• 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 having a turbine for relaxing a first medium, with a compressor for compressing a second medium using energy recovered in the turbine during the expansion of the first medium, the turbine having a turbine housing (2) and a turbine rotor (3), the compressor having a compressor housing and a compressor rotor coupled to the turbine rotor via a shaft (4), the turbine housing and the compressor housing each being connected to a bearing housing (1) therebetween in which the shaft (4) is mounted, and wherein the bearing housing (1) is connected to a Turbinenzuströmgehäuse (2) of the turbine housing via a compensation element (7).
    公开号:CH713775A2
    申请号:CH00482/18
    申请日:2018-04-16
    公开日:2018-11-15
    发明作者:Aynacioglu Fikri；Mühlenbrock Stefan；Hossbach Björn；Hörmeyer Klaus；Köster Philipp；Anding Dirk
    申请人:Man Energy Solutions Se；
    IPC主号:
    专利说明:

    Description: The invention relates to a turbocharger.
    [0002] A turbocharger has a turbine and a compressor. A first medium, in particular exhaust gas, is expanded in the turbine of a turbocharger and energy is obtained in the process. A second medium, in particular charge air, is compressed in the compressor of the turbocharger, using the energy obtained in the turbine when the first medium is expanded. The turbine of a turbocharger has a turbine housing and a turbine rotor. The turbocharger's compressor has a compressor housing and a compressor rotor. Turbine rotor and compressor rotor are coupled via a shaft which is mounted in a bearing housing, the bearing housing being connected on the one hand to the turbine housing and on the other hand to the compressor housing.
    From practice, it is also known that the turbine housing of a turbocharger has a turbine inflow housing, via which the first medium to be relaxed can be supplied to the turbine rotor. The turbine housing typically receives an insert and a nozzle ring of the turbine housing. Relaxed first medium can be discharged from the turbine via the insert, the insert extending radially outside adjacent to rotor blades of the turbine rotor. The nozzle ring, which is also referred to as a turbine guide device or guide vane or guide device, has guide vanes which are positioned upstream of the turbine rotor, as seen in the direction of flow of the first medium, and via which the first medium to be relaxed is guided upstream of the turbine rotor.
    In turbochargers known from practice, the turbine inflow housing is typically connected to the bearing housing via a clamp connection. Such a connection of the turbine inflow housing to the bearing housing is to be assessed as critical due to the design, since there are typically large temperature differences between the turbine inflow housing and the bearing housing. The turbine inflow housing is exposed to the relatively hot exhaust gas and is therefore more thermally stressed than the bearing housing. This can result in temperature-related deformations in the connection area between the turbine inflow housing and the bearing housing, as a result of which the tightness of the clamp connection between the turbine inflow housing and the bearing housing is impaired. There is a need to better secure the turbine inflow housing to the bearing housing in this regard.
    Proceeding from this, the present invention has for its object to provide a novel turbocharger. This object is achieved by a turbocharger according to claim 1. According to the invention, the bearing housing is connected to the turbine inflow housing of the turbine housing via a compensation element. The compensation element can be used to compensate for temperature-related deformations in the connection area between the turbine inflow housing and the bearing housing. The compensation element is flexible and elastic in the radial direction, so that it can carry out a radial expansion and accordingly can absorb or compensate for a temperature-related shift between the turbine inflow housing and the bearing housing.
    Preferably, the compensation element is connected at a radially outer section to the turbine inflow housing and at a radially inner section to the bearing housing, a bellows section-like contoured or curved wall extending between these sections seen in the radial direction. Such a configuration and connection of the compensation element with the turbine inflow housing and bearing housing is particularly preferred.
    According to a development of the invention, the compensation element consists of a nickel-based alloy material. The nickel-based alloy material particularly preferably has the following composition in percent by weight: 50.00-55.00% nickel (Ni), 17.00-21.00% chromium (Cr), 4.75-5.50% niobium (Nb), 2.80-3.30% molybdenum (Mo), 0.65-1.15% titanium (Ti), 0.20-0.80% aluminum (AI), the rest iron (Fe). Such a material for the compensation element provides a sufficiently high creep resistance for the compensation element even at temperatures of more than 600 ° C. Turbine inflow housings and bearing housings can be made of metallic materials, as are the same in turbochargers known from practice.
    Preferred 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:
    1: a partial cross section in the axial direction through a turbocharger according to the invention in the region of a turbine and a bearing housing.
    The invention relates to a turbocharger. A turbocharger has a turbine for expanding a first medium, in particular for expanding exhaust gas from an internal combustion engine. Furthermore, a turbocharger has a compressor for compressing a second medium, in particular charge air, using energy obtained in the turbine when the first medium is expanded. The turbine has a turbine housing and a turbine rotor. The compressor has a compressor housing and a compressor rotor. The compressor rotor is coupled to the turbine rotor via a shaft which is mounted in a bearing housing, the bearing housing being positioned between the turbine housing and the compressor housing and being connected to both the turbine housing and the compressor housing.
    The above basic structure of a turbocharger is familiar to the expert addressed here.
    Fig. 1 shows a section of a turbocharger according to the invention in the region of the connection between the bearing housing 1 and a turbine inflow housing 2 of the turbine housing of a turbine. 1 also shows a section of a turbine rotor 3 and a shaft 4, the turbine rotor 3 being coupled via the shaft 4 to a compressor rotor (not shown). The bearing housing 2 includes a bearing housing cover 5, which is connected to the bearing housing 1 and, viewed in the axial direction, is positioned in sections between the turbine rotor 3 and the bearing housing 1.
    The turbine inflow housing 2 supplies the first medium to be relaxed to the turbine rotor 3, a so-called nozzle ring 6 being positioned upstream of the turbine rotor 3, viewed in the direction of flow of the first medium to be relaxed, which is also referred to as a turbine nozzle, and the nozzle ring 6 is used for this the medium to be supplied to the turbine rotor 3 is guided upstream of the turbine rotor 3 via guide vanes of the nozzle ring 6.
    The present invention here provides a completely new connection of the turbine inflow housing 2 with the bearing housing 1, namely via a compensation element 7. Thus, the bearing housing 1 and turbine inflow housing 2 are connected to one another via the compensation element 7, the compensation element being flexible and elastic in the radial direction in order to compensate for a temperature-related, different thermal deformation of the bearing housing 1 and the turbine inflow housing 2. The compensation element 7 can compensate for a temperature-related radial expansion due to its elasticity.
    The compensation element 7 is mounted with a radially outer section 8 of the same on the turbine inflow housing 2 and connected to the bearing housing 1 with a radially inner section 9 of the same. A screw connection between the compensation element 7 and the turbine inflow housing 2 or bearing housing is typically provided here.
    Between the two sections 8, 9 of the compensation element 7, the same has a wall 10 that is contoured or curved in the manner of a bellows section or is curved in the radial direction.
    The two sections 8, 9 of the compensation element 7 are arranged in the axial direction in approximately the same axial position. Viewed in the radial direction, however, there is a clear offset between the sections 8, 9, the wall, which is contoured or curved in the manner of a bellows section, extends partly in the radial direction and partly in the axial direction with curved sections running between them.
    Seen in the flow direction of the first medium to be relaxed, the section 8 of the compensation element 7 engages a section 11 of the turbine inflow housing 2, which is positioned upstream of the nozzle ring 6. A section 12 of the bearing housing 1, on which the section 9 of the compensation element 7 engages, is positioned approximately at the radial height of the nozzle ring 6 when viewed in the radial direction.
    The compensation element 7 is made of a nickel-based alloy material.
    The nickel-based alloy material preferably has the following composition in percent by weight: 50.00-55.00% nickel (Ni), 17.00-21.00% chromium (Cr), 4.75-5.50% niobium (Nb), 2, 80-3.30% molybdenum (Mo), 0.65-1.15% titanium (Ti), 0.20-0.80% aluminum (AI), 0.00 to 1.00% cobalt (Co), 0.00 to 0.08% carbon (C), 0.00 to 0.35% magnesium (Mg), 0.00 to 0.35% silicon (Si), 0.00 to 0.015% phosphorus (P), 0.00 to 0.017% sulfur (S), 0.00 to 0.006% boron (B) 0.00 to 0.30% copper (Cu) in the rest iron (Fe).
    Such a nickel-based alloy material has good creep resistance even at temperatures of more than 600 ° C., so that a temperature-related failure of the compensation element 7 is not to be expected.
    The compensation element 7 is not only used to compensate for temperature-related radial expansions in the connection area between the bearing housing 1 and the turbine inflow housing 2, rather the containment safety of the turbocharger can also be improved via the same. If the turbine rotor 3 bursts, kinetic energy from fragments can also be intercepted via the compensation element 7.
    LIST OF REFERENCE NUMERALS 1 bearing housing 2 turbine inflow housing 3 turbine rotor 4 shaft 5 bearing housing cover 6 nozzle ring 7 compensation element 8 section 9 section 10 wall 11 section 12 section
    权利要求:
    Claims (9)
    [1]
    Claims
    1. turbocharger, with a turbine for expansion of a first medium, with a compressor for compression of a second medium using energy obtained in the turbine during expansion of the first medium, the turbine having a turbine housing and a turbine rotor (3), wherein the compressor has a compressor housing and a compressor rotor coupled to the turbine rotor (3) via a shaft (4), the turbine housing and the compressor housing each being connected to a bearing housing (1) arranged between them and in which the shaft (4) is mounted are characterized in that the bearing housing (1) is connected to a turbine inflow housing (2) of the turbine housing via a compensation element (7).
    [2]
    2. Turbocharger according to claim 1, characterized in that the compensation element (7) is connected at a radially outer portion (8) to the turbine inflow housing (2).
    [3]
    3. Turbocharger according to claim 1 or 2, characterized in that the compensation element (7) is connected to the bearing housing (1) at a radially inner section (9).
    [4]
    4. Turbocharger according to one of claims 1 to 3, characterized in that the compensation element (7) seen in the radial direction has a bellows section-like contoured or curved wall (10).
    [5]
    5. Turbocharger according to one of claims 1 to 4, characterized in that a bearing housing cover (5) is connected to the bearing housing (1).
    [6]
    6. Turbocharger according to one of claims 1 to 5, characterized in that the compensation element (7) consists of a nickel-based alloy material.
    [7]
    7. Turbocharger according to claim 6, characterized in that the nickel-based alloy material has the following composition in weight percent: 50.00-55.00% nickel (Ni), 17.00-21.00% chromium (Cr), 4.75-5 , 50% niobium (Nb), 2.80-3.30% molybdenum (Mo), 0.65-1.15% titanium (Ti), 0.20-0.80% aluminum (AI), the rest iron (Fe).
    [8]
    8. turbocharger according to claim 7, characterized in that the nickel-based alloy material a maximum of 1.00% cobalt (Co), a maximum of 0.08% carbon (C), a maximum of 0.35% magnesium (Mg), a maximum of 0.35% silicon ( Si), maximum 0.015% phosphorus (P), maximum 0.017% sulfur (S), maximum 0.006% boron (B) and maximum 0.30% copper (Cu).
    [9]
    9. Turbocharger according to one of claims 1 to 8, characterized in that the turbine is a radial turbine.
    类似技术:
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    同族专利:
    公开号 | 公开日
    KR20180125382A|2018-11-23|
    CH713775B1|2022-02-15|
    JP2018193992A|2018-12-06|
    DE102017208107A1|2018-11-15|
    US20180328373A1|2018-11-15|
    CN108868915A|2018-11-23|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US4009568A|1975-10-30|1977-03-01|General Motors Corporation|Turbine support structure|
    EP0116160B1|1983-01-18|1987-12-23|BBC Brown Boveri AG|Turbocharger having bearings at the ends of its shaft and an uncooled gas conduit|
    EP1860284A1|2006-05-23|2007-11-28|ABB Turbo Systems AG|Casings assembling|
    JP2009167971A|2008-01-18|2009-07-30|Ihi Corp|Housing fastening method and supercharger|
    DE102009058411A1|2009-12-16|2011-06-22|BorgWarner Inc., Mich.|turbocharger|
    DE102010015272A1|2010-04-15|2011-10-20|Bosch Mahle Turbo Systems Gmbh & Co. Kg|loader|
    GB2494144A|2011-08-30|2013-03-06|Gm Global Tech Operations Inc|Turbocharger to exhaust manifold connection|
    JP6037712B2|2012-08-08|2016-12-07|三菱重工業株式会社|Variable displacement exhaust turbocharger|
    DE102013013235A1|2013-08-08|2015-02-12|Man Diesel & Turbo Se|End cover for a compressor impeller of an exhaust gas turbocharger and turbocharger|
    EP3102805A4|2014-02-04|2018-02-21|Borgwarner Inc.|Heat shield for mixed flow turbine wheel turbochargers|
    US10100642B2|2015-08-31|2018-10-16|Rolls-Royce Corporation|Low diameter turbine rotor clamping arrangement|
    DE102015217668A1|2015-09-15|2017-03-16|Continental Automotive Gmbh|turbocharger|DE102017103980A1|2017-02-27|2018-08-30|Man Diesel & Turbo Se|turbocharger|
    DE102017215539A1|2017-09-05|2019-03-07|Man Diesel & Turbo Se|turbocharger|
    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    DE102017208107.4A|DE102017208107A1|2017-05-15|2017-05-15|turbocharger|
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