• 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:
    Axial turbine for a turbocharger for expanding a medium, with a turbine rotor having rotating blades (7); with a guide device (6) having adjustable guide vanes (11) positioned upstream of the rotor blades (7) as seen in the direction of flow of the medium to be expanded, each guide vane (11) having a guide vane blade (12), a guide vane turntable (14) and one in a guide ring (15) has mounted guide vane journals (13); with an inflow housing (3) positioned upstream of the diffuser (6), viewed in the direction of flow of the medium to be expanded, via which the medium to be decompressed can be fed to the guide vanes (11) of the diffuser (6). At least one sealing air bore (18) is made in the inflow housing (3). A circumferential sealing air groove (19) is made in the guide ring (15). The or each sealing air bore (18) made in the inflow housing (3) extends through the inflow housing (3) and opens into the sealing air groove (19) made in the guide ring (15), with a sealing air pressure in the area of one of the sealing air groove during operation (19) from a separating line that can be acted upon by sealing air between the guide vane turntable (14) of the respective guide vane (11) and the guide ring (15) is greater than an exhaust gas pressure in the area of this parting line.
    公开号:CH712811B1
    申请号:CH00893/17
    申请日:2017-07-10
    公开日:2021-08-16
    发明作者:Donderer Michael
    申请人:Man Energy Solutions Se；
    IPC主号:
    专利说明:

    The invention relates to an axial turbine of a turbocharger and a turbocharger.
    From DE 4426522A1 a fluid flow machine, namely an exhaust gas turbocharger, with a turbine and a compressor is known. The turbine of the exhaust gas turbocharger, which is used to relax exhaust gas, has a turbine inflow housing, via which exhaust gas is fed to a turbine rotor of the turbine, the turbine rotor having a plurality of rotor blades. A turbine outflow housing with a diffuser is connected downstream of the rotor blades of the turbine. Energy gained when the exhaust gas is expanded in the area of the turbine of the exhaust gas turbocharger is used in the area of the compressor of the exhaust gas turbocharger to compress charge air.
    DE 10016745B4 discloses an axial turbine of a turbocharger, in which, viewed in the flow direction of the exhaust gas, a diffuser with adjustable guide vanes is arranged upstream of the rotor blades of the turbine rotor. The guide vanes of the nozzle have a guide vane blade, a guide vane turntable and a guide vane pin. The guide vanes can be adjusted via an adjustment device and are adjustably mounted in a guide ring, which is also referred to as a guide vane carrier. Bearing points for the guide vanes are formed between the guide vane journal of the respective guide vane and the guide ring. An exhaust gas leakage can flow into the area of the guide vane bearing points via a separating joint between the guide vane turntable of the respective guide vane and the guide ring, which can lead to undesired deposits in the area of the guide vane support and thus cause the adjustment device of the guide apparatus to fail.
    Proceeding from this, the present invention seeks to provide a novel axial turbine of a turbocharger in which leakage of the exhaust gas can be kept away from bearing points of the adjustable vanes of the diffuser.
    This object is achieved by an axial turbine for a turbocharger according to claim 1. At least one sealing air hole is made in the inflow housing of the turbine. A circumferential sealing air groove is made in the guide ring. The or each sealing air hole made in the inflow housing extends through the inflow housing and opens into the sealing air groove made in the guide ring, with a sealing air pressure in the area of a separating joint between the guide vane turntable of the respective guide vane and the guide ring, which can be acted upon by the sealing air groove, is greater than a Exhaust pressure is in the area of this parting line. The sealing air, which can be introduced into the area of the sealing air groove of the guide ring via the or each sealing air hole, can prevent exhaust gas leakage via the joint between the guide vane turntable of the respective guide vane and the guide ring, so that exhaust gas leakage can be kept away from the bearing points of the guide vanes . In this way it can be prevented that undesired deposits form in the area of the bearing points of the guide vanes. The risk of failure of the adjusting device of the diffuser is reduced as a result.
    According to an advantageous development of the invention, a bearing surface of the respective guide vane formed between the guide ring and the guide vane pin of each guide vane can be acted upon with sealing air from the sealing air groove. The application of sealing air to the bearing points is also advantageous, in particular for cooling the bearing points of the guide vanes. The sealing air groove acts on the separating joints and the bearing points with sealing air, preferably via openings in the guide ring.
    According to an advantageous development of the invention, sealing elements for sealing the air barrier groove are arranged between the guide ring and the inflow housing. In this way, a sufficiently high sealing air pressure can be maintained in the area of the sealing air groove.
    According to an advantageous development of the invention, the air barrier bores are inclined with respect to the axial direction of the axial turbine and with respect to the radial direction of the axial turbine. This allows a particularly advantageous structural design of the turbine inflow housing.
    The turbocharger according to the invention is defined in claim 8.
    Preferred developments of the invention emerge 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 thereto. It shows: FIG. 1: a section from a turbocharger in the area of an axial turbine; FIG. 2 shows the detail II of FIG. 1; FIG. 3 shows a section from the detail of FIG. 2; FIG. 4 shows the detail from FIG. 3 in another perspective view; FIG. 5 shows the detail of FIGS. 3, 4 in a further perspective view; and FIG. 6 shows the detail VI of FIG. 5,
    The present invention relates to an axial turbine for a turbocharger and a turbocharger.
    1 shows a section from a turbocharger 1 in the area of an axial turbine 2 of the turbocharger. A turbine inflow housing 3, a turbine outflow housing 4 with a diffuser 22, a turbine rotor 5 and a diffuser 6 are shown of the axial turbine 2. Exhaust gas, which is to be expanded in the axial turbine 2 of the turbocharger 1, is fed to the axial turbine 2, namely the turbine rotor 5, via the turbine inflow housing 3, with the diffuser 6 being arranged upstream of the turbine rotor 5 and downstream of the inflow housing 3 as seen in the flow direction of the exhaust gas.
    The turbine rotor 5 comprises a plurality of rotor blades 7 which rotate together with the turbine rotor 5. Exhaust gas flowing through the axial turbine 2, namely the turbine rotor 5, is expanded in the area of the turbine rotor 5, the energy obtained in this case being used to drive a compressor rotor (not shown) of a compressor (not shown) of the exhaust gas turbocharger 1, which is coupled to the turbine rotor 5 via a shaft 8 is. A cover ring 9, which is connected to the turbine outflow housing 4 via fastening elements 10, adjoins the rotor blades 7 of the turbine rotor 5 radially on the outside.
    As already stated, upstream of the turbine rotor 5 and thus upstream of the blades 7 of the turbine rotor 5, the diffuser 6 is positioned, so that exhaust gas, which is guided via the turbine inflow housing 3 in the direction of the turbine rotor 5, first flows through the diffuser 6 before it then flows over the rotor blades 7des Turbine rotor 5 is guided. The guide vane 6 has guide vanes 11, each guide vane 11 including a guide vane blade 12, a guide vane pin 13 and a guide vane turntable 14.
    The guide vanes 11 are rotatably mounted via their guide vane pins 13 in a guide ring 15, which is referred to as a guide vane carrier, in order to adjust the diffuser 6 via the rotation of the guide vanes 11.
    The guide vanes 11 of the guide apparatus 6 in the guide ring 15 can be rotated via an adjusting device, not shown in detail, for the diffuser 6, which typically has an adjustment mechanism and an adjustment drive.
    Between the guide vane pins 13 of the guide vanes 11 and the guide ring 15, bearing points 16 for the guide vanes 11 of the adjustable guide apparatus 6 are accordingly formed.
    Between the guide vane turntable 14 of the guide vanes 11 of the guide apparatus 6 and the guide ring 15, parting lines 17 are formed. According to the prior art, an exhaust gas leak can flow through these separating joints 17. In known axial turbines, this exhaust gas leakage can get into the area of the bearing points 16 of the guide vanes 11, which are formed between the guide ring 15 and the guide vane journals 13 of the guide vanes 11, and thus cause deposits in the area of the bearing points 16. This is a disadvantage.
    In order to avoid such deposits in the area of the bearing points 16 of the guide vanes 11, at least one sealing air bore 18 is made in the inflow housing 3. A plurality of such sealing air bores 18 are preferably made in the turbine inflow housing 3 over the circumference. A circumferential sealing air groove 19 is made in the guide ring 15. The or each sealing air bore 18 made in the inflow housing 3 extends through the inflow housing 3 and opens into the sealing air groove 19 made in the guide ring 15 The sealing air pressure prevailing in the sealing air groove 19, the parting line 17 between the guide vane turntable 14 of the respective guide vane 11 and the guide ring 15 can be acted upon with sealing air, the sealing air pressure in the sealing air groove 19 and in the area of the respective parting line 17 being greater than an exhaust gas pressure in the area of the parting lines 17.
    An exhaust gas leakage, which according to the prior art can therefore flow through the parting lines 17 between the guide vane turntables 14 of the guide vanes 11 and the guide ring 15, is prevented by applying sealing air to the parting lines 17. Accordingly, no exhaust gas can get into the area of the bearing points 16 between the guide ring 15 and the guide vane journals 13 of the guide vanes 11.
    Starting from the blocking air groove 19, the bearing points 16 between the guide vane pins 13 of the guide vanes 11 and the guide ring 15 can also be acted upon with sealing air, whereby the same can be cooled.
    It is therefore within the meaning of the invention that at least one sealing air bore 18, preferably a plurality of sealing air bores 18, are introduced into the turbine inflow housing 3. The or each sealing air bore 18 communicates with a circumferential sealing air groove 19 made in the guide ring 15, from which sealing air can be applied to the parting lines 17 between the guide vane turntables 14 of the guide vanes 11 and the guide ring 17 and, on the other hand, the bearing points 16 between the guide vane pins 13 of the guide vanes 11 and the guide ring 15.
    This takes place via the openings 21 in the guide ring 15, which couple the sealing air groove 19 on the pressure side to the parting lines 17 between the guide vane turntables 14 of the guide vanes 11 and the guide ring 15 and to the bearing points 16 between the guide vane pins 13 of the guide vanes 11 and the guide ring 15. In this way, on the one hand, it can be prevented that exhaust gas leakage reaches the area of the bearing points 16, and on the other hand, the bearing points 16 can be cooled. A failure of the mounting of the adjustable guide vanes 11 in the guide ring 15 can thus be counteracted.
    As can best be seen from FIG. 6, receiving grooves 20 for sealing elements (not shown) are made in the guide ring 15 adjacent to the air barrier groove 19 on a side facing the turbine inflow housing 3. The sealing air groove 19 can be sealed by means of these sealing elements, which are positioned in the receiving grooves 20, in order to prevent sealing air leakage via a separating joint between the inflow housing 3 and the guide ring 15.
    The or each sealing air bore 18 is preferably inclined both with respect to the axial direction of the axial turbine 2 and with respect to the radial direction of the axial turbine 2. The respective sealing air bore 18 preferably forms an angle between 15 ° and 75 °, preferably an angle between 30 ° and 60 °, with the axial direction of the axial turbine 2. In this way, the air barrier bores 18 can be guided particularly preferably in the inflow housing 3bis into the area of the air barrier groove 19 of the guide ring 15.
    The sealing air can be charge air of an already existing charge air system or compressed air from a separate compressed air system.
    List of reference symbols
    1 turbocharger 2 axial turbine 3 inflow housing 4 outflow housing 5 turbine rotor 6 diffuser 7 rotor blade 8 shaft 9 cover ring 10 fastening element 11 guide vane 12 guide vane blade 13 guide vane pin 14 guide vane turntable 15 guide ring 16 bearing point 17 separation joint 18 sealing air bore 19 sealing air groove 20 diffuser 21 breakthrough
    权利要求:
    Claims (8)
    [1]
    1. Axial turbine (2) for a turbocharger to relax a medium, witha turbine rotor (5) having moving blades (7);a diffuser (6) having adjustable guide vanes (11) positioned upstream of the rotor blades (7) as seen in the flow direction of the medium to be expanded, each guide vane (11) having a guide vane blade (12), a guide vane turntable (14) and a guide vane (14) in a guide ring ( 15) has mounted guide vane journals (13);an inflow housing (3) positioned upstream of the diffuser (6), viewed in the direction of flow of the medium to be expanded, via which the medium to be decompressed can be fed to the guide vanes (11) of the diffuser (6);characterized in thatat least one sealing air bore (18) is made in the inflow housing (3);a circumferential sealing air groove (19) is made in the guide ring (15); the or each sealing air bore (18) made in the inflow housing (3) extends through the inflow housing (3) and opens into the sealing air groove (19) made in the guide ring (15), with a sealing air pressure in the area of one of the sealing air groove during operation (19) from separating line (17) which can be acted upon by sealing air between the guide vane turntable (14) of the respective guide vane (11) and the guide ring (15) is greater than an exhaust gas pressure in the area of this parting line (17).
    [2]
    2. Axial turbine according to claim 1, characterized in that between the guide ring (15) and the guide vane pin (13) of the respective guide vane (11) a respective bearing point (16) is formed, which can be acted upon with sealing air from the sealing air groove (19).
    [3]
    3. Axial turbine according to claim 1 or 2, characterized in that the sealing air groove (19) communicates with the parting line (17) and the bearing points (16) via openings (21) in the guide ring (15) and acts on the same with sealing air during operation.
    [4]
    4. Axial turbine according to one of claims 1 to 3, characterized in that sealing elements for sealing the air barrier groove (19) are arranged between the guide ring (15) and the inflow housing (3).
    [5]
    5. Axial turbine according to Claim 4, characterized in that the guide ring (15) has receiving grooves (20) for the sealing elements adjacent to the sealing air groove (19).
    [6]
    6. Axial turbine according to one of claims 1 to 5, characterized in that the or each sealing air bore (18) is inclined relative to the axial direction of the axial turbine and relative to the radial direction of the axial turbine.
    [7]
    7. Axial turbine according to claim 6, characterized in that the or each sealing air bore (18) encloses an angle between 15 ° and 75 °, in particular between 30 ° and 60 °, with the axial direction of the axial turbine.
    [8]
    8. Turbocharger (1), with an axial turbine (2) for the expansion of exhaust gas and for generating energy during the expansion of exhaust gas, and with a compressor for compressing charge air using the energy obtained in the axial turbine (2), characterized that the axial turbine (2) is designed according to one of claims 1 to 7.
    类似技术:
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    同族专利:
    公开号 | 公开日
    CN107676138A|2018-02-09|
    CH712811A2|2018-02-15|
    JP2018021554A|2018-02-08|
    KR20180015077A|2018-02-12|
    DE102016114253A1|2018-02-08|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    DE4426522A1|1994-07-27|1996-02-01|Man B & W Diesel Ag|Gas turbine flow machine|
    DE10013335A1|2000-03-17|2001-09-20|Abb Turbo Systems Ag Baden|Conducting apparatus is for position alteration of conducting blades in turbocharger exhaust gas turbine has blades arranged axially symmetrically to the turbine axis in an exhaust gas flow channel and can be pivoted by a pivot device|
    DE10016745B4|2000-04-04|2005-05-19|Man B & W Diesel Ag|Axial flow machine with a nozzle comprising a number of adjustable guide vanes|
    EP1895106A1|2006-08-28|2008-03-05|ABB Turbo Systems AG|Sealing of variable guide vanes|
    EP2112332B1|2008-04-23|2012-08-15|ABB Turbo Systems AG|Supporting ring for a guide vane assembly with an air-sealed channel|
    WO2014033878A1|2012-08-30|2014-03-06|三菱重工業株式会社|Centrifugal compressor|
    KR20170058386A|2014-09-23|2017-05-26|보르그워너 인코퍼레이티드|Turbocharger with integrated actuator|
    法律状态:
    2018-07-31| PFA| Name/firm changed|Owner name: MAN ENERGY SOLUTIONS SE, DE Free format text: FORMER OWNER: MAN DIESEL AND TURBO SE, DE |
    优先权:
    申请号 | 申请日 | 专利标题
    DE102016114253.0A|DE102016114253A1|2016-08-02|2016-08-02|Axial turbine of a turbocharger and turbocharger|
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