• 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 (1) for a turbocharger for expanding a medium, with a turbine rotor (2) having moving blades (3); with a shroud (12) adjoining the rotor blades (3) radially on the outside; with an adjustable guide vanes (7) positioned upstream of the rotor blades (3) as seen in the flow direction of the medium to be expanded, have the guide apparatus (6), the guide vanes (7) being mounted in a guide ring (8) positioned upstream of the cover ring (12) ; with a diffuser (5) positioned downstream of the rotor blades (3) as seen in the flow direction of the medium to be expanded; wherein a cavity (13), which adjoins the cover ring (12) and the guide ring (8) radially on the outside, is coupled to a flow channel (16) delimited by the diffuser (5) in such a way that the cavity (13) in the from Diffuser (5) limited flow channel (16) can be vented.
    公开号:CH712547B1
    申请号:CH00615/17
    申请日:2017-05-08
    公开日:2021-02-15
    发明作者:Bartenschlager Gabriel；Donderer Michael
    申请人:Man Energy Solutions Se；
    IPC主号:
    专利说明:

    The invention relates to an axial turbine for a turbocharger and a turbocharger.
    From DE 44 26 522 A1 a fluid flow machine, namely an exhaust gas turbocharger, with a turbine and a compressor is known. The turbine, which is used to expand exhaust gas, has a turbine housing, via which exhaust gas is fed to a turbine rotor of the turbine, the turbine rotor having a plurality of rotor blades. A diffuser is connected downstream of the rotor blades of the turbine. The energy gained during the expansion of the exhaust gas in the area of the turbine is used in the area of the compressor to compress charge air.
    DE 100 16 745 B4 discloses an axial turbine of a turbocharger, in which a diffuser with adjustable guide vanes is arranged upstream of the rotor blades of the turbine rotor, viewed in the flow direction of the exhaust gas. The guide vanes of the guide apparatus are adjustable via an adjustment device and are adjustably mounted in a guide ring, which is also referred to as a guide vane carrier. Exhaust gas leakage can flow through the mounting of the guide vanes in the guide ring or guide vane carrier, which can lead to undesired thermal loading and contamination of the adjustment device of the guide apparatus 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 for a turbocharger in which leakage of the exhaust gas can be kept away, in particular from an adjustment device for the adjustable vanes of the nozzle.
    [0005] This object is achieved by an axial turbine for a turbocharger according to claim 1.
    According to the invention, a cavity that adjoins the cover ring and the guide ring radially on the outside is coupled to a flow channel delimited by the diffuser in such a way that the cavity can be vented into the flow channel delimited by the diffuser.
    In the axial turbine according to the invention, an exhaust gas leakage that flows, for example, via a leak between the guide vanes and the guide ring into a cavity adjoining the guide ring radially on the outside, can be suctioned off in a defined manner, in the area of the flow channel delimited by the diffuser , whereby it is avoided that the exhaust gas leakage gets into the area of the adjustment device for the adjustable vanes of the diffuser. This reduces the probability of failure of the adjusting device for the diffuser.
    Furthermore, the inventively effected ventilation of the radially outwardly adjoining the cover ring and the guide ring cavity in the direction of the diffuser via openings for the adjustment device, which are formed in the housing of the axial turbine, ambient air can be sucked in, via which then a cooling , for example of the guide apparatus and the associated assemblies of the adjustment device can be effected.
    According to an advantageous development of the invention, the cavity is coupled via at least one bore to the flow channel delimited by the diffuser, the cavity being ventable via the or each bore in the flow channel delimited by the diffuser. This is particularly simple in terms of construction. According to an advantageous development of the invention, the respective bore opens into a curved, contoured diffuser wall which delimits the flow channel of the diffuser radially on the outside. This enables a particularly advantageous venting of the cavity into the diffuser.
    According to an advantageous development of the invention, the respective bore opens into a portion of the radially outwardly limiting, curved contoured diffuser wall, in which a flow within the flow channel of the diffuser is turbulence-free or almost turbulence-free and / or below atmospheric pressure provides lying pressure on the diffuser wall. This also allows a particularly advantageous venting of the cavity into the flow channel of the diffuser.
    According to an advantageous development of the invention, the diffuser has an axial extension, with an axial extension of 0% a flow inlet-side end of the diffuser, which adjoins the cover ring, with an axial extension of 100% a flow outlet end of the diffuser and wherein the or each bore through which the cavity can be vented into the flow channel of the diffuser, with an axial extent between 5% and 20% of the diffuser, preferably with an axial extent between 5% and 15% of the diffuser, particularly preferably with an axial extent between 5% and 10% of the diffuser, opens into the flow channel of the diffuser, namely into the curved, contoured diffuser wall. This development of the invention is also used for particularly effective ventilation of the cavity in the flow channel of the diffuser.
    According to an advantageous development of the invention, a sealing element is positioned between the cover ring and the guide ring. The sealing element between the cover ring and the guide ring prevents further exhaust gas leakage into the cavity.
    Preferred developments of the invention emerge from the dependent claims and the following description. Embodiments of the invention are explained in more detail with reference to the drawing, without being restricted thereto. It shows: FIG. 1: a highly schematic cross-section through an axial turbine according to the invention for an axial turbocharger,
    The present invention relates to an axial turbine for a turbocharger and a turbocharger.
    Fig. 1 shows a schematic cross section through an axial turbine 1 for a turbocharger. Exhaust gas is expanded in the turbine 1, the energy obtained being used to compress charge air in the area of a compressor, not shown, of the turbocharger.
    The axial turbine 1 has a turbine rotor 2 with several blades 3. The turbine rotor 2 is also referred to as an impeller. Exhaust gas, which is expanded in the area of the turbine rotor 2 of the turbine 1, is fed to the turbine rotor 2 via an inflow housing 4, the expanded exhaust gas being discharged from the turbine rotor 2 downstream of the turbine rotor 2 via a diffuser 5.
    1 also shows a diffuser 6, which is positioned upstream of the turbine rotor 2 as seen in the flow direction of the exhaust gas. The diffuser 6 has guide vanes 7 which are adjustable. For this purpose, the guide vanes 7 are rotatably mounted in a guide ring 8, which is also referred to as a guide vane carrier, in order to adjust the guide vanes 7 by rotating them. An adjustment device 9 for the guide apparatus 6 has an adjustment mechanism 10 and an adjustment drive 11, via which the guide vanes 7 in the guide vane carrier or guide ring 8 can ultimately be rotated.
    Seen in the flow direction of the exhaust gas, downstream of the guide ring 8 is followed by a cover ring 12, which is radially outwardly adjacent to the blades 3 of the turbine rotor 2, and which, together with the guide ring 8, delimits a flow channel for the exhaust gas from the axial turbine 1 radially on the outside in sections .
    1 also shows a cavity 13 which is delimited radially on the outside by the housing 4 of the axial turbine 1 and radially on the inside at least in sections by the cover ring 12 and guide ring 8. The adjusting mechanism 10 of the adjusting device 9 extends into this cavity 13 from outside the housing 4, the adjusting drive 11 preferably being arranged outside the housing 4. The adjustment mechanism 10 can be inserted into the cavity 13 from outside the housing 4 via a corresponding opening 14 in the housing 4.
    For the purposes of the present invention, the cavity 13, which is radially outwardly connected to the cover ring 12 and to the guide ring 8, preferably via at least one bore 15 in the diffuser 5 with a flow channel 16 defined by the diffuser 5 for the exhaust gas coupled that the cavity 13 can preferably be vented via the or each bore 15 into the flow channel 16 delimited by the diffuser 5. The venting takes place via the pressure gradient between the pressure in the cavity 13 and the pressure that prevails at the point of the diffuser 5 in which the or each bore 15 opens into the flow channel 16 of the diffuser 5.
    Although the coupling of the cavity 13 to the flow channel 16 of the diffuser 5 via the bores 15 is preferred, the coupling of the cavity 13 to the flow channel 16 can also be done in other ways, for example by another one corresponding to the channel between the cavity 13 and flow channel 16 defining structural elements such as tubular elements.
    By mounting the adjustable guide vanes 7 in the guide ring 8, an exhaust gas leakage can get into the cavity 13, which is then derived from the cavity 13 into the flow channel 16 of the diffuser 5 via the or each bore 15 in a defined manner. There is no risk of the adjustment mechanism 10 of the adjustment device 9 being exposed to inadmissible heating and contamination due to such an exhaust gas leak. Rather, ambient air can be sucked in through the or each opening 14 of the housing 4, through which the adjustment mechanism 10 is guided from outside the housing 4 into the cavity 13, for cooling, in particular, the adjustment mechanism 10 and the guide ring 8 of the guide apparatus 6.
    The diffuser 5 has a wall 17 which ultimately delimits the flow channel 16 of the diffuser 5. This wall 17 of the diffuser 5 has a curved contour, the diameter of which widens when viewed in the direction of flow of the expanded exhaust gas.
    The diffuser 5 has an axial extent, with an axial extent of 0% a flow inlet-side end of the diffuser 5 or the flow channel 16 of the diffuser 5, which adjoins the cover ring 12, and with an axial extent of 100% an end of the diffuser 5 or of the flow channel 16 of the diffuser 5 on the flow outlet side. Starting from the flow inlet end in the direction of the flow outlet end of the diffuser 5, i.e. starting from the axial extension of 0% in the direction of the axial extension of 100%, the diameter of the diffuser wall 17 delimiting the flow channel 16 on the outside expands.
    The or each bore 15 through which the cavity 13 can be vented into the flow channel 16 of the diffuser 5, opens at a portion of the curved diffuser wall 17 in the flow channel 16, in which the flow within the flow channel 16 of the diffuser 5 is almost is turbulence-free and has a pressure below atmospheric pressure in the area of the diffuser wall 17.
    Based on the axial extent of the diffuser 5 or the flow channel 16 of the diffuser 5, the or each bore 15 opens with an axial extent between 5% and 20%, preferably with an axial extent between 5% and 15%, particularly preferably with an axial extent between 5% and 10%, into the flow channel 16 of the diffuser 5. This allows the cavity 13 to be vented into the flow channel 16 of the diffuser 5 in a particularly advantageous manner.
    It can be seen from FIG. 1 that a sealing element 18 is positioned between the cover ring 12 and the guide ring 8, which prevents leakage into the cavity 13 via a gap between the guide ring 8 and the cover ring 12. If, however, a defined exhaust gas leak occurs via this sealing element 18, this can also be vented via the or each bore 15 in the flow channel 16 of the diffuser 5.
    The axial turbine 1 allows defined venting of the cavity 13 adjoining the cover ring 12 and the guide ring 8 on the outside into the flow channel 16 of the diffuser 5. An exhaust gas leak that flows into this cavity 13 can thus be discharged in a defined manner. In this way, in particular, impermissible heating or thermal loading of the adjustment device 9 of the adjustable guide apparatus 6 can be avoided. The failure safety of the axial turbine 1 is increased as a result.
    List of reference symbols
    1 axial turbine 2 turbine rotor 3 rotor blade 4 turbine housing 5 diffuser 6 diffuser 7 guide vane 8 guide ring 9 adjustment device 10 adjustment mechanism 11 adjustment drive 12 cover ring 13 cavity 14 recess 15 bore 16 flow channel 17 diffuser wall 18 sealing element
    权利要求:
    Claims (9)
    [1]
    1. Axial turbine (1) for a turbocharger for expanding a medium, witha turbine rotor (2) having moving blades (3);a shroud (12) adjoining the rotor blades (3) radially on the outside;a diffuser (6) having adjustable guide vanes (7) positioned upstream of the rotor blades (3) as seen in the flow direction of the medium to be expanded, the guide vanes (7) being mounted in a guide ring (8) positioned upstream of the cover ring (12);a diffuser (5) positioned downstream of the rotor blades (3) as seen in the flow direction of the medium to be expanded;characterized in thata cavity (13), which adjoins the cover ring (12) and the guide ring (8) radially on the outside, is coupled to a flow channel (16) delimited by the diffuser (5) in such a way that the cavity (13) enters the area from the diffuser (5) limited flow channel (16) can be vented.
    [2]
    2. Axial turbine according to Claim 1, characterized in that the cavity (13) is coupled via at least one bore (15) to the flow channel (16) delimited by the diffuser (5), the cavity (13) via the or each bore (15 ) can be vented into the flow channel (16) delimited by the diffuser (5).
    [3]
    3. Axial turbine according to Claim 2, characterized in that the respective bore (15) opens into a diffuser wall (17) which is radially outwardly delimiting the flow channel (16) of the diffuser (5) and is curved in the flow direction.
    [4]
    4. Axial turbine according to claim 3, characterized in that the respective bore (15) opens into a section of the curved, contoured diffuser wall (17) which delimits the flow channel (16) of the diffuser radially on the outside and in which a flow within the flow channel (16) of the Diffuser provides a pressure below atmospheric pressure on the diffuser wall (17).
    [5]
    5. Axial turbine according to one of Claims 2 to 4, characterized in that the diffuser (5) has an axial extension, an end of the diffuser (5) on the flow inlet side, which adjoins the cover ring (12) being located at an axial extension of 0%, with an axial extension of 100% an end of the diffuser (5) on the flow outlet side and the or each bore (15) opening into the flow channel (16) of the diffuser (5) with an axial extension of between 5% and 20%.
    [6]
    6. Axial turbine according to claim 5, characterized in that the or each bore (15) opens into the flow channel (16) of the diffuser (5) with an axial extension between 5% and 15%.
    [7]
    7. Axial turbine according to claim 6, characterized in that the or each bore (15) opens into the flow channel (16) of the diffuser (5) with an axial extent between 5% and 10%.
    [8]
    8. Axial turbine according to one of claims 1 to 7, characterized in that a sealing element (18) is positioned between the cover ring (12) and the guide ring (8).
    [9]
    9. Turbocharger, with a turbine for the expansion of exhaust gas and for generating energy in the expansion of exhaust gas, and with a compressor for compressing charge air using the energy obtained in the turbine, characterized in that the turbine as an axial turbine (1) according to one of claims 1 to 8 is formed.
    类似技术:
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    同族专利:
    公开号 | 公开日
    JP2017219039A|2017-12-14|
    CH712547A2|2017-12-15|
    CN107461226A|2017-12-12|
    KR20170137638A|2017-12-13|
    DE102016110269A1|2017-12-07|
    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|
    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|
    DE102006039064B4|2006-08-19|2020-06-25|Man Energy Solutions Se|Exhaust gas turbocharger for an internal combustion engine|
    EP2112332B1|2008-04-23|2012-08-15|ABB Turbo Systems AG|Supporting ring for a guide vane assembly with an air-sealed channel|
    CN101265814A|2008-04-30|2008-09-17|冀江|Combined turbine expansion machine|
    EP3068977B1|2013-11-14|2019-07-10|United Technologies Corporation|Gas turbine vane assembly comprising a rotatable vane with protrusions on the pressure or suction side|CN109779741B|2019-01-23|2020-05-19|宁波天阁汽车零部件有限公司|Automobile-used turbo charger|
    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
    DE102016110269.5A|DE102016110269A1|2016-06-03|2016-06-03|Axial turbine of a turbocharger and turbocharger|
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