• 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. The ribs (17) point between flow-guiding surfaces (18, 19) of the same 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) ), a mean distance which is at least 1.5 times a thickness (s) of the outer wall (13) of the Turbinenzuströmgehäuses.
    公开号:CH714150A2
    申请号:CH00806/18
    申请日:2018-06-26
    公开日:2019-03-15
    发明作者:Matthias Köhler；Sebastian Spengler
    申请人:Man Diesel & Turbo Se；
    IPC主号:
    专利说明:

    Description [0001] The invention relates to a turbine inlet housing of an axial turbine of a turbocharger.
    A turbocharger has a turbine for relaxing 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 compressor of the turbocharger has a compressor housing and a compressor rotor. The turbine rotor and the compressor rotor are connected to each other via a shaft which is rotatably mounted in a bearing housing of the turbocharger. The bearing housing of the turbocharger 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. Likewise, the compressor of a turbocharger may be designed as an axial compressor or as a centrifugal compressor. The present invention relates to a Turbinenzuströmgehäuse the turbine housing of a designed as an axial turbine turbine of a turbocharger.
    From DE 20 2014 002 981 U1 the basic structure of an axial turbine of a turbocharger is known. Thus, this prior art shows in detail the turbine rotor of the turbine together with the Turbinenzuströmgehäuse the turbine housing. In this case, DE 20 2014 002 981 U1 shows the flow exit-side end of the turbine inlet housing, on which the turbine inlet housing, namely a radially inner wall and a radially outer wall thereof, define a flow channel of annular cross-section. About this annular flow channel to be relaxed medium to the turbine rotor of the axial turbine can be fed.
    According to DE 20 2014 002 981 U1, a nozzle ring is positioned between the turbine rotor and the outlet end of the Turbinenzuströmgehäuses. The nozzle ring is also referred to as a nozzle or guide grid.
    From practice, it is known that the radially inner wall of the Turbinenzuströmgehäuses and the radially outer wall thereof are connected to each other via ribs which extend through the annular flow channel at the flow outlet end of Turbinenzuströmgehäuses. These ribs are surrounded by the medium which is to be supplied to the turbine rotor.
    Turbine induction housings known from practice are susceptible to cracking due to thermal cycling. As a result, the life of a Turbinenzuströmgehäuses is limited. In addition to the formation of cracks, there is the problem in turbine inlet cases known from practice that a relative movement between the turbine inlet housing and a module mounted on the turbine inlet housing, in particular the nozzle or nozzle ring, can likewise be formed as a result of thermal cycles, whereby gaps then set in operation change between the Turbinenzuströmgehäuse and the nozzle. There is a need for a turbine inlet housing which is less susceptible to cracking due to thermal cycling. Further, there is a need to minimize thermal motion forming relative movements between the turbine inlet housing and an assembly mounted on the turbine inlet housing.
    On this basis, the present invention has the object to provide a novel Turbinenzuströmgehäuse.
    This object is achieved according to a first aspect of the invention by a Turbinenzuströmgehäuse according to claim 1.
    According to the first aspect, the fins between the flow-guiding surfaces thereof, the between an upstream side and a downstream side of the respective rib and between the outer wall and the inner wall, a mean distance, the minimum of 1.5 times a Thickness of the outer wall of Turbinenzuströmgehäuses corresponds. This mean distance between the flow-guiding surfaces of the ribs determines the thickness of the ribs. Such ribs can reduce cracking on the turbine inlet housing due to thermal cycling. Furthermore, the risk of relative movement between the turbine inlet housing and an assembly mounted on the turbine inlet housing can be minimized.
    This object is achieved according to a second aspect of the invention by a Turbinenzuströmgehäuse according to claim 6.
    According to the second aspect, the ribs are seen in an axial section relative to the radial direction axially inclined. This tendency of the ribs also minimizes the risk of cracking and relative movement between the turbine inlet housing and an assembly mounted thereon.
    This object is achieved according to a third aspect of the invention by a Turbinenzuströmgehäuse according to claim 9.
    According to the third aspect, the ribs are seen in Axialblickrichtung tangentially inclined relative to the radial direction. Also, this inclination of the ribs serves to minimize cracking as well as minimizing relative movement between the turbine inlet housing and a subassembly mounted thereto due to thermal cycling.
    This object is achieved according to a fourth aspect of the invention by a Turbinenzuströmgehäuse according to claim 12.
    According to the fourth aspect, the ribs go into the outer wall and into the inner wall with a transition radius, which rotates unevenly around the respective rib in the region of the outer wall and in the region of the inner wall. This can be used to minimize the risk of cracking and relative movement due to thermal cycling.
    This object is achieved according to a fifth aspect of the invention by a Turbinenzuströmgehäuse according to claim 15.
    According to the fifth aspect adjacent to a region in which the ribs pass into the inner wall, formed on a side facing away from the ribs side of the inner wall connecting portions for a guide grid. The connection sections for the guide grid or the nozzle or the nozzle ring are particularly advantageous in order to minimize a relative movement between Turbinenzuströmgehäuse and guide grid due to thermal cycles. However, they are also advantageous in minimizing the risk of cracking due to thermal cycling.
    The above five aspects of the invention may be used either alone or preferably in combination with each other. Thus, two of the above five aspects, three of the above five aspects, four of the above five aspects, or even all five aspects can be used in combination. Particularly preferred is an embodiment of Turbinenzuströmgehäuses, in which the first aspect, the second aspect, the third aspect and the fourth aspect, so the defined thickness of the ribs with the inclination of the ribs and the non-uniform circumferential radii is combined.
    Preferred embodiments of the invention will become apparent from the dependent claims and the description below. Embodiments of the invention will be described, without being limited thereto, with reference to the drawings. Showing:
    1 shows an axial section through an inventive Turbinenzuströmgehäuse an axial turbine of a turbocharger,
    2 is a view in the viewing direction II of Fig. 1,
    Fig. 3 is a sectional view on the level III-III of FIG. 1.
    Fig. 1 shows a Turbinenzuströmgehäuse 10 of an axial turbine of a turbocharger. Such Turbinenzuströmgehäuse 10 has a strömungseintrittsseitiges end 11 and a flow exit side end 12. At the flow inlet side end 11 occurs medium, which is to be relaxed in the region of the axial turbine, in the Turbinenzuströmgehäuse 10 a. At the flow exit-side end 12, this medium exits from the turbine inlet housing 10 in the axial direction, in order then to 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 outlet end 12 extends accordingly in the axial direction of the axial turbine. Therefore, the section of Fig. 1 is referred to by the Turbinenzuströmgehäuse 10 shown in Fig. 1 also as an axial section.
    The Turbinenzuströmgehäuse 10 has an outer wall 13 and an inner wall 14. The outer wall 13 defines at the flow inlet-side end 11 of the Turbinenzuströmgehäuses 10 a circular cross-sectional flow channel 15 of Turbinenzuströmgehäuses 10. At the flow exit end 12 defines the outer wall 13 together with the inner wall 14 in cross-section circular flow channel 16 of Turbinenzuströmgehäuses 10th
    In the embodiment shown in Fig. 1, the Turbinenzuströmgehäuse 10 is designed in manifold construction. The inlet direction of the flow in the region of the flow inlet-side end 11 is offset from the outlet direction of the flow in the region of the flow outlet-side end 12 by 90 °. In the exemplary embodiment shown in FIG. 1, therefore, the flow of the medium to be supplied to the turbine rotor is deflected by 90 °.
    However, the invention is not limited to Turbinenzuströmgehäuse in manifold construction. In a Turbinenzuströmgehäuse, which is not designed in manifold construction, extend both the flow inlet direction in the region of the flow inlet end 11 and the flow direction in the region of the flow outlet end 12 of the Turbinenzuströmgehäuses in the axial direction.
    In any case, in the region of the flow inlet end 11 of the circular flow channel 15 is defined by the outer wall 13 and in the region of the flow outlet end 12 of the annular flow channel 16 through the outer wall 13 and the inner wall 14.
    The inner wall 14 is also referred to as a bell.
    In the region of the flow outlet end 12, ie where the outer wall 13 and the inner wall 14 define the annular flow channel 16 of Turbinenzuströmgehäuses 10, extending ribs 17, wherein the ribs 17, the outer wall 13 and the inner wall 14th connect together and extend through the annular flow channel 16. Accordingly, the ribs 17 are surrounded by the medium through which the turbine inlet housing 10 flows.
    Fig. 2 shows the Turbinenzuströmgehäuse 10 in the viewing direction II of Fig. 1. The viewing direction II of Fig. 1 extends in the axial direction. In FIG. 2, therefore, the viewing direction is directed into the annular flow channel 16 in the region of the flow exit-side end 12 of the turbine inlet housing 10.
    According to a first aspect of the present invention, the ribs 17 between flow-guiding surfaces 18, 19 thereof, which extend between an inflow side 21 and a downstream side 20 of the respective rib 17 and between the walls 13,14, a mean distance and thus having an average thickness which is at least 1.5 times a thickness s of the outer wall 13. Preferably, the mean distance between the flow-guiding surfaces 18, 19 of the ribs 17 and thus the thickness of the same between 1.5 times and 3.0 times the thickness s of the outer wall 13 of Turbinenzuströmgehäuses 10. Particularly preferred is an expression of the first aspect of the invention, in which the average distance between the flow-guiding surfaces 18, 19 of the ribs 17 and thus the average thickness thereof is at least 1.6 times the thickness s of the wall 13 of the Turbinenzuströmgehäuses 10. Most preferably, the mean distance between the flow-guiding surfaces 18, 19 of the ribs 17 and thus the average thickness of the same between 1.6 times and 2.6 times the thickness s of the outer wall 13 of Turbinenzuströmgehäuses 10th
    3, the ribs 17 are rounded adjacent to the inflow side 21 and outflow side 20, so that the distance BRAn between the flow-guiding surfaces 18,19 in the region of the inflow side 21 and the distance BRAb between the flow-guiding surfaces 18th , 19 in the region of the downstream side 20 is smaller than the distance BRn between the flow-guiding surfaces 18, 19 in the middle of the length LRn of the rib, wherein the length LRm of the rib corresponds to the distance between the inflow side 21 and outflow side 20.
    As can be seen in FIGS. 1 and 2, the ribs 17 are preferably designed such that the ribs 17, starting from the outer wall 13 in the direction of the inner wall 14 taper and seen both in Axialblickrichtung II (see Fig. 2) as well as in axial section seen (see Fig. 1).
    Seen in axial section (see Fig. 1) adjacent to the outer wall 13, the distance between the inflow side 21 and the outflow side 20 of the respective rib 17 and thus the length LRm of the rib to the dimension b and adjacent to the radially inner wall 14 corresponds this distance between the inflow side 21 and the outflow side 20 of the respective rib 17 and thus the length LRn of the rib to the dimension a.
    Fig. 2 it can be seen that the distance BRm of Fig. 3 between the flow-guiding surfaces 18, 19 of the respective rib 17 adjacent to the outer wall 13 to the dimension d and adjacent to the inner wall 14 corresponds to the dimension c. The following applies: b> a and d> c.
    It follows that the ribs 17 accordingly taper starting from the outer wall 13 in the direction of the inner wall 14, preferably continuously, both based on the distance BRm between the flow-guiding surfaces 18, 19 of the ribs 17 as well based on the distance LRm between the inflow side 21 and the outflow side 20 of the ribs 17th
    Therefore, in connection with the first aspect of the invention, reference is also made to the mean distance between the flow-guiding surfaces 18 and 19 of the respective rib 17, wherein the average distance and thus the average thickness of the respective rib 17 0.5 * ( c + d) is.
    With the average thickness of the respective rib 17 defined above, the risk of cracking due to thermal cycling can be reduced. As a result, the life of the Turbinenzuströmgehäuses 10 is increased. Between the inner wall 14, the outer wall 13 and the ribs 17, a homogeneous stress and deformation distribution can be ensured in thermal cycles. Furthermore, a relative movement between the Turbinenzuströmgehäuse 10 and a mounted on the same assembly, such as a nozzle or a nozzle ring, can be minimized, in turn, indicated by thermal cycles relative movement between these assemblies.
    According to a second aspect of the invention, which is preferably used in combination with the above-described first aspect of a Turbinenzuströmgehäuse 10, the ribs 17 are seen in the axial section of FIG. 1 viewed from the radial direction 23 axially inclined.
    1, that viewed in the axial section of Fig. 1 between the radial direction 23 and a longitudinal center axis 24 of the rib 17, an angle α is formed which defines the axial inclination of the rib 17 in axial section relative to the radial direction 23.
    This angle α is preferably between 20 ° and 80 °, preferably between 20 ° and 70 °, more preferably between 20 ° and 60 °, most preferably between 30 ° and 40 °.
    In the case of the turbine inlet housing 10 shown in FIGS. 1 and 2, a rib-specific and thus rib-specific angle α is provided in the region of each rib 17, with which the respective longitudinal central axis 24 of the respective rib 17 is inclined to the radial direction 23, in such a way in that the ribs 17 have the same or approximately the same rib heights RHm between the outer wall 13 and the inner wall 14.
    The above details of the second aspect of the invention, as well as the details of the first aspect of the invention, serve to reduce the risk of cracking of the turbine inlet housing 10 due to thermal cycling. It can be a uniform, homogeneous stress and deformation distribution between outer wall 13, inner
    Wall 14 and the ribs 17 are provided. Furthermore, the risk is reduced that, as a result of thermal cycles, a relative movement is formed between the turbine inlet housing 10 and a distributor or nozzle ring mounted on the turbine inlet housing 10.
    According to a third aspect of the invention, which is preferably used in combination with the above-described first aspect and the above-described second aspect of the invention on a Turbinenzuströmgehäuse 10, the ribs 17 are also seen in Axialblickrichtung II (see FIG. 2) tangentially inclined with respect to the radial direction 23.
    FIG. 2 shows an angle β for the upper rib 17 in FIG. 2, which encloses the longitudinal central axis 24 of the rib 17 with the radial direction 23. This angle β is between 5 ° and 30 °, preferably between 5 ° and 20 °, more preferably between 10 ° and 15 °.
    Through each of the ribs 17, an axis extending in the radial direction 23 can be pulled, which cuts in the region of the respective rib 17 with the longitudinal central axis 24 of the same, in particular in the transition region of the respective rib 17 to the inner wall 14. The angle ß, the respective longitudinal central axis 24 of the respective rib 17 with this extending through the respective rib 17 radial direction 23 encloses, therefore, is preferably in the above-mentioned angle ranges for the angle ß.
    Seen in the axial direction of FIG. 2, the longitudinal center axes 24 intersect of two ribs 17 at individual intersections. There is no common point of intersection for all longitudinal central axes L of all ribs 17.
    Also, the details of the third aspect of the invention reduce the risk of cracking and relative movement due to thermal cycling. In particular, a homogeneous stress and deformation distribution between the outer wall 13, inner wall 14 and ribs 17 is ensured.
    Then, as shown in the figures, the Turbinenzuströmgehäuse 10 is designed in a manifold construction, are the lower ribs 17, namely the intersections between the respective longitudinal center axes 24 of the lower ribs 17 and the outer wall 13, approximately at the same height , Transition regions of the lower ribs 17 to the outer wall 13 are thus seen in the vertical direction, not offset from each other, but positioned in the vertical position as seen in the vertical direction approximately at the same vertical position.
    According to a fourth aspect of the present invention, which is preferably used in combination with the three aspects of the invention described above at Turbinenzuströmgehäuse 10, go the ribs 17 in the outer wall 13 with a transition radius Ra and in the inner wall fourteenth with a transition radius R, over which in the region of the outer wall 13 and in the region of the inner wall 14 each unevenly revolves around the respective rib 17. Thus, in the region of the outer wall 13, the transition radius RaAn adjacent to the inflow side 21 of the respective rib 17 is smaller than the transition radius RaAb adjacent to an outflow side 20 thereof. The following applies: RaAn <RaAb- In the region of the inner wall 14, the transition radius RiAn adjacent the inflow side 21 of the respective rib 17 is greater than the transition radius RiAb adjacent to an outflow side 20 thereof. Thus, RiAn> RiAb In a fifth aspect of the present invention, which is preferably used in combination with the four aspects of the invention described above on the turbine inlet housing 10, is adjacent to the regions in which the ribs 17 engage on the inner wall 14 and pass into the same, formed on a side facing away from the respective rib 17 side of the inner wall 14, a connection portion 22 for fixing a guide grid or nozzle or nozzle ring on Turbinenzuströmgehäuse 10. In particular, these attachment portions 22 adjacent the transition region of the ribs 17 to the inner wall 14 in combination with the other details of the invention described above reduce the risk of relative movement between the turbine inlet housing 10 and a nozzle mounted thereto due to thermal cycling. Discontinued games and gaps between Turbinenzuströmgehäuse 10 and nozzle ring remain unchanged and are subject to lesser changes or none due to thermal cycles.
    By the above-described aspects of the invention alone or preferably in combination thereof can be achieved that a Turbinenzuströmgehäuse is exposed to a significantly reduced risk of cracking due to thermal cycling. As a result, longer service life can be achieved and maintenance intervals can be increased. An elastic overall structure with smaller jumps in stiffness is provided, whereby a homogeneous stress and deformation distribution between outer wall 13, inner wall 14 and ribs 17 due to thermal cycles is ensured. The inner wall 14 undergoes a similar deformation behavior as the outer wall 13. In particular, components attached to the turbine inlet housing, such as a nozzle, are prevented from relatively shifting due to thermal cycles to the turbine inlet housing, so that clearance and gaps remain and less variation or undergo any change due to thermal cycling.
    The ribs 17 may be designed as hollow ribs. Then, when the ribs 17 are hollow, weight can be saved, further can be performed by the same cooling medium.
    权利要求:
    Claims (16)
    [1]
    1. turbine inlet housing (10) of an axial turbine of a turbocharger, with a flow inlet end (11) on which an outer wall (13) of Turbinenzuströmgehäu-ses a circular cross-section flow channel (15) defined, with a flow outlet end (12) at in which the outer wall (13) of the Turbinenzuströmgehäu-ses and an inner wall (14) thereof define a circular annular flow channel (16), with ribs (17), via which the outer wall (13) of Turbinenzuströmgehäuses and the inner wall ( 14) thereof, characterized in that the ribs (17) between flow-guiding surfaces (18,19) thereof between an upstream side (21) and a downstream side (20) of the respective rib (17) and between the outer Wall (13) and the inner wall (14) extend, have an average distance which is at least 1.5 times a thickness of the äusse ren wall (13) of Turbinenzuströmgehäuses corresponds.
    [2]
    2. turbine inlet housing according to claim 1, characterized in that the mean distance between the flow-guiding surfaces (18, 19) of the ribs (17) between 1.5 times and 3.0 times the thickness of the outer wall (13) of the Turbine inlet housing corresponds.
    [3]
    3. Turbinenzuströmgehäuse according to claim 1 or 2, characterized in that the average distance between the flow-guiding surfaces (18, 19) of the ribs (17) minimally 1.6 times the thickness of the outer wall (13) of Turbinenzuströmgehäuses corresponds.
    [4]
    4. turbine inlet housing according to one of claims 1 to 3, characterized in that the mean distance between the flow-guiding surfaces (18, 19) of the ribs (17) between 1.6 times and 2.6 times the thickness of the outer wall (13).
    [5]
    5. Turbinenzuströmgehäuse according to one of claims 1 to 4, characterized in that the same is further developed according to one of claims 6 to 15.
    [6]
    6. Turbinenzuströmgehäuse (10) an axial turbine of a turbocharger, with a flow inlet end (11) on which an outer wall (13) of Turbinenzuströmgehäuses a circular in cross-section flow channel (15) defined, with a flow outlet end (12) to which the outer wall (13) of the Turbinenzuströmgehäuses and an inner wall (14) thereof define a circular in cross-section flow channel (16), with ribs (17), via which the outer wall (13) of Turbinenzuströmgehäuses and the inner wall (14) of the same are connected, characterized in that the ribs (17) seen in an axial section relative to a radial direction (23) are axially inclined.
    [7]
    7. Turbinenzuströmgehäuse according to claim 6, characterized in that in the axial section seen a longitudinal center axis (24) of the respective rib (17) with the radial direction (23) an angle (a) between 20 ° and 80 °, preferably between 20 ° and 70 °, more preferably between 20 ° and 60 °, including.
    [8]
    8. Turbinenzuströmgehäuse according to claim 6 or 7, characterized in that seen in the axial section in a manifold construction of Turbinenzuströmgehäuses the longitudinal center axes (24) of the ribs (17) with rib-specific angles (a) relative to the radial direction (23) are axially inclined so that the ribs (17) have the same or approximately the same rib heights between the outer wall (13) and inner wall (14).
    [9]
    9. Turbinenzuströmgehäuse (10) an axial turbine of a turbocharger, with a strömungseintrittsseitigen end (11) on which an outer wall (13) of Turbinenzuströmgehäuses a circular in cross-section flow channel (15) defined, 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), with ribs (17), via which the outer wall (13) of Turbinenzuströmgehäuses and the inner wall (14) of the same are connected, characterized in that the ribs (17) seen in Axialblickrichtung are tangentially inclined relative to a radial direction (23).
    [10]
    10. Turbinenzuströmgehäuse according to claim 9, characterized in that viewed in Axialblickrichtung a longitudinal center axis (24) of the respective rib (17) with the radial direction (23) an angle (ß) between 5 ° and 30 °, preferably between 5 ° and 20 ° , more preferably between 10 ° and 15 °, includes.
    [11]
    11. Turbinenzuströmgehäuse according to claim 9 or 10, characterized in that the longitudinal central axes (24) of two respective ribs (17) intersect at individual points of intersection.
    [12]
    12 Turbinenzuströmgehäuse (10) of an axial turbine of a turbocharger, with a flow inlet end (11) on which an outer wall (13) of Turbinenzuströmgehäuses a circular in cross-section flow channel (15) defined, with a flow outlet end (12) to which the outer wall (13) of the Turbinenzuströmgehäuses and an inner wall (14) thereof define a circular in cross-section flow channel (16), with ribs (17), via which the outer wall (13) of Turbinenzuströmgehäuses and the inner wall (14) of the same are connected, characterized in that the ribs (17) in the outer wall (13) and in the inner wall (14) with a transition radius, in the region of the outer wall (13) and in the region of the inner wall (14) unevenly around the respective rib (17) rotates.
    [13]
    13. Turbinenzuströmgehäuse according to claim 12, characterized in that in the region of the outer wall (13) of the transition radius adjacent to an inflow side (21) of the respective rib (17) is smaller than the transition radius adjacent to a downstream side (20) thereof.
    [14]
    14 Turbinenzuströmgehäuse according to claim 12 or 13, characterized in that in the region of the inner wall (14) of the transition radius adjacent to an inflow side (21) of the respective rib (17) is greater than the transition radius adjacent to a downstream side (20) thereof.
    [15]
    15. Turbinenenzuströmgehäuse (10) an axial turbine of a turbocharger, with a strömungseintrittsseitigen end (11) on which an outer wall (13) of Turbinenzuströmgehäuses a circular in cross-section flow channel (15) defined, 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), with ribs (17), via which the outer wall (13) of Turbinenzuströmgehäuses and the inner wall (14) of the same are connected, characterized in that adjoining a region in which the ribs (17) in the inner wall (14), on a side facing away from the ribs (17) side of the inner wall (14) connecting portions (22) for a Leitgitter are formed.
    [16]
    16. turbine inlet housing according to one of claims 1 to 15, characterized in that the ribs (17) are hollow.
    类似技术:
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    同族专利:
    公开号 | 公开日
    CN109209514A|2019-01-15|
    DE102017114608A1|2019-01-03|
    KR20190003376A|2019-01-09|
    JP2019011758A|2019-01-24|
    引用文献:
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    EP0575659A1|1992-06-26|1993-12-29|Asea Brown Boveri Ag|Inlet casing for a steam turbine|
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    FR3005108B1|2013-04-30|2018-01-05|Safran Helicopter Engines|TURBOMACHINE AIR INTAKE CASTER WASHING DEVICE|
    DE202014002981U1|2014-04-08|2014-04-16|Man Diesel & Turbo Se|Axial turbine for an exhaust gas turbocharger|
    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    DE102017114608.3A|DE102017114608A1|2017-06-30|2017-06-30|Turbine inlet housing of an axial turbine of a turbocharger|
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