• 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 (10) with a rotor-side turbine runner (11) which has rotor blades (12); with a stator-side turbine housing (13); with a cover ring (20) which is non-positively fastened to the turbine housing (13) and which adjoins the rotor blades (12) radially on the outside and defines a radial gap (22) together with the rotor blades (12); and with a centering ring (23) which is positively connected to the cover ring (20) in such a way that a force fit between the centering ring (23) and the cover ring (20) is greater than a force fit between the cover ring (20) and the turbine housing ( 13), the centering ring (23) protruding into a groove (25) of the turbine housing (13) at least in sections such that in a cold state of the axial turbine the centering ring (23) over a radially inner surface (26) of the same on a radially inner surface (27) of the groove (25) is centered, whereas in a warm state of the axial turbine the centering ring (23) is centered on a radially outer surface (28) of the same on a radially outer surface (29) of the groove (25).
    公开号:CH712548B1
    申请号:CH00616/17
    申请日:2017-05-08
    公开日:2021-02-15
    发明作者:Löwlein Oswald
    申请人:Man Energy Solutions Se；
    IPC主号:
    专利说明:

    The invention relates to an axial turbine. The invention also relates to an exhaust gas turbocharger with such an axial turbine.
    Axial turbines known from practice have a rotor-side turbine impeller with rotor blades and a stator-side turbine housing. Furthermore, it is already known from practice to fasten a cover ring to the turbine housing in a non-positive manner using fastening screws, the cover ring adjoining the rotor blades radially on the outside and defining a radial gap together with the rotor blades.
    From DE 10 2009 045 167 A1 an axial turbine of an exhaust gas turbocharger with a turbine housing, a turbine impeller having rotating blades and a cover ring attached to the turbine housing is known.
    In operation, the turbine housing and the cover ring are subject to uneven heating or heating, which changes the radial gap between the rotor blades and the cover ring. A changing radial gap between the shroud and the rotor blades can cause the rotor blades of the turbine impeller to rub against the shroud. This is a disadvantage.
    [0005] There is therefore a need for an axial turbine in which the radial gap between the rotor blades and the shroud is subject to less change during operation.
    Proceeding from this, the present invention is based on the object of creating a novel axial turbine and an exhaust gas turbocharger with such an axial turbine.
    [0007] This object is achieved by an axial turbine according to claim 1. The axial turbine according to the invention comprises a centering ring for the cover ring, the centering ring being non-positively connected to the cover ring such that a force fit between the centering ring and the cover ring is greater than a force fit between the cover ring and the turbine housing. The centering ring protrudes at least in sections into a groove in the turbine housing, in such a way that in a cold state of the axial turbine the centering ring is centered over a radially inner surface of the same on a radially inner surface of the groove of the turbine housing, whereas in a warm state of the axial turbine the centering ring is centered over a radially outer surface thereof on a radially outer surface of the groove of the turbine housing.
    The axial turbine according to the invention comprises the centering ring, with the centering ring and cover ring as well as the cover ring and turbine housing each being fastened to one another in a non-positive manner. Due to the size ratio of the frictional connection between the centering ring and the cover ring as well as the frictional connection between the cover ring and the turbine housing, thermally induced sliding of the cover ring on the turbine housing is permitted when the axial turbine is heated up and cooled down, but no corresponding relative movement between the cover ring and centering ring. The radially inner surface and the radially outer surface of the groove in the turbine housing, into which the centering ring protrudes at least in sections, limit a thermally induced relative movement between the cover ring and the turbine housing and thus limit the change in the radial gap between the rotor blades and the cover ring. The risk of the blades of the turbine rotor rubbing against the shroud can thus be reduced.
    According to an advantageous development, the cover ring and the centering ring are non-positively attached to one another via first fastening screws and the cover ring and the turbine housing via second fastening screws. The size ratio between the frictional connection between the centering ring and the cover ring and the frictional connection between the cover ring and the turbine housing is preferably determined by the number and / or size and / or tightening torque of the first and second fastening screws. This allows the size ratio of the frictional connection between the centering ring and the cover ring and the frictional connection between the cover ring and the turbine ring to be set particularly easily and advantageously in order to allow a thermally induced relative movement between the cover ring and the turbine housing, but a corresponding relative movement between the cover ring and Avoid centering ring.
    According to an advantageous development, the size ratio between the frictional connection between the centering ring and the cover ring and the frictional connection between the cover ring and the turbine housing is additionally determined by the roughness of the friction surfaces between the centering ring and the cover ring and between the cover ring and the turbine housing. This also allows the size ratio between the frictional connection between the turbine ring and the cover ring and the frictional connection between the cover ring and the turbine housing to be set in a simple and advantageous manner.
    According to an advantageous development, the turbine housing has, based on the rotor blades, an inflow-side housing section, an inflow-side nozzle ring and an outflow-side housing section, the cover ring being fastened to the downstream housing section via the second fastening screws and the nozzle ring also clamping the cover ring on the turbine housing. When the nozzle ring clamps the cover ring on the turbine housing and this provides part of the frictional connection between cover ring and turbine housing, the number of second fastening screws between cover ring and turbine housing can be reduced.
    As a variant, the complete takeover of the frictional connection via the nozzle ring is also possible. In this variant, the fastening screw is designed in such a way that it is screwed onto the base or onto a collar and a gap is created between the screw head and the support of the cover ring. The fastening screw is "free". No further measures, as described e.g. with expansion sleeves, are necessary. The fastening screws then only serve as an assembly lock so that the cover ring with centering ring does not fall out during assembly / disassembly and as a protection against rotation.
    The exhaust gas turbocharger is defined in claim 12.
    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 first axial section through an axial turbine according to the invention; 2 shows a second axial section through the axial turbine according to the invention; 3 shows a third axial section through the axial turbine according to the invention; 4 shows a detail of the axial turbine according to the invention in the axial direction of view; Fig. 5 shows section V-V of Fig. 4; and FIG. 6 shows section VI-VI from FIG. 4.
    [0015] The invention relates to an axial turbine, in particular an axial turbine for an exhaust gas turbocharger. 1 and 3 show three different axial sections, offset from one another in the circumferential direction, through an axial turbine 10, a turbine rotor 11 with rotor blades 12 of the axial turbine 10 being shown. 1 to 3 show a turbine housing 13, with several sections of the turbine housing 13 being shown in FIGS. 1 to 3, namely a housing section 14 on the inflow side with respect to the rotor blades 12, a nozzle ring 15 on the inflow side, and a housing section 16 on the outflow side 1 to 3, the upstream nozzle ring 15 is mounted on the upstream housing section 14 via a clamping ring 17 and fastening screws 18, a rotation lock 19 preventing relative rotation between the upstream nozzle ring 15 and the upstream housing section 14.
    Fig. 1 also shows a stator-side cover ring 20. The cover ring 20 is attached to the turbine housing 13, namely in Fig. 1 to 3 on the downstream housing portion 16 of the turbine housing 13, namely via fastening screws 21 visible in Fig. 3. These fastening screws 21 serve for the frictional fastening of the cover ring 20 on the housing section 16 of the turbine housing 13.
    The cover ring 12 is positioned radially on the outside adjacent to the rotor blades 12 of the turbine rotor 11 and, together with the rotor blades 12 of the turbine rotor 11, delimits a radial gap 22.
    The axial turbine 10 according to the invention has a centering ring 23 for the cover ring 20, which is non-positively mounted on the cover ring 20, namely via fastening screws 24 visible in FIG. 2. A force fit between the centering ring 23 and the cover ring 20 is greater as a frictional connection between the cover ring 20 and the turbine housing 13, so that a temperature-related relative movement between the cover ring 20 and the turbine housing 13 is permitted, but a corresponding, thermally induced relative movement between the centering ring 23 and the cover ring 20 is prevented.
    The centering ring 23 connected to the cover ring 20 protrudes into a groove 25 of the turbine housing 13, namely the housing section 16 of the same, in sections, in such a way that the centering ring 23 over a radially inner surface 26 in a cold state of the axial turbine 10 is centered on a radially inner surface 27 of the groove 25, whereas in a hot state of the axial turbine the centering ring 23 is centered via a radially outer surface 28 on a radially outer surface 29 of the groove 25. The cold state of the axial turbine should be understood to mean a state in which the axial turbine has cooled down, whereas the warm state of the axial turbine 10 should be understood to mean a state in which it is heated up during operation.
    The radial surfaces 27, 29 of the groove 25 of the housing section 16 of the turbine housing 13 therefore limit the relative movement of the cover ring 20 relative to the turbine housing 13, namely through the interaction of the corresponding radial surfaces 26, 28 of the centering ring 23 attached to the cover ring 20 with the corresponding Radial surfaces 27, 29 of the groove 25 of the turbine housing 13.
    As already stated, the cover ring 20 and the centering ring 23 are fastened to one another via fastening screws 24 (see FIG. 2), these fastening screws 24 being referred to below as the first fastening screws. These first fastening screws 24 extend through a corresponding through hole 30 in the cover ring 20 and engage in a threaded bore 31 of the centering ring 23.
    The cover ring 20 is attached to the housing section 16 of the turbine housing 13 via the fastening screws 21 (see FIG. 3), these fastening screws 21 being referred to below as second fastening screws. These second fastening screws 21 extend through through holes 32, 33 of the cover ring 20 and centering ring 23 and engage in a threaded bore 34 of the turbine housing 13.
    As already stated, the frictional connection between the cover ring and the centering ring 23 is greater than the frictional connection between the cover ring and the turbine housing 13.
    The size ratio between the frictional connection between the centering ring 23 and the cover ring 20 and the frictional connection between the cover ring 20 and the turbine housing 13 is determined in particular by the number and / or the size and / or the tightening torque of the fastening screws 21, 24.
    In the embodiment shown in Fig. 4, the number of first fastening screws 24, which are used to attach the cover ring 20 and centering ring 23, twice as large as the number of second fastening screws 21, which are used to attach the cover ring 20 to the housing portion 16 of the Turbine housing 13 are used. Although the diameter of the fastening screws 21, 24 is identical in FIG. 4, it is also possible to increase the diameter of the first fastening screws 24 compared to the diameter of the second fastening screws 21.
    Due to the fact that the second fastening screws 21 extend into the turbine housing 13, the length of the second fastening screws 21 is greater than the length of the first fastening screws 24.
    Furthermore, the tightening torque of the first fastening screws 24 is preferably greater than the tightening torque of the second fastening screws 21, preferably by at least 1.3 times, particularly preferably by at least 1.5 times, most preferably by at least 1.8 times.
    As already stated, the second fastening screws 21 are used to fasten the cover ring 20 on the turbine housing 13. Since a thermally induced relative movement between the cover ring 20 and the turbine housing 13 is permitted during operation of the axial turbine 10, the second fastening screws 21 are subject to a Deflection. So that they can safely absorb the corresponding bending forces, the second fastening screws 21 have an adapted length, the fastening screws 21 being supported on the cover ring 20 via expansion sleeves 35 in the exemplary embodiments shown. However, these expansion sleeves 35 are optional assemblies. In order to be able to accommodate a corresponding length of the second fastening screws 21, the threaded bores 34 of the turbine housing 13 can also be made correspondingly longer.
    The size ratio between the frictional connection between the centering ring and the cover ring 20 and the frictional connection between the cover ring 20 and the turbine housing 13 can also be set via a roughness of friction surfaces on the one hand between the centering ring 23 and the cover ring 20 and on the other hand between the cover ring 20 and the turbine housing 13 . A greater roughness is preferably selected for the friction surfaces between cover ring 20 and centering ring 23 than for the friction surfaces between cover ring 20 and turbine housing 13.
    In the embodiment shown in Fig. 1 to 3, an axial gap 36 is formed between the nozzle ring 13 and the cover ring 20. In this case, the frictional connection between the cover ring 20 and turbine housing 13 is set exclusively via the first fastening screws 21. In contrast to this, it is also possible for the nozzle ring 15 to clamp the cover ring 20 in the turbine housing 13, in which case there is no axial gap 36 between the cover ring 20 and the nozzle ring 15. In this case, part of the frictional connection between cover ring 20 and turbine housing 13 is provided by the clamping force exerted on cover ring 20 by nozzle ring 15, so that the number of second fastening screws 21 can then be reduced. In this case too, the frictional connection between cover ring 20 and turbine housing 13, which is then determined by the clamping force of nozzle ring 15 and the screw forces of second fastening screws 21, is smaller than the frictional connection between cover ring 20 and centering ring 23.
    With the invention, the thermally induced relative movement between the cover ring 20 and the turbine housing 13 is limited. The cover ring 20 is centered on the turbine housing 13 via the centering ring 23. The radial gap 22 between the rotor blades 12 and the shroud 20 can thus be set more precisely during operation even with different thermal expansion of the assemblies involved. A rubbing of the rotor blades 12 into the shroud 20 can be reduced or even completely reduced compared to the prior art.
    The axial turbine according to the invention is preferably part of an exhaust gas turbocharger which comprises a compressor and the axial turbine.
    Due to the tolerance, alignment and misalignment of the various housing and rotor parts, there may be an uneven gap between the turbine blade and the shroud during assembly.
    In order to be able to correct this uneven gap, the cover ring is not firmly centered, but adjustable and thus mounted by means of frictional engagement.
    The frictional engagement only between the cover ring and the housing has always led to unilateral migration of the cover ring and thus to gap changes and grazing damage due to the temperature change and different heating of the components.
    In order to avoid this, the cover ring gap was partially enlarged in the past and thus the efficiency was reduced.
    This is where the invention comes in, which makes the cover ring and centering ring in two parts to compensate for this uneven gap, for the purpose of setting.
    The adjustability is realized between the cover ring and centering ring. The outer diameter of the cover ring has enough space for the housing.
    Advantages of this invention are precisely the reduction of grazing damage (rotor blades and shroud) or the possibility of reducing the gap and thus a gain in efficiency.
    List of reference symbols
    10 axial turbine 11 turbine rotor 12 rotor blade 13 turbine housing 14 housing section 15 nozzle ring 16 housing section 17 clamping ring 18 fastening screw 19 anti-twist device 20 cover ring 21 fastening screw 22 radial gap 23 centering ring 24 fastening screw 25 groove 26 surface 27 surface 28 surface 29 surface 30 through hole 31 threaded hole 32 through hole 33 Through hole 34 threaded hole 35 expansion sleeve 36 axial gap
    权利要求:
    Claims (12)
    [1]
    1. Axial turbine (10), witha rotor-side turbine runner (11) which has rotor blades (12);a stator-side turbine housing (13);a cover ring (20) which is non-positively attached to the turbine housing (13) and adjoins the rotor blades (12) radially on the outside and defines a radial gap (22) together with the rotor blades (12);marked bya centering ring (23) which is positively connected to the cover ring (20) in such a way that a force fit between the centering ring (23) and the cover ring (20) is greater than a force fit between the cover ring (20) and the turbine housing (13) , wherein the centering ring (23) protrudes at least in sections into a groove (25) of the turbine housing (13) in such a way that in a cold state of the axial turbine the centering ring (23) extends over a radially inner surface (20) of the same on a radially inner surface (27 ) the groove (25) is centered, whereas in a hot state of the axial turbine the centering ring (23) is centered over a radially outer surface (28) of the same on a radially outer surface (29) of the groove (25).
    [2]
    2. Axial turbine according to claim 1, characterized in that the turbine housing (13) has, in relation to the rotor blades (12), an inflow-side housing section (14), an inflow-side nozzle ring (15) and an outflow-side housing section (16), the cover ring (20) is attached to the downstream housing section (16).
    [3]
    3. Axial turbine according to claim 1 or 2, characterized in that the cover ring (20) and the centering ring (23) are non-positively fastened to one another via first fastening screws (24).
    [4]
    4. Axial turbine according to one of Claims 1 to 3, characterized in that the cover ring (20) and the turbine housing (13) are non-positively fastened to one another via second fastening screws (21).
    [5]
    5. Axial turbine according to Claims 2 and 4, characterized in that, in addition, the nozzle ring (15) clamps the cover ring (20) on the turbine housing.
    [6]
    6. Axial turbine according to claim 5, characterized in that the sum of the screw force of the second fastening screws (21) and the clamping force of the nozzle ring (15) defines the frictional connection between the cover ring (20) and the turbine housing (13).
    [7]
    7. Axial turbine according to one of claims 4 to 6, characterized in that the size ratio between the frictional connection between the centering ring (23) and the cover ring (20) and the frictional connection between the cover ring (20) and the turbine housing (13) by number and / or the size and / or tightening torque of the first and second fastening screws (21, 24) is determined.
    [8]
    Axial turbine according to Claim 7, characterized in that the number of first fastening screws (24) is greater than the number of second fastening screws (21).
    [9]
    9. Axial turbine according to Claim 7 or 8, characterized in that the tightening torque of the first fastening screws (24) is greater than the tightening torque of the second fastening screws (21).
    [10]
    Axial turbine according to one of Claims 7 to 9, characterized in that the diameter of the first fastening screws (24) is greater than the diameter of the second fastening screws (21).
    [11]
    11. Axial turbine according to one of claims 1 to 10, characterized in that the size ratio between the frictional connection between the centering ring (23) and the cover ring (20) and the frictional connection between the cover ring (20) and the turbine housing (13) by the roughness of Friction surfaces between the centering ring (23) and the cover ring (20) and between the cover ring (20) and the turbine housing (13) is determined.
    [12]
    12. Exhaust gas turbocharger with a compressor and an axial turbine according to one of claims 1 to 11.
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    同族专利:
    公开号 | 公开日
    JP2017219046A|2017-12-14|
    CN107461224A|2017-12-12|
    DE102016209911A1|2017-12-07|
    CH712548A2|2017-12-15|
    KR20170138037A|2017-12-14|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
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    JP2008169705A|2007-01-09|2008-07-24|Toshiba Corp|Steam turbine|
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    US10450895B2|2016-04-22|2019-10-22|United Technologies Corporation|Stator arrangement|
    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
    DE102016209911.6A|DE102016209911A1|2016-06-06|2016-06-06|axial turbine|
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