• 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:
    Radial turbine for a turbocharger, with a turbine housing and a turbine rotor (19), the turbine housing having a turbine inflow housing (23), a turbine outflow housing (24) and an insert piece (26) mounted on the turbine inflow housing (23), the insert piece (26) being radial adjoins the outside of the rotor blades (20) of the turbine rotor (19) and delimits a flow channel of the radial turbine in sections in the region of the rotor blades (20). A wall of the insert (26) delimiting the flow channel is drawn radially outward at a defined circumferential section and is thus eccentric in order to close the nominal radial gap in this circumferential section between the outer ends of the rotor blades (20) and the insert (26) when the turbine rotor is stationary. to enlarge.
    公开号:CH711975B1
    申请号:CH01123/16
    申请日:2016-08-30
    公开日:2020-11-30
    发明作者:Peter Harald；Weisbrod Tobias；Kahanek Tomas；Hossbach Björn
    申请人:Man Energy Solutions Se；
    IPC主号:
    专利说明:

    The invention relates to a radial turbine for a turbocharger according to the preamble of claim 1. Furthermore, the invention relates to a turbocharger with a radial turbine and an insert for a radial turbine.
    [0002] A turbocharger has a turbine and a compressor, a first process gas being expanded in the turbine and the energy obtained in this case being used to compress a second process gas in the area of the compressor. Both the turbine and the compressor of a turbocharger have a housing and a rotor, the rotors of the compressor and turbine being connected via a shaft mounted in a bearing housing.
    The turbine of a turbocharger has a turbine inflow housing and a turbine outflow housing. Then, if the turbine is designed as a radial turbine, a so-called insert is mounted on the turbine inflow housing which, radially outwardly adjacent to the rotor blades of the turbine, delimits a flow channel of the radial turbine in sections in the area of the rotor blades of the turbine rotor. A radial gap between the radially outer ends of the blades of the turbine rotor and the insert should be large enough to prevent the blades of the turbine rotor from running into the insert, on the other hand it should be small enough to ensure the highest possible efficiency of the radial turbine.
    Proceeding from this, the present invention is based on the object of creating a novel radial turbine, a turbocharger with such a radial turbine and an insert for a turbine housing of the radial turbine.
    [0005] This object is achieved by a radial turbine according to claim 1.
    According to the invention, a wall of the insert that delimits the flow channel is drawn radially outward at a defined circumferential section with a partial enlargement of a nominal radial gap between the rotor blades and the insert when the turbine rotor is stationary.
    According to the invention, the wall of the insert that delimits the flow channel is drawn radially outward in a defined circumferential section and is thereby formed eccentrically in order to enlarge the nominal radial gap in this circumferential section when the turbine rotor is at a standstill between the outer ends of the blades and the insert. In this way, on the one hand, during operation with the turbine rotor rotating, in particular during a heating-up phase and a cooling-down phase of the turbine inflow housing, the blades of the turbine rotor can be prevented from running into the insert in a defined, particularly critical circumferential section, and on the other hand, a good efficiency of the radial turbine can still be guaranteed.
    The invention is based on the knowledge that when a radial turbine is in operation, in particular during a heating-up phase and a cooling-down phase, the turbine inflow housing of the radial turbine is subject to an uneven deformation in the circumferential direction of the same, so that the radial gap between the radially outer ends is accordingly in operation the rotor blades and the insert change differently over the circumferential extent of the turbine inflow housing and thus the circumferential extent of the insert piece. This uneven deformation itself causes an uneven change in the radial gap. With the invention, this non-uniform change in the radial gap can be compensated in such a way that, during operation, a radial gap which is uniform in the circumferential direction exists between the rotor blades of the turbine rotor and the insert piece of the turbine inflow housing.
    According to an advantageous development, the circumferential section in which the wall of the insert piece is drawn radially outward with an increase in the nominal radial gap between the blades and the insert piece, has a circumferential extension of 120 ° ± 40 °, in particular of 120 ° ± 30 °, preferably from 120 ° ± 20 °, particularly preferably from 120 ° ± 10 °. In this way, with a high degree of efficiency, running-in of the rotor blades of the radial turbine into the insert piece of the turbine housing can be safely and reliably avoided.
    According to an alternative advantageous development, the turbine inflow housing has an inflow flange and a screw housing-like in the circumferential direction circumferential inflow duct, the inflow duct having an upstream end adjacent to the inflow flange and a downstream end seen in the flow direction of the same, seen in the flow direction Circumferential section in which the wall of the insert piece is drawn radially outward with enlargement of the nominal radial gap between the rotor blades and the insert piece, is limited at a first end by the upstream end or the downstream end of the inflow channel and, starting from this first end, relates to the Direction of flow of the inflow channel extends opposite to the direction of flow of the inflow channel in the direction of its second end. This arrangement of the circumferential section in relation to the flow direction of the inflow channel is particularly preferred, since it has been shown that in this circumferential section, due to the different deformation of the inflow housing over the circumference, there is a higher probability of the rotor blades running into the insert than in other circumferential sections of the turbine inflow housing and thus insert.
    The turbocharger according to the invention is defined in claim 7. The insert according to the invention is defined in claim 9.
    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:<tb> Fig. 1: <SEP> a turbocharger with a compressor and a radial turbine;<tb> Fig. 2: <SEP> a detail of the turbocharger in the area of the radial turbine;<tb> Fig. 3: <SEP> another detail of the turbocharger in the area of the radial turbine together with contamination;<tb> Fig. 4: <SEP> a view of the turbine inflow housing of the radial turbine in the axial direction of view; and<tb> Fig. 5 <SEP> an insert piece of the radial turbine in a perspective view alone.
    1 shows details of a turbocharger 10, which comprises a turbine 11 designed as a radial turbine and a compressor 12 designed as a radial compressor.
    Of the compressor 12 designed as a radial compressor, a compressor rotor 13 with a shaft 14 and rotor blades 15 is shown. Furthermore, a compressor spiral housing 16, which functions as an outflow housing, and an intake housing 17, which functions as an inflow housing, of the compressor 12, which is designed as a radial compressor, is shown. An insert 18 of the compressor 12 is mounted on the compressor spiral housing 16 serving as an outflow housing and delimits a flow channel of the compressor 12 in sections radially outwardly adjacent to the rotor blades 15 of the compressor rotor 13.
    Of the turbine 11 designed as a radial turbine, a turbine rotor 19 is shown, which comprises rotor blades 20 and a shaft 21. The shaft 14 of the compressor rotor 13 and the shaft 21 of the turbine rotor 19 are coupled to one another, these shafts 14, 21 being supported in a so-called bearing housing 22. A turbine housing of the turbine 11 designed as a radial turbine is also shown, which comprises a turbine inflow housing 23 and a turbine outflow housing 24. The turbine inflow housing 23 is contoured in the manner of a spiral or a screw housing and provides an inflow duct 25 of the radial turbine 11.
    On the turbine inflow housing 23 of the turbine housing of the radial turbine 11, an insert 26 is mounted, this insert 26 delimiting a flow channel of the radial turbine 11 in sections in the area of the blades 20 radially outside adjacent to the outer ends of the blades 20 of the turbine rotor 19.
    Fig. 3 shows a section of the exhaust gas turbocharger 10 in the area of the turbine 11, wherein in Fig. 3 both the turbine inflow housing 23 and the turbine outflow housing 24 are each surrounded by contaminants 27, 28. Furthermore, FIG. 3 shows a protection 29 in the area of the compressor spiral housing 16.
    The contaminations 27, 28 of the turbine housing of the radial turbine 11 leave an inflow flange 30 in the area of the turbine inflow housing 23 and an outflow flange 31 in the area of the turbine outflow housing 24.
    As already stated, the turbine inflow housing in a radial turbine 11 is contoured in the manner of a spiral or a screw housing, the inflow channel 25 of the inflow housing 23 extending from the inflow flange 30 of the turbine inflow housing 23, namely in a spiral or worm housing-like manner around the turbine rotor 19 in the circumferential direction and thus the rotor blades 20 of the turbine rotor 19.
    This inflow channel 25 of the turbine inflow housing 23 has an upstream end 33 that is adjacent to the inflow flange 30 and is coupled to the same flow side, as well as a downstream end 34 as seen in the direction of flow of the inflow channel 25. Starting from the upstream end 33 of the Inflow channel 25 in the direction of the downstream end 34 thereof, the flow cross section of the inflow channel 25 decreases.
    In operation, the turbine inflow housing 23 is subject to different deformations over its circumferential extent. In radial turbines known from the prior art, this also reduces a radial gap between the radially outer ends of the rotor blades 20 of the turbine rotor 19 and the insert 26 mounted on the turbine inflow housing 23, viewed differently in the circumferential direction.
    In order to prevent the moving blades 20 from running into the insert 26 at such sections of the circumferential extent of the insert 26 of the turbine inflow housing 23, at which the radial gap between the insert 26 and the rotor blades 20 per se decreases more strongly during operation According to the invention, it is provided that a wall 35 of the insert 26 delimiting the flow channel is drawn radially outward on a defined circumferential section 36 with a section-wise enlargement of the nominal radial gap between the rotor blades 20 and the insert 26 when the turbine rotor 13 is at a standstill, so that this circumferential section can move during operation to compensate for the greater deformation of the turbine housing, namely the turbine inflow housing 23, and thus to prevent the rotor blades 20 of the turbine rotor 19 from running into the insert 26 in this circumferential section. Outside of this circumferential section 36, in which there is less risk of the turbine blades 20 running into the insert 26, the insert 26 is not drawn radially outward on its wall 35 delimiting the flow channel in order to ensure a high efficiency of the radial turbine.
    The circumferential section 36 of the insert 26, in which the wall 35 of the insert 26 is drawn radially outward with respect to the other circumferential sections of the same with an increase in the nominal radial gap between the rotor blades 20 and the insert 26, has a circumferential extension of 120 ° ± 40 °, in particular a circumferential extension of 120 ° ± 30 °, preferably of 120 ° ± 20 °, particularly preferably of 120 ° ± 10 °.
    The nominal radial gap between the rotor blades 20 and the insert 26 of the radial turbine 11 is the radial gap when the turbine rotor 13 and the radial turbine 11 has cooled down. In operation when the turbine rotor 13 is rotating, in particular during the heating phase and the cooling phase of the radial turbine 11, this gap changes non-uniformly seen in the circumferential direction of the insert 26. The defined contouring of the wall 35 of the insert 26 in the circumferential section 36 ensures that when the turbine rotor 13 is rotating, in particular during the heating phase and the cooling phase of the radial turbine 11, the radial gap between the rotor blades 20 and the insert 26 of the radial turbine 11 in the circumferential direction of the insert 26 is seen uniform. This prevents the rotor blades from running into the insert 26 when the radial turbine 11 is highly efficient.
    The invention is based on the knowledge that in a circumferential extent in particular of approximately 120 °, the turbine inflow housing 23 and the insert 26 mounted on the turbine inflow housing 23 are subject to a different deformation during operation than in other circumferential sections of the same, in such a way that in In this circumferential section 36, the rotor blades 20 of the turbine rotor 19 are more likely to run into the insert 26, so that, according to the invention, in this circumferential section 36, the radially inner wall 35 of the insert 26 is drawn radially outward.
    Fig. 4 visualizes the exact positioning or alignment of that peripheral portion 36 of the insert 26 on which the radially inner wall 35 of the same is drawn radially outward. 4 shows that the circumferential section 36 is delimited in the circumferential direction by two ends 37, 38. A first end 37 preferably coincides with the upstream end 33 or the downstream end 34 of the inflow channel 25 of the turbine inflow housing 23, the upstream end 33 of the inflow channel 25 adjoining the inflow flange 30 of the turbine inflow housing 23 as seen in the flow direction 32 of the inflow channel 25. The circumferential section 36 with the radially outwardly drawn wall 35 of the insert 26 extends from its first end 37 in the direction of its second end 38, namely as seen in the flow direction 32 of the inflow channel 25 opposite to the flow direction 32 of the same.
    The peripheral portion 36 of the insert 26, on which the radially inner wall 35 is drawn radially outward, accordingly runs over a peripheral portion of the inflow channel 25, which is seen in the flow direction 32 of the inflow channel 25, than the downstream end 34 of the inflow channel 25 faces.
    According to FIG. 4, a longitudinal center axis 40 of the inflow flange 30 runs perpendicular to a longitudinal center axis 41 of the insert 26 in the projection.
    FIG. 4 also visualizes a connection flange 39 of the turbine inflow housing, on which the turbine outflow housing 24 engages.
    The radial turbine 11 according to the invention is preferably used in the turbocharger 10 shown in FIG. 1, which comprises a radial compressor 12.
    The invention relates not only to the radial turbine 11 and the turbocharger 10 comprising the radial turbine 11, but also to the insert 26 as such, with which radial turbines 11 or turbochargers 10 already installed in the field can be retrofitted. By replacing an existing insert with the insert 26 according to the invention, a conventional radial turbine 11 installed in the field can accordingly be converted or converted into a radial turbine 11 according to the invention.
    As already stated, the wall 35 of the insert 26 is drawn in the circumferential section 36 radially outward. As a result, the flow-relevant radius of the radially inner wall 35 in the circumferential section 36 is increased. This enlargement can be constant over the entire circumferential extent 36; in contrast to this, however, it is also possible that this enlargement of the flow-relevant radius changes over the circumferential region 36.
    It can be provided that the enlargement of the radius and thus the radially outward pulling of the wall 35 starting from the ends 37, 38 of the peripheral portion 36 towards its center initially increases continuously and then a central region of the peripheral portion 36 is constant remains.
    List of reference symbols
    10 Turbocharger 11 Turbine 12 Compressor 13 Compressor rotor 14 Shaft 15 Blade 16 Compressor outflow housing 17 Compressor inflow housing 18 Insert 19 Turbine rotor 20 Blade 21 Shaft 22 Bearing housing 23 Turbine inflow housing 24 Turbine outflow housing 25 Inflow duct 26 Insert 27 Soiling 28 Soiling 29 Soiling 30 Flange 31 Flange 32 Flow direction 33 End 34 end 35 wall 36 circumferential section 37 end 38 end 39 connecting flange 40 longitudinal center axis 41 longitudinal center axis
    权利要求:
    Claims (10)
    [1]
    1. Radial turbine (11) for a turbocharger, with a turbine housing and a turbine rotor (19), the turbine housing having a turbine inflow housing (23), a turbine outflow housing (24) and an insert (26) mounted on the turbine inflow housing (23), wherein the Insert (26) adjoins the rotor blades (20) of the turbine rotor (19) radially on the outside and delimits a flow channel of the radial turbine in sections in the area of the rotor blades (20), characterized in that a wall (35) of the insert (26) delimiting the flow channel in one defined circumferential section (36) is drawn radially outward and is thereby eccentric in order to enlarge the nominal radial gap between the outer ends of the rotor blades and the insert in this circumferential section when the turbine rotor is stationary.
    [2]
    2. Radial turbine according to Claim 1, characterized in that the circumferential section (36) in which the wall (35) of the insert (26) is drawn radially outward has a circumferential extension of 120 ° ± 40 °.
    [3]
    3. Radial turbine according to Claim 2, characterized in that the circumferential section (36) in which the wall (35) of the insert (26) is drawn radially outward has a circumferential extension of 120 ° ± 30 °, preferably 120 ° ± 20 ° , particularly preferably of 120 ° ± 10 °.
    [4]
    4. Radial turbine according to one of claims 1 to 3, characterized in that the turbine inflow housing (23) has an inflow flange (30) and an inflow channel (25) running around the circumference in the manner of a worm housing or spiral, the inflow channel (25) having a flow direction of the same has an upstream end (33) adjoining the inflow flange (30) and a downstream end (34) seen in the flow direction thereof, and wherein the peripheral section (36) in which the wall (35) of the insert (26) is drawn radially outward is, is limited in the circumferential direction by two ends (37, 38), the first end (37) coinciding with the upstream end (33) of the inflow duct (25) of the turbine inflow casing (23), and starting from the first end (37 ) in relation to the flow direction of the inflow channel opposite to the flow direction of the inflow channel (25) in the direction of the second end (38).
    [5]
    5. Radial turbine according to one of claims 1 to 3, characterized in that the turbine inflow housing (23) has an inflow flange (30) and an inflow channel (25) running around in the circumferential direction like a worm housing, the inflow channel (25) being connected to the inflow flange when viewed in the flow direction (30) has adjacent, upstream end (33) and a downstream end (34) seen in the flow direction thereof, and wherein the peripheral section (36) in which the wall (35) of the insert (26) is drawn radially outward in The circumferential direction is limited by two ends (37, 38), the first end (37) coinciding with the downstream end (34) of the inflow channel (25) of the turbine inflow housing (23), and starting from the first end (37) the direction of flow through the inflow channel (25) extends counter to the direction of flow through the inflow channel (25) in the direction of the second end (38).
    [6]
    A radial turbine according to claim 4 or 5, characterized in that a longitudinal central axis (40) of the inflow flange (30) extends perpendicular to a longitudinal central axis (41) of the insert (26) in the projection.
    [7]
    7. Turbocharger (10) with a radial turbine (11) according to one of claims 1 to 6 and with a compressor (12), wherein the compressor (12) has a compressor housing (16, 17) and a compressor rotor (13) and the radial turbine ( 11) comprises a turbine housing (23, 24) and a turbine rotor (19), the compressor rotor (13) and the turbine rotor (19) being coupled via shafts (14, 21) mounted in a bearing housing (22).
    [8]
    8. Turbocharger according to Claim 7, characterized in that the compressor (12) is designed as a radial compressor.
    [9]
    9. insert (26) for a radial turbine according to one of claims 1 to 6, wherein the insert (26) when properly installed in the radial turbine radially outwardly adjoins rotor blades (20) of the turbine rotor (19) and a flow channel of the radial turbine in the area of Rotating blades (20) delimited in sections, characterized in that the insert is designed in such a way that when the insert is installed in the radial turbine as intended, a wall (35) of the insert (26) delimiting the flow channel is drawn radially outward at a defined circumferential section (36) and As a result, when the radial turbine is leveled as intended, it is eccentric in order to enlarge the nominal radial gap between the outer ends of the rotor blades (20) and the insert (26) when the turbine rotor (19) is stationary.
    [10]
    10. Insert according to claim 9, characterized in that the peripheral section (36) in which the wall (35) of the insert (26) is drawn radially outward has a peripheral extension of 120 ° ± 40 °, in particular 120 ° ± 30 ° , preferably of 120 ° ± 20 °, particularly preferably of 120 ° ± 10 °.
    类似技术:
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    同族专利:
    公开号 | 公开日
    JP2017110631A|2017-06-22|
    DE102015016486A1|2017-06-22|
    CN106968723A|2017-07-21|
    CN106968723B|2020-01-10|
    JP6877952B2|2021-05-26|
    CH711975A2|2017-06-30|
    KR20170072791A|2017-06-27|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    DE102008000849A1|2008-03-27|2009-10-01|Bosch Mahle Turbo Systems Gmbh & Co. Kg|Exhaust gas turbocharger for vehicles, has housing, in which guide vane module is inserted centered to rotating axis of turbine, where guide vane of guide vane module is arranged between base plate and cover plate|
    AT506001B1|2009-01-29|2010-08-15|Avl List Gmbh|ABGASTURBINE FOR AN EXHAUST BURGLAR|
    DE102009007735A1|2009-02-05|2010-08-12|Daimler Ag|Double-flow turbine housing for exhaust gas turbocharger of e.g. internal combustion engine, has guide vane arranged in transfer region between spiral channel and space, and intermediate wall sectionwise integrally designed with vane|
    DE102010064047A1|2010-12-23|2012-06-28|Man Diesel & Turbo Se|Fluid flow machine has housing with fluid guiding housing and bearing housing that is connected with fluid guiding housing, where impeller is mounted in fluid guiding housing over central impeller shaft in rotating manner|
    DE102011010744A1|2011-02-09|2012-08-09|Daimler Ag|Turbine for an exhaust gas turbocharger and turbocharger with such a turbine|DE102018105827A1|2018-03-14|2019-09-19|Man Energy Solutions Se|Formwork of a turbocharger and turbocharger|
    DE102018107264A1|2018-03-27|2019-10-02|Man Energy Solutions Se|Centrifugal compressor and turbocharger|
    法律状态:
    2017-07-31| PCOW| Change of address of patent owner(s)|
    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
    DE102015016486.4A|DE102015016486A1|2015-12-17|2015-12-17|Radial turbine, turbocharger and insert for a turbine housing of the radial turbine|
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