• 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:
    Turbocharger, with a turbine (2) for expanding a first medium and with a compressor for compressing a second medium. The turbine (2) has a turbine housing (4) and a turbine rotor (5) bladed with turbine rotor blades (14), with radially outer edges (14a) of the turbine rotor blades (14) and one of the turbine rotor blades (14) facing portion of the turbine housing (4) or a stator-side component (13) connected to the turbine housing (4) define a turbine-side gap. The compressor has a compressor housing and a compressor rotor which is coupled to the turbine rotor via a shaft (8) and is bladed with compressor rotor blades, with radially outer edges of the compressor rotor blades and a section of the compressor housing facing the compressor rotor blades or a section of the compressor housing connected to the compressor housing stator-side component define a gap on the compressor side. The turbine housing (4) and the compressor housing are each connected to a bearing housing in which the shaft (8) is mounted. The section of the turbine housing (4) facing the turbine rotor blades (14) or the stator-side component (13) connected to the turbine housing (4) and / or the section of the compressor housing or the stator-side component connected to the compressor housing facing the compressor rotor blades has an inlet structure (17) comprising cavities (18).
    公开号:CH716127A2
    申请号:CH00320/20
    申请日:2020-03-18
    公开日:2020-10-30
    发明作者:Benetschik Hannes；Bornhorn Alfons；Heinz Christoph
    申请人:Man Energy Solutions Se；
    IPC主号:
    专利说明:

    The invention relates to a turbocharger.
    Fig. 1 shows the basic structure of a turbocharger 1 known from practice. A turbocharger 1 has a turbine 2 for expanding a first medium, in particular for expanding exhaust gas from an internal combustion engine, with energy being obtained when the first medium is expanded . Furthermore, the turbocharger 1 comprises a compressor 3 for compressing a second medium, in particular charge air to be supplied by an internal combustion engine, to be precise using the energy obtained during the expansion of the first medium in the turbine 2.
    The turbine 1 has a turbine housing 4 and a turbine rotor 5. The compressor 3 has a compressor housing 6 and a compressor rotor 7. The turbine rotor 5 and the compressor rotor 7 are coupled via a shaft 8 which is mounted in a bearing housing 9. The bearing housing 9 is connected, on the one hand, to the turbine housing 4 and, on the other hand, to the compressor housing 6.
    Fig. 1 also shows an optional muffler 10, which is connected to the compressor housing 6, wherein 10 charge air is passed through the muffler.
    The turbine housing 4 comprises an inflow housing 11 and an outflow housing 12. The first medium to be relaxed is fed to the turbine rotor 5 via the inflow housing 11, here in the radial direction. The relaxed first medium can be discharged from the turbine rotor 5 via the outflow housing 12, here in the axial direction. The turbine of FIG. 1 is a radial turbine.
    As components of the turbine housing 4, Fig. 1 also shows an insert 13 and a nozzle ring 15. The insert 13, which is a connected to the turbine housing 4, stator-side assembly of the turbine 2, closes radially on the outside of turbines Rotor blades 14 of the turbine rotor 5 and delimits a flow channel of the inflow housing 11 at least in sections. Radially outer edges 14a of the turbine rotor blades 14 and a section of the turbine housing 4 facing the turbine rotor blades 14 or of the insert 13 connected to the turbine housing 4 define a turbine-side gap between the turbine rotor blades 14 and the stator of the turbine 2.
    The compressor rotor 7, which is designed in Fig. 1 as a radial compressor, carries compressor blades 16. Radial outer edges 16a of the compressor blades 16 and a compressor blade 16 facing portion of the compressor housing 6 or one connected to the compressor housing Components on the stator side define a gap on the compressor side between the compressor rotor blades 16 and the stator of the compressor 2.
    A turbocharger according to FIG. 1 is known from DE 10 2016 125 189 A1.
    In order to provide the highest possible efficiency for the turbocharger, it is desirable to make the turbine-side gap between the turbine blades and the stator of the turbine and the compressor-side gap between the compressor blades and the stator of the compressor as small as possible. When the turbocharger is in operation, however, there is a risk that the turbine rotor blades will run into the stator, particularly in the area of the turbine, as a result of centrifugal forces acting on the turbine rotor and as a result of thermally induced expansions of the turbine rotor. This can then damage the respective rotor blades. This is a disadvantage.
    From DE 10 2015 016 486 A1 a turbocharger is known in which the insert piece has a defined contouring in the area of the turbine in order to prevent the turbine rotor blades from running into the insert piece.
    There is a need for a new type of turbocharger in which small gaps are set in the area of the turbine and / or the compressor for the gap between the turbine blades and / or the compressor blades and a stator of the turbine and / or the compressor can be, without the risk that in the event of the rotor blades running into the stator, the respective rotor blades will be damaged.
    Proceeding from this, the present invention is based on the object of creating a new type of turbocharger. This object is achieved by a turbocharger according to claim 1. According to the invention, the section of the turbine housing facing the turbine rotor blades or the stator-side component connected to the turbine housing and / or the section of the compressor housing facing the compressor rotor blades or the stator-side component connected to the compressor housing has an inlet structure comprising cavities. With the present invention it is proposed for the first time that the section of the turbine housing facing the turbine rotor blades or the stator-side component connected to the turbine housing and / or the section of the compressor housing facing the compressor rotor blades or the stator-side component connected to the compressor housing with an inlet structure Cavities. If the rotor blades run into the inlet structure, for example as a result of centrifugal forces acting during operation and / or as a result of thermal expansions, the inlet structure yields so that the respective rotor blades are not subject to any risk of damage. In this way, a minimal gap can be set between the edges of the respective rotor blades and the respective stator of the turbine without the risk of damage to the respective rotor blades during operation of the turbocharger.
    According to a further development of the invention, the inlet structure is designed to be open-pored or open-celled in such a way that the cavities of the inlet structure are designed to be open in the direction of the respective rotor blades or to face the respective rotor blades. Such an open-pore or open-cell inlet structure is particularly preferred in order to set a minimum gap between the rotor blades and the stator-side inlet structure without the risk of damage to the rotor blades and the inlet structure when the rotor blades run into the inlet structure.
    According to a further development of the invention, the inlet structure comprises honeycomb-like cavities. Honeycomb-like cavities for the inlet structure on the stator side are particularly preferred in order to set a minimal gap between the rotor blades and the respective stator without any risk of damage to the rotor blades and the inlet structure during operation. Here, the inventors also understand honeycomb-like cavities to be surface structures such as those found in golf balls. In this way, the efficiency can be optimized, since the thin, turbulent boundary layer can be formed.
    According to a development of the invention, walls of the inlet structure have a maximum wall thickness of 0.2 mm. Such thin walls of the inlet structure are particularly flexible and make it possible to set a minimal gap between the rotor blades and the respective stator during operation without the risk of damage to the rotor blades and to the inlet structure.
    [0016] Preferred developments of the invention emerge from the subclaims 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 cross section through a turbocharger known from practice;<tb> Fig. 2: <SEP> a cross section through a turbocharger according to the invention in the area of a turbine of the turbocharger designed as a radial turbine;<tb> Fig. 3: <SEP> a cross section through a further turbocharger according to the invention in the area of a turbine of the turbocharger designed as an axial turbine; and<tb> Fig. 4: <SEP> the detail A-A of Figs. 2, 3.
    A turbocharger 1 has a turbine 2 for expanding a first medium, in particular for expanding exhaust gas from an internal combustion engine. Furthermore, a turbocharger 1 has a compressor 3 for compressing a second medium, in particular charge air, specifically using the energy obtained in the turbine 2 when the first medium is expanded.
    The turbine 2 has a turbine housing 4 and a turbine rotor 5. The compressor 3 has a compressor housing 6 and a compressor rotor 7. The compressor rotor 7 is coupled to the turbine rotor 5 via a shaft 8 which is supported in a bearing housing 9 is, wherein the bearing housing 9 is positioned between the turbine housing 4 and the compressor housing 5 and is connected to both the turbine housing 4 and the compressor housing 5.
    The turbine housing 4 typically has an inflow housing 11 and an outflow housing 12. Via the inflow housing 11, which is connected to the bearing housing 9, the first medium to be relaxed can be guided onto the turbine rotor 5. Relieved, first medium can be removed from the turbine rotor 5 via the outflow housing 12, which is connected to the inflow housing 11. The turbine housing 4 typically also has an insert piece 13 and a nozzle ring 15. The insert piece 13 delimits a flow channel for the first medium in sections, the insert piece 13 adjoining turbine blades 14 of the turbine rotor 5 radially on the outside. The nozzle ring 15 is positioned upstream of the turbine rotor 5 and serves to guide the flow of the first medium to be expanded upstream of the turbine rotor 5.
    The turbine rotor 5 accordingly carries the turbine blades 14, with a gap between the radially outer edges 14a of the turbine blades 14 and a radially outer adjoining stator-side assembly, typically the stator-side insert 13, which is connected to the turbine housing 4 is trained.
    Such a gap is also formed in the area of the compressor 3 between the compressor rotor blades 16 of the compressor rotor 7 and the compressor housing 6 adjoining the compressor rotor 7 radially on the outside, in particular between the outer edges 16a of the compressor rotor blades 16 and a compressor - Blade 16 facing portion of the compressor housing 6 or a stator-side component connected to the compressor housing 6.
    With the present invention it is now proposed that to form a minimal turbine-side gap between the turbine blades 14 and the stator of the turbine 2 and / or to form a minimal compressor-side gap between the compressor blades 16 and the adjacent stator of the compressor 3, the section of the turbine housing 4 facing the turbine rotor blades 14 or the stator-side component connected to the turbine housing 4 and / or the section of the compressor housing 6 facing the compressor rotor blades 16 or the stator-side component connected to the compressor housing 6 carries an inlet structure 17 , which includes cavities 18.
    In operation, the blades 14 and 16 with their radially outer edges 14a and 16a run into this inlet structure 17, without risk of damage to the blades 14 or 16, so that there is then a minimal gap between the blades during operation 14 or 16 and the respective adjacent stator or the stator-side inlet structure 17 is formed. This enables a high degree of efficiency to be achieved for the turbocharger.
    The inlet structure 17 is preferably of open-pore or open-cell design, specifically in such a way that the cavities 18 of the inlet structure 17 are designed to be open in the direction of the respective rotor blade 14 or 16.
    The inlet structure is preferably designed in a honeycomb shape; it then comprises honeycomb-like cavities 18.
    The cavities 18 of the inlet structure 17 are delimited or defined by walls 19, which preferably have a maximum wall thickness of 0.2 mm and a minimum wall thickness of 0.05 mm. Such an inlet structure 17 is particularly flexible. Damage to the rotor blades and to the inlet structure 17 when the rotor blades run into or rub against the inlet structure 17 can thus be reliably avoided.
    In the area of the turbine 2, the inlet structure 17 is preferably made of a high-temperature steel, in particular a steel of a nickel-based alloy or a nickel-chromium-based alloy. X12 steels or X22 steels in particular can be used here.
    In the area of the compressor 3, the respective inlet structure 17 can consist of a gray cast material or an aluminum material.
    The respective inlet structure 17 is preferably applied to the stator-side component carrying the inlet structure 17 using an additive manufacturing method, such as, for example, 3D printing.
    As already stated, the inlet structure 17 can be used both in the area of the turbine 2 of the turbocharger 1 and in the area of the compressor 3 of the turbocharger 1.
    The turbine 2 can, as shown in FIGS. 1 and 2, be a radial turbine. It is also possible that the turbine 2 is an axial turbine. 3 shows a detail from an axial turbine in the area of the rotor blades 14 of the turbine, the turbine housing 4 or a stator-side assembly 20 connected to the turbine housing 4 again having the inlet structure 17 with the cavities 18 on a section facing the rotor blades 14.
    The invention can also be used on a compressor, for example on a radial compressor or also on an axial compressor, a turbocharger.
    With the invention it is possible to increase the efficiency of a turbocharger 1. In the area of the turbine 2 as well as in the area of the compressor 3 of the turbocharger 1, minimal gaps can be set between the rotor blades 14 or 16 of turbine 2 or compressor 3 and a radially outwardly adjoining stator-side component. There is no risk of damage to the rotor blades 14 or 16 when they rub against or run into the inlet structure 17. The inlet structure 17 is designed to be relatively soft or resilient. When the rotor blades 14 or 16 run in or rub against it, there is no risk of damage to the rotor blades 14 or 16;
    List of reference symbols
    1 turbocharger 2 turbine 3 compressor 4 turbine housing 5 turbine rotor 6 compressor housing 7 compressor rotor 8 shaft 9 bearing housing 10 muffler 11 inflow housing 12 outflow housing 13 insert 14 turbine blade 14a edge 15 nozzle ring 16 compressor blade 16a edge 17 inlet structure 18 cavity 19 wall
    权利要求:
    Claims (9)
    [1]
    1. Turbocharger (1),with a turbine (2) for the expansion of a first medium,with a compressor (3) for compressing a second medium using the energy obtained in the turbine (2) when the first medium is expanded,wherein the turbine (2) has a turbine housing (4) and a turbine rotor (5) bladed with turbine rotor blades (14), with radially outer edges (14a) of the turbine rotor blades (14) and one of the turbine rotor blades (14) the facing section of the turbine housing (4) or of a stator-side component (13) connected to the turbine housing (4) define a turbine-side gap,wherein the compressor (3) has a compressor housing (6) and a compressor rotor (7) which is coupled to the turbine rotor (5) via a shaft (8) and is bladed with compressor rotor blades (16), with radially outer edges (16a) of the compressor - rotor blades (16) and a section of the compressor housing (6) facing the compressor rotor blades (16) or a stator-side component connected to the compressor housing (6) define a gap on the compressor side,wherein the turbine housing (4) and the compressor housing (6) are each connected to a bearing housing (9) arranged between the same and in which the shaft (8) is mounted,characterized in thatthe section of the turbine housing (4) facing the turbine rotor blades (14) or of the stator-side component (13) connected to the turbine housing (4) and / or the section of the compressor housing (6) facing the compressor rotor blades (16) or of the with the stator-side component connected to the compressor housing (6) has an inlet structure (17) comprising cavities (18).
    [2]
    2. Turbocharger according to claim 1, characterized in that the inlet structure (17) is designed with open pores or open cells in such a way that the cavities (18) of the inlet structure (17) in the direction of the respective rotor blades (14, 16) or the respective rotor blades (14 , 16) are open facing.
    [3]
    Turbocharger according to Claim 1 or 2, characterized in that the inlet structure (17) comprises honeycomb-like cavities (18).
    [4]
    4. Turbocharger according to one of Claims 1 to 3, characterized in that the walls (19) of the inlet structure (17) have a maximum wall thickness of 0.2 mm.
    [5]
    5. Turbocharger according to one of Claims 1 to 4, characterized in that the inlet structure (17) in the area of the turbine (2) consists of a high-temperature steel.
    [6]
    6. Turbocharger according to one of Claims 1 to 5, characterized in that the inlet structure (17) in the area of the compressor (3) consists of a gray cast iron material or an aluminum material
    [7]
    7. Turbocharger according to one of Claims 1 to 6, characterized in that the turbine is an axial turbine, the section of the turbine housing or of the component connected to the same which faces the turbine rotor blades of the axial turbine carrying the inlet structure.
    [8]
    8. Turbocharger according to one of Claims 1 to 6, characterized in that the turbine (2) is a radial turbine, the section of the turbine housing (4) or of the component (13) connected to it facing the turbine rotor blades (14) of the radial turbine the inlet structure (17) carries.
    [9]
    9. Turbocharger according to one of Claims 1 to 8, characterized in that the compressor is a radial compressor, the section of the compressor housing (6) or of the component connected to the same, facing the compressor rotor blades (16) of the radial compressor, carrying the inlet structure (17) .
    类似技术:
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    DE10028733A1|2001-12-13|Exhaust turbine for turbocharger ha guide blades with flow intake edges and/or outflow edges at angle relative to jacket line, and cover rings to connected blade ends
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    EP3056684B1|2018-05-16|Axially split inner ring for a flow machine, guide blade assembly and aircraft engine
    EP1673519B1|2012-08-29|Sealing arrangement for a gas turbine
    CH716127A2|2020-10-30|Turbocharger.
    EP3412875A2|2018-12-12|Running-in structure for a turbomachine and method for producing a running-in structure
    同族专利:
    公开号 | 公开日
    DE102019110671A1|2020-10-29|
    KR20200125479A|2020-11-04|
    RU2020112758A|2021-09-30|
    CN111852579A|2020-10-30|
    JP2020180616A|2020-11-05|
    US20200386116A1|2020-12-10|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US3365172A|1966-11-02|1968-01-23|Gen Electric|Air cooled shroud seal|
    US3656862A|1970-07-02|1972-04-18|Westinghouse Electric Corp|Segmented seal assembly|
    US4867639A|1987-09-22|1989-09-19|Allied-Signal Inc.|Abradable shroud coating|
    DE10259963B4|2002-12-20|2010-04-01|Mtu Aero Engines Gmbh|honeycomb seal|
    DE102016125189B4|2016-12-21|2020-11-26|Man Energy Solutions Se|turbocharger|
    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    DE102019110671.0A|DE102019110671A1|2019-04-25|2019-04-25|turbocharger|
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