• 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:
    Turbine inlet housing (10) of an axial turbine of a turbocharger having a flow inlet end (11) on which an outer wall (13) of Turbinenzuströmgehäuses defines a circular in cross-section flow channel (15), with a flow outlet end (12) on which the outer wall (13) of the Turbinenzuströmgehäuses and an inner wall (14) thereof define a circular in cross-section flow channel (16), and with ribs (17), via which the outer wall (13) of the Turbinenzuströmgehäuses and the inner wall (14) of the same are. Connecting portions (22) of the ribs (17) with which they engage the outer wall (13) of the Turbinenzuströmgehäuses are positioned in the region of the flow-inlet-side flange (11).
    公开号:CH714062A2
    申请号:CH00831/18
    申请日:2018-07-03
    公开日:2019-02-15
    发明作者:Kalchschmid Markus；Stöhr Stefan；Schatzinger Andreas
    申请人:Man Energy Solutions Se；
    IPC主号:
    专利说明:

    Description: The invention relates to a turbine inflow housing of an axial turbine of a turbocharger.
    A turbocharger has a turbine for expanding a first medium and a compressor for compressing a second medium. The turbine of the turbocharger has a turbine housing and a turbine rotor. The turbocharger's compressor has a compressor housing and a compressor rotor. The turbine rotor and the compressor rotor are connected to one another via a shaft which is rotatably mounted in a bearing housing of the turbocharger. The turbocharger bearing housing is connected to both the turbine housing and the compressor housing. The turbine of a turbocharger can be designed as an axial turbine or as a radial turbine. The compressor of a turbocharger can also be designed as an axial compressor or as a radial compressor. The present invention relates to a turbine inflow housing of the turbine housing of a turbine of a turbocharger designed as an axial turbine.
    The basic structure of an axial turbine of a turbocharger is known from DE 20 2014 002 981 U1. This prior art shows sections of the turbine rotor of the turbine together with the turbine inflow housing of the turbine housing. DE 20 2014 002 981 U1 shows the end of the turbine inflow housing on the flow outlet side, at which the turbine inflow housing, namely a radially inner wall and a radially outer wall of the same, define a flow channel which is annular in cross section. The medium to be expanded can be supplied to the turbine rotor of the axial turbine via this annular flow channel.
    According to DE 20 2014 002 981 U1, a nozzle ring is positioned between the turbine rotor and the end of the turbine inflow housing on the flow outlet side. The nozzle ring is also referred to as a diffuser or diffuser.
    From practice it is known that the radially inner wall of the turbine inflow housing and the radially outer wall of the same are connected to one another via ribs which extend through the annular flow channel at the flow exit end of the turbine inflow housing. The medium which is to be fed to the turbine rotor flows around these ribs.
    Turbine inflow housings known from practice are subject to cracking as a result of thermal cycles. This limits the life of a turbine inflow housing. In addition to the formation of cracks, there is the problem with turbine inflow housings known from practice that a relative movement between the turbine inflow housing and an assembly mounted on the turbine inflow housing, in particular the guide apparatus or nozzle ring, can also form as a result of thermal cycles, as a result of which gaps set during operation change between the turbine inflow housing and the diffuser. There is a need for a turbine inflow housing that is less prone to cracking due to thermal cycles. There is also a need to minimize relative movements between the turbine inflow housing and an assembly mounted on the turbine inflow housing as a result of thermal cycles. Proceeding from this, the object of the present invention is to create a new type of turbine inflow housing.
    This object is achieved according to a first aspect of the invention by a turbine inflow housing according to claim 1. According to the first aspect, connecting sections of the ribs, with which they engage on the outer wall of the turbine inflow housing, are positioned in the region of the flange on the flow inlet side.
    This object is achieved according to a second aspect of the invention by a turbine inflow housing according to claim 5. According to the second aspect, the ribs have a drop-shaped contour in cross section.
    This object is achieved according to a third aspect of the invention by a turbine inflow housing according to claim 7. According to the third aspect, flow-leading surfaces of the ribs, which extend between an inflow side and an outflow side of the respective rib and between the outer wall and the inner wall, are contoured in such a way that they diverging from the inflow side in the direction of turning points of the rib contour and then, starting from the turning points, converge towards the outflow side, a ratio d / l between the distance d of the flow-guiding surfaces in the area of the turning points and the distance I from the inflow side and outflow side being greater than 0.4 and less than 1.0.
    [0010] The above aspects of the invention can be used either alone or preferably in combination with one another. So two or three of the above aspects can be used in combination. With all three aspects, the risk of cracks forming on the turbine inflow housing can be reduced. Furthermore, the risk of a relative movement between the turbine inflow housing and an assembly mounted on the turbine inflow housing is minimized. The turbine inflow housing according to the invention can withstand a large number of thermal load change cycles.
    Preferred further 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:
    CH 714 062 A2
    1 shows an axial section through an inventive turbine inflow housing of an axial turbine of a turbocharger.
    Fig. 1 shows a turbine inflow housing 10 of an axial turbine of a turbocharger. Such a turbine inlet housing 10 has an end on the inlet side with a flange 11 on the inlet side and an end on the outlet side with a flange 12 on the outlet side.
    At the flow inlet end, medium, which is to be relaxed in the area of the axial turbine, enters the turbine inflow housing 10. At the end on the flow exit side, this medium emerges from the turbine inflow housing 10 in the axial direction in order to then be fed in the axial direction to a turbine rotor of the axial turbine. An outlet direction of the medium in the region of the end 12 on the flow outlet side accordingly runs in the axial direction of the axial turbine. The section of FIG. 1 through the turbine inflow housing 10 shown in FIG. 1 is therefore also referred to as an axial section.
    The turbine inflow housing 10 has an outer wall 13 and an inner wall 14. At the flow inlet end of the turbine inflow housing 10, the outer wall 13 defines an inlet flow duct 15 of the turbine inflow housing 10 which is circular in cross section. At the flow outlet end, the outer wall 13 together with the inner wall 14 defines an outlet flow channel 16 of the turbine inflow housing 10 which is circular in cross section.
    In the area of the flow inlet end, the circular flow channel 15 in cross section is defined by the outer wall 13 and in the area of the flow outlet end, the annular flow channel 16 is defined by the outer wall 13 and the inner wall 14. The inner wall 14 is also referred to as a bell.
    Ribs 15 extend between the outer wall 13 and the inner wall 14, the inner wall 14 being connected to the outer wall 13 via the ribs 17. The ribs 17 run in the flow channel between the annular, outlet-side flow channel 16 and the circular, inlet-side flow channel 15. The ribs 17 are surrounded by the medium which flows through the turbine inflow housing 10. The ribs 17 around which the medium flows have an inflow side 21, an outflow side 20 and flow-guiding surfaces 18, 19 extending between the outflow side 20 and the inflow side 21.
    According to a first aspect of the invention, it is provided that connection sections 22 of the ribs 17, with which the ribs 17 engage on the outer wall 13 of the turbine inflow housing 10, are positioned in the region of the flange 11 on the flow inlet side and in the region of the flange 11 on the flow inlet side extend into it. The connecting section 22 of the ribs on the outer wall 13 is thus displaced into the region of the end on the flow inlet side and thus of the flange 11 of the turbine inflow housing 10 on the flow inlet side.
    That connecting portion 26 of the ribs 17, over which the ribs 17 engage on the inner wall 14, is positioned closer to the flow outlet end of the turbine inflow housing 10 than at the flow inlet end of the turbine inflow housing.
    The ribs 17 are seen in the axial section of FIG. 1 axially inclined relative to a radial direction 23, in such a way that a longitudinal central axis 24 of the respective ribs 17 includes an angle a with the radial direction 23, which is between 45 ° and 85 ° , preferably between 60 ° and 80 °, particularly preferably between 60 ° and 70 °. As a result, the ribs 17 have a relatively small height, and thus radial extension, when viewed in the radial direction.
    With these features, the thermal stability and thus the life of the turbine inflow housing 10 can be increased. The risk of crack formation in the area of the ribs 17 is reduced. The crack propagation behavior is also minimized. The risk of a relative movement between the turbine inflow housing and an assembly mounted on the turbine inflow housing is also reduced.
    According to a second aspect of the invention, which is preferably used in combination with the first aspect of the invention, the ribs 17 are contoured in cross-section (see detail II of FIG. 1, which shows the cross section II-II). The ribs 17 are preferably contoured in a drop shape such that the flow-guiding surfaces 18, 19 of the ribs 17 initially diverge from the inflow side 21 in the direction of turning points 25 of the teardrop-shaped surfaces 18, 19 and then proceed from these turning points 25 in the direction of the The outflow side 20 converge, the distance between the turning points 25 from the outflow side 20 being greater than from the inflow side 21. The turning points 25 are those points of the flow-guiding surfaces 18, 19 at which the diverging profile of the same converges into the converging profile. This provides a particularly advantageous flow guidance in the area of the ribs 17, in particular the flow is gently combined downstream of the ribs 17. Shading effects are minimized.
    According to a third aspect of the invention, which can be used in combination with the first aspect or the second aspect or the first and second aspects, it is provided that a ratio d / l between the distance between the flow-guiding surfaces 18, 19 in The range of the turning points 25 and the distance I from the inflow side 21 and the outflow side 20 is greater than 0.4 and less than 1.0, preferably greater than 0.5 and less than 0.9, particularly preferably greater than 0.6 and less than 0.8.
    CH 714 062 A2 If the ribs 17 are characterized by such a ratio d / l, they have a strong thickening, as a result of which the thermal stability and thus the service life of the turbine inflow housing 10 are increased. The risk of crack formation in the area of the ribs 17 is reduced. The crack propagation behavior is also minimized. The risk of a relative movement between the turbine inflow housing and an assembly mounted on the turbine inflow housing is also reduced.
    The present invention accordingly proposes a novel turbine inflow housing 10 for an axial turbine of a turbocharger. All aspects according to the invention serve to reduce the risk of cracking as a result of thermal load change cycles. Furthermore, a minimized crack propagation behavior can be provided. The turbine inflow housing 10 can withstand a variety of thermal load cycling cycles. There is no risk of relative movement between the turbine inflow housing and an assembly mounted on the turbine inflow housing. Furthermore, homogeneous flow guidance can be provided for a subsequent guide vane without the risk of vibration excitation.
    LIST OF REFERENCE NUMERALS [0025]
    Turbine inflow housing, flow inlet flange, flow outlet flange outer wall inner wall circular inlet flow channel annular outlet flow channel
    Rib flow-guiding surface
    outflow
    inflow
    connecting section
    radial direction
    Longitudinal central axis
    turning point
    connecting section
    权利要求:
    Claims (11)
    [1]
    claims
    1. Turbine inflow housing (10) of an axial turbine of a turbocharger, with a flange (11) on the flow inlet side at an end (11) on the flow inlet side, on which an outer wall (13) of the turbine inflow housing defines an inlet flow channel (15) of circular cross section, with a flange on the flow outlet side (11) at an end (12) on the flow outlet side, at which the outer wall (13) of the turbine inflow housing and an inner wall (14) of the same define an outlet flow channel (16) with a circular cross-section, with ribs (17) via which the outer wall (13) of the turbine inflow housing and the inner wall (14) of the same are connected to one another, characterized in that
    Connection sections (22) of the ribs (17), with which they engage on the outer wall (13) of the turbine inflow housing, are positioned at least in sections in the region of the flange (11) on the flow inlet side.
    CH 714 062 A2
    [2]
    2. Turbine inflow housing according to claim 1, characterized in that the connecting portions (22) of the ribs (17), with which they engage on the outer wall (13) of the turbine inflow housing, extend to the flow inlet flange (11).
    [3]
    3. Turbine inflow housing according to claim 1 or 2, characterized in that the ribs (17) seen in an axial section are axially inclined with respect to a radial direction (23).
    [4]
    4. Turbine inflow housing according to claim 3, characterized in that seen in the axial section a longitudinal central axis (24) of the respective rib (17) with the radial direction (23) an angle (a) between 45 ° and 85 °, preferably between 60 ° and 80 °, particularly preferably between 60 ° and 70 °.
    [5]
    5. Turbine inflow housing according to one of claims 1 to 4, characterized in that the same is further developed according to one of claims 6 to 10.
    [6]
    6. Turbine inflow housing (10) of an axial turbine of a turbocharger, with a flange (11) on the flow inlet side at an end (11) on the flow inlet side, on which an outer wall (13) of the turbine inflow housing defines an inlet flow channel (15) of circular cross section, with a flange on the flow outlet side (11) at an end (12) on the flow outlet side, at which the outer wall (13) of the turbine inflow housing and an inner wall (14) of the same define an outlet flow channel (16) with a circular cross-section, with ribs (17) via which the outer wall (13) of the turbine inflow housing and the inner wall (14) thereof are connected to one another, characterized in that the ribs (17) are contoured in the shape of a drop in cross section.
    [7]
    7. Turbine inflow housing according to claim 6, characterized in that flow-guiding surfaces (18, 19) of the ribs (17), which are located between an inflow side (21) and an outflow side (20) of the respective rib (17) and between the outer wall ( 13) and the inner wall (14), which define the drop contour of the ribs (17).
    [8]
    8. Turbine inflow housing according to claim 7, characterized in that the flow-guiding surfaces (18, 19) of the ribs (17) first diverge starting from the inflow side (21) in the direction of turning points (25) of the drop contour and then starting from the turning points (25 ) converge towards the outflow side (20), the distance between the turning points (25) from the outflow side (20) being greater than from the upstream side (21).
    [9]
    9. Turbine inflow housing (10) of an axial turbine of a turbocharger, with a flange (11) on the flow inlet side at an end (11) on the flow inlet side, on which an outer wall (13) of the turbine inflow housing defines an inlet flow channel (15) of circular cross section, with a flange on the flow outlet side (11) at an end (12) on the flow outlet side, at which the outer wall (13) of the turbine inflow housing and an inner wall (14) thereof define an outlet flow channel (16) with a circular cross-section, with ribs (17) via which the outer wall (13) of the turbine inflow housing and the inner wall (14) thereof are connected to one another, characterized in that flow-guiding surfaces (18, 19) of the ribs (17), which are located between an inflow side (21) and an outflow side (20) of the respective Rib (17) and between the outer wall (13) and the inner wall (14) extend, first diverging from the inflow side (21) in the direction of turning points (25) of the rib contour and then converging starting from the turning points (25) in the direction of the outflow side, with a ratio d / l between the distance d of the flow-guiding surfaces (18, 19) in the area of the turning points (25) and the distance I from the inflow side (21) and outflow side (20) is greater than 0.4 and less than 1.0.
    [10]
    10. Turbine inflow housing according to claim 9, characterized in that the ratio d / l is greater than 0.5 and less than 0.9.
    [11]
    11. Turbine inflow housing according to claim 9, characterized in that the ratio d / l is greater than 0.6 and less than 0.8.
    CH 714 062 A2
    类似技术:
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    同族专利:
    公开号 | 公开日
    KR20190015107A|2019-02-13|
    DE102017117783A1|2019-02-07|
    JP2019031972A|2019-02-28|
    CN109386312A|2019-02-26|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    EP0575659A1|1992-06-26|1993-12-29|Asea Brown Boveri Ag|Inlet casing for a steam turbine|
    CN201090252Y|2007-07-06|2008-07-23|大连经济技术开发区泽通机械有限公司|Improvement of turbine inlet casing dowel plate of axial-flow turbine supercharger|
    DE102009041223B4|2009-09-11|2014-01-02|Man Diesel & Turbo Se|Method for designing a drive system|
    US8672620B2|2010-08-17|2014-03-18|Hamilton Sundstrand Corporation|Air turbine starter turbine nozzle airfoil|
    US20130180245A1|2012-01-12|2013-07-18|General Electric Company|Gas turbine exhaust diffuser having plasma actuator|
    DE202014002981U1|2014-04-08|2014-04-16|Man Diesel & Turbo Se|Axial turbine for an exhaust gas turbocharger|
    US11268394B2|2020-03-13|2022-03-08|General Electric Company|Nozzle assembly with alternating inserted vanes for a turbine engine|
    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    DE102017117783.3A|DE102017117783A1|2017-08-04|2017-08-04|Turbine inlet housing of an axial turbine of a turbocharger|
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