , so that the drive shaft 30 can be rotatably driven by an engaging drive of the turbine 2, and a compressor impeller 40 with blading 41, the compressor impeller 40 in the compressor housing 10 with respect to an air flow path between the air inlet 11 and the air outlet 12 and on the drive shaft 30 is arranged.
    The turbine 2 is usually formed and has a turbine housing 20 and a turbine impeller 21 which forms the drive for the drive shaft 30 and which is arranged in the turbine housing 20 and on the drive shaft 30.
    In the compressor housing 10 of the compressor 1, a diffuser passage or intermediate passage 14 and a compressor spiral 15 are formed in the form of a spiral housing. The compressor scroll 15 closes as an air passage
    CH 713 634 A2 in the air flow path via the radially extending intermediate passage 14 to the compressor impeller 40 and opens into the air outlet 12.
    As can be seen from FIGS. 1 and 2, the compressor housing 10 also has an insert 13 which is inserted into the compressor housing 10 on the air inlet side, so that the insert 13 radially surrounds the compressor impeller 40. The compressor 1 also has a redirector 60, which is arranged in the diffuser passage 14 of the compressor housing 10.
    In the preferred embodiment of the compressor 1, the radially extending diffuser passage 14 in the compressor housing 10 has a first radial wall 22 and a second radial wall 24. The first radial wall 22 of the diffuser passage 14 preferably forms part of the compressor spiral 15.
    The Nachleitapparat 60 is a separate paddle-free Nachleitapparat, which is arranged in the radial diffuser passage 14 and attached to the first radial wall 15 of the diffuser passage 14. In particular, connecting elements not shown in the figures, e.g. Screws are provided, by means of which the separate vane-free guide device 60 is detachably fastened to the first radial wall 22 of the diffuser passage 14.
    As is shown in particular in FIG. 2, an axial clear width a is present between the separate bladeless guide device 60 and the second radial wall 24 of the diffuser passage 14, which is axially opposite this. In this case, the axial clear width a between the separate bladeless guide device 60 and the second radial wall 24 of the diffuser passage 14 axially opposite this is largely constant with respect to the radial extent of the diffuser passage 14. Only in the area of the radially inner diameter of the separate bladeless guide device 60 does this diverge somewhat conically away from the axially opposite second radial wall 24 of the diffuser passage 14.
    The separate shovel-free follow-up device 60 is designed as an annular disk which, in the region of its radially inner diameter, comprises a first pipe piece 32 which is coaxial with the drive shaft 30 and points away from the second radial wall 24 of the diffuser passage 14 and has a specific axial extent b ,
    Furthermore, a radially inner circumferential surface of the first tube piece 32 is radially opposite a section of the compressor housing 10, this section being formed in particular by a section of the insert piece 13 and in particular a narrow radial gap, not visible in FIG. 2, between the radial Inner circumferential surface of the first pipe section 32 and this section of the insert 13 is present, but which is so narrow that it does not affect the air flow through the diffuser passage 14.
    Preferably, the washer 60 has a second, different from the first pipe section 32 second pipe section 34, which is coaxial with the drive shaft 30, away from the second radial wall 24 of the diffuser passage 14 and which has the annular disk 60 on a radially inner Level 36 of the compressor scroll 15 centered. In particular, the second pipe section 34 has a larger inner diameter than the first pipe section 32. The first pipe section 32 and the second pipe section 34 are formed, for example, in one piece with the annular disk 60. Furthermore, the first pipe section 32 and the second pipe section 34 in particular enclose the drive shaft 30 and the compressor impeller 40.
    Furthermore, the axial clear width a between the separate paddle-free follow-up device in the form of the annular disk 60 and the axially opposite second radial wall 24 of the diffuser passage 14 is smaller than the axial extent b of the first pipe section 34. This prevents that at one unintentional loosening of the separate bladeless guide device in the form of the washer 60 from the first radial wall 32, for example as a result of a break in the screw (s), which can come into contact with the compressor impeller 40 and thereby seriously damage the compressor 1.
    The invention can be implemented in any type of compressor 1 without a combination of the compressor 1 with a turbine 2 being necessary for this.
    Reference symbol list [0033]
    compressor
    turbine
    compressor housing
    air intake
    air outlet
    insert
    diffuser passage
    CH 713 634 A2
    compressor spiral
    turbine housing
    Turbine impeller first radial wall second radial wall
    Drive shaft first pipe section second pipe section radially inner stage
    compressor impeller
    blading
    Guide device a axial clear width b axial extension
    权利要求:
    Claims (11)
    [1]
    claims
    1. Compressor (1) for a turbocharger, comprising at least the following:
    a) A compressor housing (10) with an air inlet (11) for receiving air to be compressed in the compressor (1) and with an air outlet (12) for discharging air compressed in the compressor (1), b one in the axial direction extending drive shaft (30) which is rotatably mounted in the compressor housing (10) and can be driven in rotation by a drive acting thereon,
    c) a compressor impeller (40) which is arranged in the compressor housing (10) with respect to an air flow path between the air inlet (11) and the air outlet (12) and on the drive shaft (30), d a radially extending diffuser passage (14 ) in the compressor housing (10), which has a first radial wall (22) and a second radial wall (24),
    e) a compressor spiral (15), which connects as an air passage in the air flow path via the diffuser passage (14) to the compressor impeller (40) and opens into the air outlet (12),
    f) a separate paddle-free guide device which is arranged in the radial diffuser passage (14) and is fastened to the first radial wall (22) of the diffuser passage (14), wherein
    g) an axial clear width (a) is present between the separate bladeless guide device and a second radial wall (24) of the diffuser passage (14) axially opposite this, wherein
    h) the separate, vane-less guide device is designed as an annular disc (60) which, in the region of its radially inner diameter, has a first pipe section (32) which is coaxial with the drive shaft (30) and points away from the second radial wall (24) of the diffuser passage (14) which has a specific axial extent (b),
    i) a radially inner peripheral surface of the first pipe section (32) radially opposite a section (13) of the compressor housing (10), wherein
    j) the axial clear width (a) is smaller than the axial extent (b) of the first pipe section (32).
    [2]
    2. Compressor according to claim 1, characterized in that the first radial wall (22) of the diffuser passage (14) forms part of the compressor spiral (15).
    [3]
    3. Compressor according to claim 2, characterized in that the annular disc (60) has a second, from the first pipe section (32) different second pipe section (34), which is coaxial with the drive shaft (30), from the second
    CH 713 634 A2 faces away from the radial wall (24) of the diffuser passage (14) and which centers the annular disc (60) on a step (36) of the compressor spiral (15).
    [4]
    4. Compressor according to claim 3, characterized in that the second pipe section (34) has a larger inner diameter than the first pipe section (32).
    [5]
    5. Compressor according to one of the preceding claims, characterized in that at least the first pipe section (32) is integrally formed with the annular disc (60).
    [6]
    6. Compressor according to one of the preceding claims, characterized in that a radially inner diameter of the first pipe section (32) radially opposite an insert (13) which is inserted on the air inlet side in the compressor housing (10) and the compressor impeller (40) at least partially radially encloses.
    [7]
    7. Compressor according to one of the preceding claims, characterized in that connecting elements are provided, through which the annular disc (60) on the first radial wall (22) of the diffuser passage (14) is releasably attached.
    [8]
    8. Compressor according to one of the preceding claims, characterized in that the axial clear width (a) between the annular disc (60) and the axially opposite second radial wall (24) of the diffuser passage (14) is at least largely constant with respect to the radial extent is.
    [9]
    9. turbocharger with a compressor (1) according to any one of claims 1 to 8.
    [10]
    10. Turbocharger according to claim 9, characterized by a turbine (2) having a turbine housing (20) and a drive for the drive shaft (30) forming turbine impeller (21) in the turbine housing (20) on the drive shaft (30 ) is arranged.
    [11]
    11. Turbocharger according to claim 10, characterized in that the turbine housing (20) is connected to the compressor housing (10).
    CH 713 634 A2
    类似技术:
    公开号 | 公开日 | 专利标题
    EP1394365B1|2006-10-25|Turbocharger shaft sealing
    DE60114484T2|2006-08-03|compressor
    EP0903468A1|1999-03-24|Shroud for an axial turbine
    EP3408503B1|2021-04-07|Turbomachinery with bladed diffuser
    DE112015001237B4|2021-06-24|Exhaust gas turbocharger
    DE112014003165T5|2016-03-24|Variable nozzle unit and turbocharger with variable geometry system
    DE112015003934T5|2017-05-11|gas turbine
    DE112012002923B4|2021-11-11|Centrifugal compressor
    WO2019063384A1|2019-04-04|Diffuser for a compressor
    EP2617947A2|2013-07-24|Aviation gas turbine with adjustable fan
    CH708790A2|2015-04-30|A method and system for controlling compressor Front leakage.
    CH703666B1|2015-06-30|Device with a turbine, a diffuser and a hub flow path profile.
    DE102015111462B3|2016-09-22|Compressor with return flow channel and adjustable pilot vanes
    EP3246518A1|2017-11-22|Guide vane ring, corresponding assembly and turbomaschine
    DE112016002752T5|2018-03-29|SEAL STRUCTURE AND TURBOLADER
    EP2483567A1|2012-08-08|Radial compressor diffuser
    DE102008051980A1|2010-02-25|Air supply device for fuel cell for passenger car, has compressor including radial diffuser whose effective flow cross section is changeable by air guiding element of compressor
    CH713634A2|2018-09-28|Compressor for a turbocharger.
    DE102014221362A1|2016-04-21|Profiling of vanes of nozzles in turbomachinery, in particular compressors
    EP3376041A1|2018-09-19|Return stage and radial turbo fluid energy machine
    CH703654B1|2015-06-15|Means having a turbine and a diffuser.
    DE102012100339A1|2013-07-18|Method and device for stabilizing a compressor flow
    DE102015014900A1|2017-04-27|Radial turbine housing
    WO2019034740A1|2019-02-21|Diffuser for a radial compressor
    DE102014212909A1|2016-01-07|Flow deflection in a turbomachine
    同族专利:
    公开号 | 公开日
    CN108626173A|2018-10-09|
    CH713634B1|2021-07-30|
    JP2018162789A|2018-10-18|
    DE102017106360A1|2018-09-27|
    KR20180108462A|2018-10-04|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    JP5369198B2|2012-01-05|2013-12-18|トヨタ自動車株式会社|Compressor housing|
    DE102012212410A1|2012-07-16|2014-01-30|Siemens Aktiengesellschaft|Parallel diffuser for a fluid machine|
    WO2014030248A1|2012-08-24|2014-02-27|三菱重工業株式会社|Centrifugal compressor|
    WO2015138183A1|2014-03-11|2015-09-17|Borgwarner Inc.|Compressor wheel-shaft assembly|
    US10066639B2|2015-03-09|2018-09-04|Caterpillar Inc.|Compressor assembly having a vaneless space|
    GB2539227B|2015-06-10|2021-04-14|Cummins Ltd|Compressor and turbocharger|
    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    DE102017106360.9A|DE102017106360A1|2017-03-24|2017-03-24|Compressor for a turbocharger|
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