• 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 multistage exhaust gas turbocharger (1) having an exhaust gas turbine (3) having at least one turbine impeller and a compressor (2) having an outer compressor stage (4) with an outer compressor impeller section (6a) and an inner compressor stage (5) with an inner compressor impeller section (6b), wherein the turbine runner and inner (6b) and outer compressor runner portions (6a) are disposed on a common shaft rotatably mounted about an axis of rotation (1a), the outer compressor stage (4) having an axial compressor runner (6) upstream of the outer compressor runner portion (6a). 8) for connection to a fresh air duct and downstream of the outer compressor impeller section (6a) comprises at least two outer auger duct assemblies (10a, 10b, 10c, 10d, 10e) arranged in at least two inner auger duct assemblies (11) extending upstream of the inner compressor impeller section (6b) internal compressions go over step (5). In order to reduce thermal stresses, an outer coolant channel arrangement (13) extending at least between the outer screw channel arrangements (10a, 10b, 10c, 10d, 10e) and / or an inner coolant channel arrangement (14) extending between the inner screw channel arrangements (11) is provided.
    公开号:AT516978A1
    申请号:T50242/2015
    申请日:2015-03-26
    公开日:2016-10-15
    发明作者:Kurt Ing Prevedel
    申请人:Avl List Gmbh；
    IPC主号:
    专利说明:

    The invention relates to a multi-stage exhaust gas turbocharger, in particular high-pressure turbocharger, for an internal combustion engine having an at least one turbine impeller exhaust gas turbine and a compressor with an outer compressor stage with an outer Verdichterlaufradabschnitt and an inner compressor stage with an inner Verdichterlaufradabschnitt, wherein turbine runner and inner and outer Verdichterlaufradabschnitt on a The outer compressor stage upstream of the outer compressor rotor section has an axial compressor inlet port for connection to a fresh air line and downstream of the outer compressor rotor section at least two outer screw channel arrangements arranged in at least two inner upstream of the inner compressor rotor section
    Skip the screw channel arrangements of the internal compressor stage. The invention further relates to an internal combustion engine having at least one such exhaust gas turbocharger.
    Turbochargers with high pressure ratios are needed to provide high fuel economy, high horsepower, and improved emissions performance in internal combustion engines.
    In order to achieve high pressure conditions, the rotational speeds of the rotors of exhaust gas turbochargers can be increased. However, this can lead to loads that exceed the capacity of the materials used.
    It is known to carry out a multi-stage compression of the charge air with two or more exhaust gas turbochargers, which operate with compressors connected in series, intercoolers being arranged between the compressors. Such solutions are known for example from US 2014/0358404 Al. The disadvantage, however, is that these solutions are very complex and space-consuming. A similar approach is to use multiple compressor wheels on a common axle to achieve compressor stages, including combining axial and radial compression stages. However, here, too, disadvantages in the package size, but also in the rotor dynamics and bearing issues, result, in particular, from the increased length of the exhaust gas turbocharger.
    DE 699 14 199 Τ2 shows this purpose a slow-speed high-pressure turbocharger with two-stage compressor, wherein the turbine runner and the compressor wheel are connected to each other via a common shaft. The compressor impeller has first impeller blades on a front side near an air inlet and second impeller blades on a rear side. The compressed air is passed through a diffuser from the front to the back and from there into the inlet system. A similar solution is shown in EP 1 825 149 B1. On the other hand, US Pat. No. 6,834,501 B1, US Pat. No. 6,792,755B2 or US Pat. No. 6,920,754 B2 discloses an exhaust-gas turbocharger in which annular gaps are formed between the front and rear sides of the two-stage compressor. While this allows high compression ratios, the material is subjected to high stresses due to the high temperatures. While the air at the air inlet is at a temperature of approximately 25 ° C, the temperature at the impeller blades rises above 4 bar at pressures below 4 ° C well above 200®C. Both the impeller blades and the turbocharger housing and the bearings are exposed to high thermal loads. In addition, from temperatures of about 180 ° C, coking of airborne oil fractions, e.g. from blowby gases.
    EP 1 957 802 Bl proposes in this respect to use temperature-resistant materials or to make provision in this respect bearing and wave design.
    A disadvantage of all known solutions, on the one hand, the high temperature of the compressed air streams, on the other hand, the resulting thermal stresses of the turbocharger housing and the components used.
    The object of the invention is to reduce the thermal load of a multi-stage exhaust gas turbocharger.
    This object is achieved by an aforementioned multistage exhaust gas turbocharger according to the invention in that an extending at least between the outer screw channel assemblies outer coolant channel arrangement and / or extending between the inner screw channel arrangements inner coolant channel arrangement is / are provided.
    The invention allows cooling of the air in the exhaust gas turbocharger, either by cooling the precompressed air already in the outer compressor stage, in the inner compressor stage or in both compressor stages. This also results in a smaller compressor drive and Turbineabgabeleistung and a reduced exhaust backpressure. Since the highest thermal load in the volute of the inner compressor stage occurs, ie where the air from the exhaust gas turbocharger in a subsequent charge air passage, this can in any case reduce the high thermal load. While the air enters the external compressor stage at about 25 ° C, it has almost 200 ° C at the outlet - an inadmissibly high temperature increase would occur in the inner compressor stage, which causes high loads on turbocharger components. By means of the coolant arrangements, the charge air can be cooled to about 60 ° C. Thus, the air is maintained in a temperature range at which the coking of airborne oil fractions, e.g. from blowby gases, is avoided.
    On the one hand, cooling of the charge air takes place through the coolant channel arrangements, which leads to lower intercooler waste heat and thus better efficiency, but on the other hand also to cooling of the compressor housing and of the remaining exhaust gas turbocharger. The cooling liquid can be used subsequently for cooling the shaft bearings of the exhaust gas turbocharger, which allows a saving of connections and lines. Furthermore, the arrangement allows a particularly compact design, so that, for example, before the compressor input other components such. a cross-charger can be arranged.
    In order to achieve particularly effective cooling, it is advantageous if the outer coolant channel arrangement extends at least partially into the outer contour region of the outer compressor rotor section and / or the inner coolant channel arrangement extends at least partially into the inner contour region of the inner compressor rotor section. In this case, the contoured region is the channel wall section between the entry of a compressor impeller section and the exit of a compressor impeller section. Since it comes in this area to particularly high temperature gradient due to the compression of the air here is an effective cooling of particular advantage.
    In a variant of the invention, the outer coolant arrangement extends from the region between the outer screw channel arrangements into an ambient area surrounding at least one or more of the outer screw channel arrangements and / or the inner coolant arrangement from the area between the inner screw channel arrangements into at least one or more of the inner screw channel arrangements surrounding surrounding area. In this way, the cooling effect can advantageously be increased since there is an increase in the cooling surfaces - the screw channel arrangements increase with increasing distance from the axis of rotation of their inner surface, which offers by the enclosure by the coolant assemblies particularly high heat transfer contact surface.
    To achieve favorable flow conditions, the outer coolant channel arrangement has an outer coolant collector and outer coolant sub-ducts emanating therefrom and / or the inner coolant channel arrangement has an inner coolant collector and inner coolant sub-ducts emanating therefrom. In this way, coolant can be provided via the coolant collectors and guided via the subchannels to the areas to be cooled. Both coolant collectors and subchannels may comprise or extend between the screw channel arrangements.
    Particularly effective cooling can be achieved if the inner coolant arrangement and the outer coolant arrangement, advantageously the outer coolant sub-channels and the inner coolant sub-channels, are flow-connected to one another. This also results in a simple design of the cooling, since it can be saved on inlets and outlets.
    Depending on the thermal load, at least one coolant supply line to the inner coolant channel arrangement and at least one coolant discharge line from the outer coolant arrangement are provided, or vice versa. This is ensured by appropriate connections. Thus, depending on the requirement, fresh coolant can first be routed to the inner or first to the outer compressor stage.
    In order to facilitate the production of the exhaust gas turbocharger according to the invention, it is advantageous if the compressor has a compressor housing with at least one outer compressor housing part and at least one inner compressor housing part. The parts can be cast separately and then joined together.
    The object of the invention is further achieved by an internal combustion engine with at least one such exhaust gas turbocharger.
    The invention is explained in more detail below with reference to the non-limiting figures. Show:
    1 shows an exhaust gas turbocharger according to the invention in a longitudinal section,
    2 shows the upper half of the compressor side of the exhaust gas turbocharger of FIG. 1 in a section along the line II -II in Fig. 1, and
    3 shows the compressor side of the exhaust gas turbocharger from FIG. 1 in a sectional view along the line III-III in FIG. 1.
    Functionally identical parts are provided in the embodiments with the same reference numerals.
    Fig. 1 shows schematically a multi-stage compression exhaust gas turbocharger 1 with a compressor 2 and an exhaust gas turbine 3 with a turbine impeller, not shown. The compressor 2 has an outer compressor stage 4 and an inner compressor stage 5. The term outer and inner refers to the flow direction of the fresh air flowing through the compressor 2. The separation between outer 4 and inner compressor stage 5 is shown in FIGS. 1 and 2 indicated by the dashed line.
    A compressor impeller 6 is connected to the turbine wheel of the exhaust gas turbine 3 of the exhaust gas turbocharger 1 in a rotationally fixed connection via a shaft which is rotatably mounted about an axis of rotation la and not shown further. The compressor impeller 6 has an outer compressor impeller section 6a associated with the outer compressor section 4 and an inner compressor impeller section 6b assigned to the inner compressor section 5. The compressor wheel sections 6a, 6b are arranged in the illustrated embodiment on opposite sides of a common compressor wheel 6.
    The compressor 2 is disposed in a compressor housing, which has an outer compressor housing part 7a and an inner compressor housing part 7b, which are interconnected and sealed. In the outer compressor housing part 7a, the outer compressor stage 4 is arranged while the inner compressor stage 5 is located in the inner compressor housing part 7b. The bonding area is indicated by the above-mentioned dashed lines in Figs. 1 and 2 indicated. Embodiments are also possible where a plurality of housing parts are provided.
    The outer compressor housing part 7a has, upstream of the outer compressor rotor section 6a, an axial compressor inlet connection 8 for the connection of a fresh air line not shown for sucking in fresh air. A compressor outlet for charge air on the inner compressor housing part 7b for connection to a charge air line of an internal combustion engine is also not shown in detail.
    From the compressor inlet port 8, the air to the (outer) contour region 9 of the outer Verdichterlaufradabschnitts 6 a is performed. As a contour region, the channel wall section between the entry of a compressor impeller section and the outlet of a compressor impeller section is designated here, in particular the section where the air duct widens from a small diameter to a larger diameter.
    Upstream of the outer compressor impeller section 6a, the precompressed air is transferred to a plurality of outer auger duct arrangements 10a, 10b, 10c, 10d, 10e and volutes, respectively. The outer screw channel arrangements 10a, 10b, 10c, 10d, 10e run in a circular manner with increasing radius about the rotation axis 1a. At the same time, the diameter of the outer screw channel arrangements 10a, 10b, 10c, 10d, 10e increases in the flow direction.
    The outer screw channel arrangements 10a, 10b, 10c, 10d, 10e of the outer compressor stage 4 enter into an equal number of inner screw channel arrangements 11, 11 (only two inner screw channel arrangements 11, 11 are shown in the figures, or only one 11 is discussed in the following). the inner compressor stage 5 via. As can be seen in FIG. 3, in the exemplary embodiment illustrated, the outer screw channel arrangements 10a, 10b, 10c, 10d, 10e lie essentially on a circle whose center lies on the axis of rotation 1a (in FIG. 3 normal to the image plane and not drawn) ,
    The inner screw channel assemblies 11, 1Γ also run in a circle around the axis of rotation la, but in contrast to the outer
    Screw channel arrangements with decreasing radius in the flow direction, possibly also with decreasing diameter. The inner screw channel assemblies 11 open near the axis of rotation la in the (inner) contour region 12 of the inner Verdichterlaufradabschnitts 6b or its entrance. From the outlet of the inner compressor impeller section 6b, the compressed air is continued to a charge air duct, not shown.
    For cooling the compressor 2, coolant duct arrangements 13, 14 according to the invention are now carried out in the compressor housing parts 7a, 7b. In this case, an outer coolant channel arrangement 13 is provided in the outer compressor stage 4, which has an outer coolant accumulator 15 and outer coolant subducts 16a, 16b, 16c, 16d, 16e (shown by dashed lines in FIGS Coolant discharge 17 is connected. The outer coolant collector 15 runs in the illustrated embodiment in an annular manner around the inner contour region 9.
    An inner coolant passage assembly 14 is provided in the inner compressor stage 5 and includes an inner coolant manifold 18 and internal coolant sub-channels 19, 19 '(shown in broken lines in FIGS. The inner coolant passage assembly 14 is connected to a coolant supply line 20. As coolant while water or other liquids or fluids can be used.
    The coolant channel arrangements 13, 14 or the coolant sub-channels 16a, 16b, 16c, 16d, 16e, 19 extend between the respective ones
    Screw channel arrangements 10a, 10b, 10c, 10d, 10e, 11, 1Γ. This results in efficient heat removal in the thermally critical areas and the temperature of the compressed air can be kept within an optimal range. As can be seen in FIG. 2, the coolant arrangements 13, 14 extend into the contour regions 9, 12 of the respective compressor rotor sections 6a, 6b, where a particularly high thermal load occurs and therefore heat dissipation is particularly necessary.
    3 shows a sectional view along the line III-III from Fig.l - in the upper half, the outer coolant assembly 13 extends or extend the outer coolant sub-channels 16a, 16b, 16c from the area between the outer screw channel assemblies 10a, 10b, 10c, 10d, 10e surrounding regions in the screw channel assemblies 10a, 10b, 10c, 10d, 10e. Ambient area here means areas outside the intermediate area between the screw channel arrangements, that is to say around the screw channel arrangements or in their circumference, wherein surroundings still thermally denote areas influenced by the compressed air. The coolant arrangement 13 thus comprises the screw channel arrangements 10a, 10b, 10c, 10d, 10e for optimum heat dissipation. This achieves an increase in the heat transfer area between hot air ducts and cooling arrangement. The sufficiently high degree of cooling surfaces and the teeth of the cooling and cooling flow paths allows sufficient cooling of the compressor 2 and a use of the exhaust gas turbocharger 1 as a high-pressure turbocharger. A corresponding embodiment can also be provided for the inner compressor stage 5, but is not shown for reasons of clarity.
    The inner 13 and outer coolant channel assembly 14 are fluidly connected to each other, wherein in the illustrated embodiment, the flow connection via the outer 16a, 16b, 16c, 16d, 16e and inner coolant sub-channels 19 takes place. Thus, a coolant supply line 20 in the region of the inner compressor stage 5 take place, the coolant discharge line 17 is then arranged on the outer compressor stage 4. Of course, the coolant can also be reversed.
    As described above, the inventive arrangement of air ducts and cooling channels can be realized particularly well with a compressor housing with an outer compressor housing part 7a and an inner compressor housing part 7b: these can be easily cast, e.g. made of particularly good heat-conducting aluminum, and assembled with suitable seals to a compact, media-tight compressor 2.
    The described invention allows by the two-stage charging and the additional cooling compared to a single-stage compression significant thermodynamic advantages with a compact design, which accommodates the increasing problem of decreasing space.
    It should be understood that the invention is not limited to the embodiment described, but various modifications are possible within the scope of the main claim.
    权利要求:
    Claims (9)
    [1]
    1. Multistage exhaust gas turbocharger (1), in particular high-pressure turbocharger, for an internal combustion engine, having an exhaust turbine (3) having at least one turbine impeller and a compressor (2) having an external compressor stage (4) with an external compressor impeller section (6a) and an internal compressor stage ( 5) having an inner compressor rotor section (6b), wherein turbine rotor and inner (6b) and outer compressor rotor section (6a) are arranged on a common shaft rotatably mounted about a rotation axis (la), the outer compressor stage (4) upstream of the outer compressor rotor section (6). 6a) comprises an axial compressor inlet stub (8) for connection to a fresh air duct and downstream of the outer compressor impeller section (6a) at least two outer auger duct arrangements (10a, 10b, 10c, 10d, 10e) extending in at least two upstream of the inner compressor impeller section (6b) inner snake canteen arrangements (11, 1Γ) of the inner compressor stage (5), characterized in that an outer coolant channel arrangement (13) extending at least between the outer screw channel arrangements (10a, 10b, 10c, 10d, 10e) and / or between the inner screw channel arrangements (11). 11, 1Γ) extending inner coolant passage arrangement (14) is provided.
    [2]
    2. Exhaust gas turbocharger (1) according to claim 1, characterized in that the outer coolant channel arrangement (13) extends at least partially into the outer contour region (9) of the outer Verdichterlaufradabschnitts (6a) and / or that the inner coolant channel assembly (14) at least partially in the inner contour region (12) of the inner Verdichterlaufradabschnitts (6b) extends.
    [3]
    3. Exhaust gas turbocharger (1) according to claim 1 or 2, characterized in that the outer coolant assembly (13) from the area between the outer screw channel assemblies (10a, 10b, 10c, lOd, lOe) in at least one or more of the outer screw channel assemblies (10a, 10b, 10c, 10d, 10e) and / or that the inner coolant assembly (14) extends from the region between the inner screw channel assemblies (11) into an ambient region surrounding at least one or more of the inner screw channel assemblies (11) ,
    [4]
    4. Exhaust gas turbocharger (1) according to any one of the preceding claims, characterized in that the outer coolant channel assembly (13) has an outer coolant collector (15) and outgoing outer coolant sub-channels (16a, 16b, 16c, 16d, 16e) and / or that the inner coolant channel arrangement (14) has an inner coolant collector (18) and outgoing inner coolant sub-channels (19, 19 ').
    [5]
    5. Exhaust gas turbocharger (1) according to one of the preceding claims, characterized in that the inner coolant channel arrangement (14) and the outer coolant channel arrangement (13) are flow-connected to one another.
    [6]
    6. Exhaust gas turbocharger (1) according to claim 4 or 5, characterized in that the outer coolant sub-channels (16a, 16b, 16c, 16d, 16e) are fluidly connected to the inner coolant sub-channels (19).
    [7]
    7. Exhaust gas turbocharger (1) according to any one of the preceding claims, characterized in that at least one coolant supply line (20) to the inner coolant passage assembly (14) is provided and at least one coolant discharge line (19) from the outer coolant passage arrangement (13) is provided, or vice versa.
    [8]
    8. Exhaust gas turbocharger (1) according to one of the preceding claims, characterized in that the compressor (2) has a compressor housing with at least one outer compressor housing part (7a) and at least one inner compressor housing part (7b).
    [9]
    9. Internal combustion engine with at least one exhaust gas turbocharger (1) according to one of claims 1 to 8.
    类似技术:
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    同族专利:
    公开号 | 公开日
    AT516978B1|2018-04-15|
    WO2016149728A1|2016-09-29|
    CN107636279B|2019-06-04|
    DE112016001401A5|2017-12-07|
    CN107636279A|2018-01-26|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US7014418B1|2004-12-03|2006-03-21|Honeywell International, Inc.|Multi-stage compressor and housing therefor|
    DE102007023142A1|2007-05-16|2008-11-20|Audi Ag|Exhaust gas compressor for automotive exhaust gas turbocharger has spiral wall incorporating cooling duct|
    DE102009001321A1|2009-03-04|2010-09-16|Ford Global Technologies, LLC, Dearborn|Supercharged internal combustion engine has intake line for supplying internal combustion engine with combustion air and compressor arranged in intake line|
    DE102011003901A1|2011-02-10|2012-08-16|Continental Automotive Gmbh|Exhaust gas turbocharger with cooled turbine housing and cooled bearing housing and common coolant supply|
    DE102013203376A1|2013-02-28|2014-08-28|Ford Global Technologies, Llc|Liquid-cooled radial-flow turbine for exhaust gas turbocharger of motor car, has bearing housing comprising coolant cladding integrated in bearing housing and arranged adjacent and spaced apart to assembly flange surface in flange|US10190596B2|2016-11-03|2019-01-29|Garrett Transportation I Inc.|Two-stage compressor with asymmetric second-stage inlet duct|
    DE102017114232A1|2017-06-27|2018-12-27|Ebm-Papst Mulfingen Gmbh & Co. Kg|Return geometry of a turbocompressor|
    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    ATA50242/2015A|AT516978B1|2015-03-26|2015-03-26|MULTI-STAGE ABGASTURBOLADER|ATA50242/2015A| AT516978B1|2015-03-26|2015-03-26|MULTI-STAGE ABGASTURBOLADER|
    CN201680028699.XA| CN107636279B|2015-03-26|2016-03-24|Multi-stag exhaust-driven turbo-charger exhaust-gas turbo charger and internal combustion engine|
    PCT/AT2016/050077| WO2016149728A1|2015-03-26|2016-03-24|Multi-stage turbocharger|
    DE112016001401.5T| DE112016001401A5|2015-03-26|2016-03-24|Multi-stage turbocharger|
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