• 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 turbocharger (1) comprising a turbine (2) for venting a first medium, the turbine (2) comprising a turbine housing (4) and a turbine rotor (5), comprising a compressor (3) for compressing a second medium using energy recovered in the turbine (2) upon expansion of the first medium, the compressor (3) having a compressor housing (6) and a compressor rotor (7), wherein a temperature of the first medium to be relaxed or relaxed is lower than a temperature of the first medium to be compressed or the compressed second medium, and wherein the turbine rotor (5) and the compressor rotor (7) are directly connected to each other.
    公开号:CH715034A2
    申请号:CH5242019
    申请日:2019-04-16
    公开日:2019-11-29
    发明作者:Haag Jan-Christoph；Aurahs Lutz；Heinz Christoph；Bartholomä Klaus
    申请人:Man Energy Solutions Se；
    IPC主号:
    专利说明:

    Description: The invention relates to a turbocharger. Furthermore, the invention relates to a drive system with a fuel cell and a turbocharger.
    The basic structure of a turbocharger is known to those skilled in the art. A turbocharger has a turbine in which a first medium is expanded. Furthermore, a turbocharger has a compressor in which a second medium is compressed, using the energy obtained in the turbine when the first medium is expanded. The turbine of the turbocharger has a turbine housing and a turbine rotor. The turbocharger's compressor has a compressor housing and a compressor rotor. In turbochargers known from practice, a bearing housing is positioned between the turbine housing of the turbine and the compressor housing of the compressor, the bearing housing being connected on the one hand to the turbine housing and on the other hand to the compressor housing. A shaft is mounted in the bearing housing, via which the turbine rotor is coupled to the compressor rotor in turbochargers known from practice.
    In known from practice turbochargers, in which the turbine of the turbocharger serves to relax exhaust gas from an internal combustion engine, in particular a diesel engine or gasoline engine, is the spacing of the turbine rotor and compressor rotor via the shaft and the spacing of the compressor housing and turbine housing via the bearing housing important to prevent heat transfer from the turbine towards the compressor as much as possible. This is to prevent the second medium to be compressed in the compressor from being heated up by heat transfer or heat conduction from the turbine.
    Based on this, the present invention seeks to provide a novel turbocharger and a drive system with such a turbocharger.
    This object is achieved by a turbocharger according to claim 1.
    The turbocharger according to the invention has a turbine for expansion of a first medium, the turbine having a turbine housing and a turbine rotor. The turbocharger according to the invention also has a compressor for compressing a second medium using energy obtained in the turbine when the first medium is expanded, the compressor having a compressor housing and a compressor rotor, the temperature of the first medium to be relaxed or relaxed being lower as a temperature of the medium to be compressed or the compressed second medium, and wherein the turbine rotor and the compressor rotor are connected directly to one another. The turbine rotor and the compressor rotor are connected to one another without an intermediate shaft.
    In the turbocharger according to the invention, the turbine serves to relax a medium whose temperature level is below the temperature level in the compressor. The invention is based on the knowledge that in such a turbocharger the turbine rotor and the compressor rotor can be connected directly to one another, since in this case heat transfer or heat conduction starting from the compressor in the direction of the turbine is preferred in order to increase the efficiency of the compressor. In this case, heat coupling between the compressor and the turbine, which is not desired in turbochargers known from practice, is particularly advantageous, so that the turbine rotor and the compressor rotor are advantageously directly connected to one another without an intermediate shaft.
    Preferably, the turbine is a radial turbine with a radially flowed and axially flowed turbine rotor, the compressor being a radial compressor with an axially flowed and radially flowed compressor rotor, and wherein the turbine rotor and the compressor rotor are positioned back to back and directly with each other without an intermediate shaft are connected. In such a turbocharger with a radial turbine and radial compressor, the rotors of which are positioned back to back and coupled without a shaft, heat transfer from the compressor towards the turbine can be used particularly advantageously in order to achieve high compressor efficiency.
    Preferably, the unit consisting of turbine rotor and compressor rotor is mounted on the side. At least one first bearing is arranged downstream of the turbine rotor, as seen in the flow direction of the first medium. At least one second bearing is arranged upstream of the compressor rotor, viewed in the direction of flow of the second medium. The turbine housing and the compressor housing are connected to one another without an intermediate bearing housing. This configuration is particularly preferred in order to ensure a compact design of the turbocharger according to the invention. Since the compressor rotor and turbine rotor are positioned back to back and are directly connected to one another without an intermediate shaft, there is no bearing housing located between the turbine housing and the compressor housing. Bearings for bearing the rotors are positioned laterally, i.e. not between the compressor rotor and turbine rotor.
    The drive system is defined in claim 8.
    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:
    Fig. 1 shows a cross section through a turbocharger.
    The invention relates to a turbocharger and a drive system with a turbocharger.
    CH 715 034 A2 [0013] FIG. 1 shows a cross section through a turbocharger 1 according to the invention, the turbocharger 1 comprising a turbine and a compressor 3.
    [0014] A first medium is expanded in the turbine 2. Energy obtained in this way is used to compress a second medium in the compressor 3.
    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.
    In the preferred embodiment shown, the turbine 2 is a radial turbine, the compressor 3 is a radial compressor. The turbine rotor 5 of the turbine 2 is flowed radially by the first medium to be relaxed, the relaxed first medium flowing axially from the turbine rotor 5 of the turbine 2. Arrows I visualize the direction of flow of the first medium, in particular the radial inflow and axial outflow of the first medium in relation to the turbine rotor 5.
    The compressor rotor 7 of the radial compressor 3 is axially flowed against by the second medium to be compressed, furthermore compressed second medium flows from the compressor rotor 7 in the radial direction in the region of the compressor rotor 7. Arrows II visualize the direction of flow of the second medium in the area of the compressor 3, in particular the axial flow against the compressor rotor 7 and the radial flow of the compressed second medium from the compressor rotor 7.
    In the region of the compressor 3, the second medium to be compressed or compressed has a higher temperature level than the relaxed or relaxed first medium in the region of the turbine. A temperature of the first medium to be expanded or relaxed in the region of the turbine 2 is accordingly lower than a temperature of the second medium to be compressed or compressed in the region of the compressor 3.
    The compressor rotor 7 and the turbine rotor 5 are connected directly to one another, and without an intermediate shaft. In the preferred exemplary embodiment shown in FIG. 1, in which the turbine 2 is a radial turbine and the compressor 3 is a radial compressor, the turbine rotor 5 and the compressor rotor 7 are positioned back to back and are directly connected to one another without an intermediate shaft.
    This design of the turbocharger enables heat transfer or heat conduction starting from the compressor 3 in the direction of the turbine 2, as a result of which the compression efficiency in the region of the compressor can be increased.
    Characterized in that the turbine rotor 5 and the compressor rotor 7 are directly connected to each other without a shaft, a bearing housing between the turbine housing 2 and the compressor housing 3 is dispensed with. The preferably monolithic unit comprising the turbine rotor 5 and the compressor rotor 7 is mounted laterally via bearings 8, 9, at least one first bearing 8 being arranged downstream of the turbine rotor 5 as seen in the flow direction of the first medium to be relaxed in the region of the turbine 2, and at least one second bearing 9 is arranged upstream of the compressor rotor 7, viewed in the flow direction of the second medium to be compressed in the region of the compressor 3. The respective first bearing 8 is integrated in the turbine housing 4, whereas the respective second bearing 9 is integrated in the compressor housing 6.
    By dispensing with a separate bearing housing between the turbine housing 2 and the compressor housing 3 and by dispensing with the turbine rotor 5 and the compressor rotor 7 for a while, not only can the heat transfer from the compressor 3 in the direction of the turbine 2 be used advantageously, but can also be used the space requirement of the turbocharger 1 can be reduced. The turbocharger 1 has a high efficiency, a low weight and a compact design. Another advantage of the arrangement of turbine rotor 5 and compressor rotor 7 according to the invention is that, in practice, existing wheel side spaces on the rear sides of turbine rotor 5 and compressor rotor 7 are eliminated. As a result, the efficiency can be increased. Because of the pressure ratios on the compressor side and turbine side, an axial thrust, which acts on the unit comprising the turbine rotor 5 and the compressor rotor 7, can be minimized. In turbochargers known from practice, this axial thrust must be absorbed by a bearing, such a bearing leading to bearing losses. Such axial thrust-related bearing losses can be minimized in the turbocharger 1 according to the invention.
    The turbocharger 1 according to the invention is part of a drive system which, as the drive unit, comprises a fuel cell, in particular a hydrogen-oxygen fuel line. Exhaust gas from the fuel cell is expanded in the turbine 2 of the turbocharger 1. This exhaust gas is water vapor. This has a temperature level below the temperature level in the compressor 3. Air is compressed in the compressor 3 of the turbocharger 1 and is fed to the fuel cell process. As already stated, the design of the turbocharger 1 enables good heat conduction from the compressor 3 in the direction of the turbine 2. As a result, the compression efficiency for a drive system with such a turbocharger 1 and a fuel cell can be increased.
    Reference symbol list [0024]
    turbocharger
    CH 715 034 A2
    turbine
    compressor
    turbine housing
    turbine rotor
    compressor housing
    compressor rotor
    camp
    camp
    权利要求:
    Claims (8)
    [1]
    claims
    1. Turbocharger (1), with a turbine (2) for expanding a first medium, the turbine (2) having a turbine housing (4) and a turbine rotor (5), with a compressor (3) for compressing a second medium Utilization of energy obtained in the turbine (2) when the first medium relaxes, the compressor (3) having a compressor housing (6) and a compressor rotor (7), the temperature of the first medium to be relaxed or the relaxed first being less than one Temperature of the medium to be compressed or the compressed second medium, the turbine rotor (5) and the compressor rotor (7) being connected directly to one another.
    [2]
    2. Turbocharger according to claim 1, characterized in that the turbine (2) is a radial turbine with a radially flowed and axially flowed turbine rotor (5), the compressor (3) is a radial compressor with an axially flowed and radially flowed compressor rotor (7) , the turbine rotor (5) and the compressor rotor (7) are positioned back to back and are directly connected to one another.
    [3]
    3. Turbocharger according to claim 1 or 2, characterized in that the turbine rotor (5) and the compressor rotor (7) are connected to each other directly without an intermediate shaft.
    [4]
    4. Turbocharger according to one of claims 1 to 3, characterized in that the unit consisting of turbine rotor (5) and compressor rotor (7) is mounted laterally.
    [5]
    5. Turbocharger according to claim 4, characterized in that at least one first bearing (8), seen in the flow direction of the first medium, is arranged downstream of the turbine rotor (5), at least one second bearing (9), seen in the flow direction of the second medium, upstream of the compressor rotor ( 7) is arranged.
    [6]
    6. Turbocharger according to claim 5, characterized in that the respective first bearing (8) is integrated in the turbine housing (4), the respective second bearing (9) is integrated in the compressor housing (6).
    [7]
    7. Turbocharger according to one of claims 1 to 6, characterized in that the turbine housing (4) and the compressor housing (6) are connected to one another without an intermediate bearing housing.
    [8]
    8. Drive system with a fuel cell, a turbocharger (1) according to any one of claims 1 to 7, wherein the turbine (2) of the turbocharger relaxes as the first medium exhaust gas of the fuel cell.
    CH 715 034 A2

    类似技术:
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    同族专利:
    公开号 | 公开日
    KR20190134517A|2019-12-04|
    DE102018112443A1|2019-11-28|
    JP2019203504A|2019-11-28|
    US20200025075A1|2020-01-23|
    RU2019115644A|2020-11-23|
    CN110529253A|2019-12-03|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    DE762097C|1942-05-02|1954-05-31|Brown Ag|Exhaust gas turbocharger|
    FR1075901A|1952-04-28|1954-10-21|Rotor mounted in cantilever, for turbo-compressor|
    NL99624C|1955-08-29|
    US20040150366A1|2003-01-30|2004-08-05|Ferrall Joseph F|Turbocharged Fuel Cell Systems For Producing Electric Power|
    DE102008048126A1|2008-09-20|2010-03-25|Bosch Mahle Turbo Systems Gmbh & Co. Kg|Exhaust gas turbocharger i.e. supercharger, for use in vehicle, has rotor provided with compressor part and turbine part, where rotor is radially and/or axially mounted only at axial ends in pivotable manner|
    DE102008057729A1|2008-11-17|2010-05-27|Bosch Mahle Turbo Systems Gmbh & Co. Kg|Exhaust gas turbo-charger for internal combustion engine in motor vehicle, has rotor supported in stator via pneumatic radial bearing and axial bearing, where radial bearing is pneumatically loaded by rotor, during operation of charger|
    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    DE102018112443.0A|DE102018112443A1|2018-05-24|2018-05-24|Turbocharger and propulsion system with fuel cell and turbocharger|
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