JP2016156358A - Turbine and turbo super charger - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a turbine excellent in maintainability with a simple constitution.SOLUTION: In a turbine, a turbine nozzle includes an annular division plate that forms an inner nozzle passage between a nozzle inner ring and the turbine nozzle, and an outer nozzle passage between a nozzle outer ring and the turbine nozzle. An inlet side casing includes: a cylindrical first casing; a second casing that forms a first channel between the first casing and the inlet side casing for introducing exhaust gas to the inner nozzle passage, and a second channel on the outer peripheral side of the first channel for introducing exhaust gas to the outer nozzle passage; and a by-pass pipe that is connected to the first channel on one end side with a first aperture provided on the outer peripheral surface of the second casing in between, and is connected to the second channel on the other end side with a second aperture provided on the outer peripheral surface of the second casing in between. The by-pass pipe is provided with a valve.SELECTED DRAWING: Figure 1

Description

  The present disclosure relates to turbines and turbochargers.

  A turbocharger is known as one means for increasing the thermal efficiency of an internal combustion engine. Patent Document 1 discloses a turbocharger including a turbine driven by exhaust gas discharged from an internal combustion engine.

  In the turbocharger turbine shown in FIGS. 1 to 4 of Patent Document 1, the partition walls (42, 81) are provided between the inner peripheral member (25a) and the outer peripheral member (25b) of the turbine nozzle (25). Is provided.

  For example, in the turbocharger turbine shown in FIGS. 1 and 2 of Patent Document 1, the exhaust gas is led from the exhaust gas passage (26) to the outer peripheral side of the partition wall (42) of the turbine nozzle, and the inside of the partition wall Exhaust gas is led to the peripheral side from the exhaust gas flow path (36). In such a configuration, when the on-off valve (41) provided in the pipe (38) connecting the exhaust gas passage (26) and the exhaust gas passage (36) is closed, the exhaust gas passage (26 When the exhaust gas is guided only to the outer peripheral side of the partition wall from the turbine nozzle and the open valve is opened, the exhaust gas is exhausted from the exhaust gas passage (26) and the exhaust gas passage (36) to the entire area of the turbine nozzle. Is guided.

  Further, in the turbocharger turbine shown in FIGS. 3 and 4 of Patent Document 1, the exhaust gas is led from the exhaust gas passage (76) to the outer peripheral side of the partition wall (81) of the turbine nozzle, and the partition wall The exhaust gas is guided from the exhaust gas flow path (80) to the inner peripheral side. In such a configuration, when the on-off valve (41) provided in the pipe (38) connecting the exhaust gas passage (76) and the exhaust gas passage (80) is closed, the exhaust gas passage (80 ), The exhaust gas is guided only to the inner peripheral side of the partition wall of the turbine nozzle, and the release valve (41) is opened. From the exhaust gas passage (76) and the exhaust gas passage (80), Exhaust gas is guided to the entire area.

  According to the turbocharger turbine shown in FIGS. 1 to 4 of Patent Document 1, the turbine blades are supplied only by the opening / closing operation of the opening / closing valve without providing a rotation mechanism for each nozzle vane in the turbine nozzle. It becomes possible to adjust the flow rate of the exhaust gas to be produced.

Japanese Patent No. 522274

  In the turbocharger turbine described in FIGS. 1 and 2 of Patent Document 1, a pipe (38) connecting the exhaust gas passage (26) and the exhaust gas passage (36) is provided in the radial direction of the turbine rotor. It is provided so as to straddle the space inside the gas inlet casing (27, 51), and it is difficult to access the turbine rotor through the space during maintenance of the turbine. For example, it has been difficult or impossible to mount a rotor locking tool for locking the turbine rotor so as not to rotate through the space to the turbine rotor.

  On the other hand, in the turbocharger turbine described in FIGS. 3 and 4 of Patent Document 1, it is difficult to access the turbine rotor during maintenance of the turbine due to the structure of the gas inlet casing (77, 107). . In addition, the structure of the gas inlet casing is complicated and difficult to disassemble, and there is room for improvement in terms of maintainability.

  The present invention has been made in view of the above-described conventional problems, and an object of the present invention is to provide a turbine having a simple configuration excellent in maintainability and a turbocharger including the turbine. It is.

  (1) A turbine according to at least one embodiment of the present invention includes a turbine rotor provided rotatably, a turbine nozzle provided upstream of a turbine rotor blade of the turbine rotor, and the exhaust gas at the turbine nozzle. A plurality of turbine nozzles arranged along a circumferential direction of the turbine rotor between the nozzle inner ring, the nozzle outer ring, and the nozzle inner ring and the nozzle outer ring. An annular partition plate that is provided at an intermediate position in the blade height direction of the nozzle vane and that forms an inner nozzle passage between the nozzle inner ring and an outer nozzle passage between the nozzle outer ring and the nozzle vane. The inlet-side casing includes a cylindrical first casing and a second casing located on the outer peripheral side of the first casing. A second flow path for guiding the exhaust gas to the outer nozzle passage and a first flow path for guiding the exhaust gas to the inner nozzle passage. Is connected to the first flow path on one end side through a second casing formed on the outer peripheral side of the first flow path, and a first opening provided on the outer peripheral surface of the second casing. A bypass pipe configured to connect to the second flow path on the other end side through a second opening provided on the outer peripheral surface of the casing, and the bypass pipe is provided with a valve. Yes.

  According to the turbine described in (1) above, when the valve provided in the bypass pipe that connects the first flow path and the second flow path is closed, the inner side of the partition plate of the turbine nozzles is closed. The exhaust gas is guided from the first flow path only to the inner nozzle passage. Further, when the valve is opened, the exhaust gas flows from the first flow path to the inner nozzle passage and the exhaust gas is guided from the second flow path to the outer nozzle passage. Therefore, it is possible to adjust the flow rate of the exhaust gas supplied to the turbine rotor blades only by opening and closing the valves without providing a rotation mechanism for each nozzle vane in the turbine nozzle.

  In the turbine described in (1) above, a bypass pipe can be provided on the outer peripheral side of the second casing located on the outer peripheral side of the cylindrical first casing. The first flow path and the second flow path can be communicated with each other with a simple configuration without the bypass pipe straddling the space. Thereby, it becomes easy to access the turbine rotor through the space inside the cylindrical first casing during the maintenance of the turbine. For example, it becomes easy to attach a rotor locking tool for locking the turbine rotor so as not to rotate to the turbine rotor through the space. Thus, a turbine having a simple configuration excellent in maintainability can be realized.

  (2) In some embodiments, in the turbine described in (1) above, at each position in the axial direction of the turbine rotor, the distance between the partition plate and the nozzle inner ring in the radial direction of the turbine rotor is: It is larger than the interval between the partition plate and the nozzle outer ring in the radial direction of the turbine rotor.

  The turbocharger described in FIG. 1 and FIG. 2 of Patent Document 1 includes the partition wall (42) of the turbine nozzle (25) in both the open state and the closed state (41). The exhaust gas flowing through the gap between the tip of the turbine rotor blade and the shroud wall facing the tip has a relatively large effect on the turbine efficiency.

  On the other hand, according to the turbine described in (2) above, the exhaust gas is guided to the outer nozzle passage on the outer peripheral side of the partition plate among the turbine nozzles only when the valve is open, and the valve is closed. Exhaust gas is not guided. For this reason, the influence which the exhaust gas which passes along the clearance gap between the front-end | tip of a turbine rotor blade and the shroud wall facing this front-end | tip has a turbine efficiency fall can be made small. Further, since the interval between adjacent nozzle vanes increases toward the outside in the radial direction of the turbine rotor, the flow area of the turbine nozzle is increased with the opening and closing of the valve even if the interval between the nozzle outer ring and the partition plate is relatively small. It can be changed greatly.

  (3) In some embodiments, in the turbine according to the above (1) or (2), the nozzle outer ring is not joined to the nozzle vane.

  According to the turbine described in the above (3), when the nozzle vanes and the partition plate are welded to each other at the time of manufacture of the turbine nozzle, the nozzle vanes are exposed, that is, the outer peripheral side tip of the nozzle vane is caused by the nozzle outer ring. Since welding can be performed without being surrounded, welding work is facilitated, and the manufacturing cost of the turbine nozzle can be reduced. Further, even during maintenance, the nozzle vane is not surrounded by the nozzle outer ring by exposing the nozzle vane by separating the nozzle outer ring and the nozzle vane from the state where the outer peripheral side tip of the nozzle vane is surrounded by the nozzle outer ring. The portion corresponding to the outer nozzle passage can be easily cleaned.

  (4) In some embodiments, in the turbine according to the above (3), the turbine includes an outlet guide tube for guiding the exhaust gas that has passed through the turbine rotor blade, and the nozzle outer ring includes: The outlet guide tube is configured as a separate part and is fixed to the outlet guide tube.

  According to the turbine described in (4) above, since the nozzle outer ring is constituted by a separate part (separate body) from the outlet guide cylinder, for example, the material of the nozzle outer ring is selected independently of the material of the outlet guide cylinder. It is possible to increase design freedom.

  (5) In some embodiments, in the turbine according to (4), the turbine further includes an outlet side casing for discharging the exhaust gas that has passed through the turbine rotor blade, and the outlet guide tube. Is a blade-side flow channel wall facing the turbine blade, and an outer peripheral side extending from the blade-side flow channel wall to the outer peripheral side of the blade-side flow channel wall and being fixed to the outlet-side casing The nozzle outer ring is provided so as to cover a space formed between the moving blade side flow path wall and the outer peripheral side extending portion.

  According to the turbine described in (5) above, since the nozzle outer ring is provided so as to cover the space formed between the moving blade side flow path wall and the outer peripheral side extending portion, exhaust to the space is performed. It is possible to suppress a decrease in turbine efficiency due to gas entering.

  (6) In some embodiments, in the turbine according to the above (3), the turbine includes an outlet guide tube for guiding the exhaust gas that has passed through the turbine rotor blade, and the nozzle outer ring includes: It comprises a part of the outlet guide tube.

  According to the turbine described in (6) above, since the nozzle outer ring is configured by a part of the outlet guide cylinder (that is, the nozzle outer ring and the outlet guide cylinder are not separate parts), the nozzle outer ring is configured as the outlet guide cylinder. Compared with the case where it comprises with another parts, the number of parts of a turbine can be reduced.

  (7) In some embodiments, in the turbine according to any one of the above (1) to (6), the interval between the partition plate and the nozzle inner ring decreases as the partition plate approaches the turbine rotor blade. So that it is installed diagonally.

  According to the turbine described in (7) above, since the exhaust gas flowing along the partition plate goes inward in the radial direction of the turbine rotor as it goes downstream, the outer periphery of the turbine rotor blade in the state where the valve is opened The amount of exhaust gas passing through the gap between the side tip and the shroud wall facing the tip can be reduced. Thereby, turbine efficiency can be improved.

  (8) A turbocharger according to at least one embodiment of the present invention is a turbocharger including a turbine that is driven by exhaust gas discharged from an internal combustion engine. The turbine according to any one of (7).

  According to the turbocharger described in (8) above, since the turbine is configured by the turbine described in any one of (1) to (7) above, each nozzle vane in the turbine nozzle rotates. Even without providing a mechanism, it is possible to adjust the flow rate of the exhaust gas supplied to the turbine rotor blade only by opening and closing the valve. Further, it is possible to realize a turbocharger with a simple configuration excellent in maintainability.

  According to at least one embodiment of the present invention, a turbine having a simple configuration excellent in maintainability and a turbocharger including the turbine are provided.

It is a figure which shows typically the cross-sectional structure of the turbocharger which concerns on one Embodiment. It is a fragmentary perspective view of the turbine nozzle shown in FIG. It is a fragmentary perspective view which shows structures other than a nozzle outer ring | wheel among the turbine nozzles shown in FIG. It is the schematic diagram which expanded the cross-sectional structure of the turbine nozzle vicinity in the turbocharger shown in FIG. It is a figure which shows typically the cross-sectional structure of the turbocharger which concerns on one Embodiment.

Hereinafter, some embodiments of the present invention will be described with reference to the accompanying drawings. However, the dimensions, materials, shapes, relative arrangements, etc. of the components described in the embodiments or shown in the drawings are not intended to limit the scope of the present invention, but are merely illustrative examples. Absent.
For example, expressions expressing relative or absolute arrangements such as “in a certain direction”, “along a certain direction”, “parallel”, “orthogonal”, “center”, “concentric” or “coaxial” are strictly In addition to such an arrangement, it is also possible to represent a state of relative displacement with an angle or a distance such that tolerance or the same function can be obtained.
For example, an expression indicating that things such as “identical”, “equal”, and “homogeneous” are in an equal state not only represents an exactly equal state, but also has a tolerance or a difference that can provide the same function. It also represents the existing state.
For example, expressions representing shapes such as quadrangular shapes and cylindrical shapes represent not only geometrically strict shapes such as quadrangular shapes and cylindrical shapes, but also irregularities and chamfers as long as the same effects can be obtained. A shape including a part or the like is also expressed.
On the other hand, the expressions “comprising”, “comprising”, “comprising”, “including”, or “having” one constituent element are not exclusive expressions for excluding the existence of the other constituent elements.

  FIG. 1 is a diagram schematically illustrating a cross-sectional configuration of a turbocharger 100 according to an embodiment. FIG. 2 is a partial perspective view of the turbine nozzle shown in FIG.

  In one embodiment, for example, as shown in FIG. 1, the turbocharger 100 includes a turbine 2 that is driven by exhaust gas discharged from an internal combustion engine (not shown) (for example, a marine internal combustion engine or a power generation internal combustion engine). ing. In the turbocharger 100, when the turbine rotor 4 of the turbine 2 is rotated by exhaust gas, a compressor (not shown) connected to the turbine rotor 4 is driven, and fuel gas such as air supplied to the internal combustion engine is supplied. Compressed. The turbine 2 is an axial turbine as shown in FIG.

  As shown in FIG. 1, the turbine 2 includes a turbine rotor 4 rotatably supported by a bearing 78, a turbine nozzle 8 provided on the upstream side of the turbine rotor blade 6 of the turbine rotor 4, and an exhaust to the turbine nozzle 8. An inlet side casing 10 configured to guide gas, an outlet side casing 12 for discharging exhaust gas that has passed through the turbine rotor blade 6, a valve 40, and a control unit 42 are included. The turbine 2 described in the present embodiment is a variable capacity turbine.

  As shown in at least one of FIGS. 1 and 2, the turbine nozzle 8 includes a nozzle inner ring 14, a nozzle outer ring 16 provided concentrically with the nozzle inner ring 14 on the outer peripheral side of the nozzle inner ring 14, a nozzle inner ring 14, and a nozzle outer ring. 16 includes a plurality of nozzle vanes 18 disposed along the circumferential direction of the turbine rotor 4 and an annular partition plate 20. The annular partition plate 20 is provided so as to intersect with each of the nozzle vanes 18 at an intermediate position P1 in the blade height direction of the nozzle vane 18 (the radial direction of the turbine rotor 4). Shared part). The annular partition plate 20 is provided concentrically with the nozzle inner ring 14 and the nozzle outer ring 16, and forms an inner nozzle passage 22 between the nozzle inner ring 14 and an outer nozzle passage with the nozzle outer ring 16. 24 is formed.

  As shown in FIG. 1, the inlet side casing 10 includes a cylindrical first casing 26 (inner casing), a cylindrical second casing 28 (outer casing) located on the outer peripheral side of the first casing 26, and a bypass. Tube 30. The inlet side casing 10 is configured such that exhaust gas flows from an exhaust gas inlet 69 provided in the second casing 28. The second casing 28 forms an annular first flow path 32 for guiding the exhaust gas to the inner nozzle passage 22 between the first casing 26 and an annular shape for guiding the exhaust gas to the outer nozzle passage 24. The second flow path 34 is configured to be formed on the outer peripheral side of the first flow path 32.

  The bypass pipe 30 is connected to the first flow path 32 on one end side through a first opening 36 provided on the outer peripheral surface 28 a of the second casing 28 and provided on the outer peripheral surface 28 a of the second casing 28. It is configured to be connected to the second flow path 34 on the other end side through the second opening 38. The bypass pipe 30 is provided with a valve 40 whose opening and closing is controlled by the control unit 42.

  In the turbocharger 100, when the valve 40 is controlled to be closed by the control unit 42, all of the exhaust gas flowing into the first flow path 32 from the exhaust gas inlet 69 is inward from the first flow path 32. After flowing through the nozzle passage 22 to the turbine rotor blade 6 and passing through the turbine rotor blade 6, it is discharged from the exhaust gas outlet 70 of the outlet side casing 12.

  Further, in the turbocharger 100, when the valve 40 is controlled to be opened by the control unit 42, most of the exhaust gas flowing into the first flow path 32 from the exhaust gas inlet 69 remains as it is in the first flow path. A part of the exhaust gas flowing into the first flow path 32 from the exhaust gas inlet 69 flows into the second flow path 34 through the bypass pipe 30, and is guided to the inner nozzle passage 22 through 32. Guided to the passage 24. Then, the exhaust gas that has passed through the inner nozzle passage 22 and the exhaust gas that has passed through the outer nozzle passage 24 flow to the turbine rotor blade 6 and are discharged from the exhaust gas outlet 70 of the outlet side casing 12 after passing through the turbine rotor blade 6. .

  According to the turbocharger 100, the flow rate of the exhaust gas supplied to the turbine rotor blade 6 is adjusted only by the opening / closing operation of the valve 40 without providing a rotation mechanism for each nozzle vane 18 in the turbine nozzle 8. It becomes possible.

  Further, in the turbocharger 100, since the bypass pipe 30 can be provided on the further outer peripheral side of the second casing 28 located on the outer peripheral side of the cylindrical first casing 26, the inner side of the cylindrical first casing 26 can be provided. The first flow path 32 and the second flow path 34 can be communicated with each other with a simple configuration without the bypass pipe 30 straddling the space 72. Thereby, it becomes easy to access the turbine rotor 4 from the space inside the cylindrical first casing 26 during maintenance of the turbocharger 100. For example, it becomes easy to attach the rotor locking tool 74 for locking the turbine rotor 4 so as not to rotate through the space 72 to the turbine rotor 4. Therefore, the turbocharger 100 including the turbine 2 having a simple configuration excellent in maintainability can be realized.

  In one embodiment, for example, as illustrated in FIG. 1, the cylindrical first casing 26 includes one end side fixing portion 52 that is fixed to the nozzle inner ring 14 with a bolt 76 a on one end side in the axial direction of the turbine rotor 4, The other end side fixing | fixed part 54 fixed to the 2nd casing 28 with the volt | bolt 76b in the other end side in the axial direction of the turbine rotor 4 and the enlarged diameter part 56 are included. The enlarged diameter portion 56 is located between the one end side fixing portion 52 and the other end side fixing portion 54 in the axial direction of the turbine rotor 4, and the inner diameter and outer diameter increase as the distance from the nozzle inner ring 14 in the axial direction of the turbine rotor 4 increases. It is comprised so that it may become.

  According to such a configuration, the fixed state of the other end side fixing portion 54 with respect to the second casing 28 is released (the bolt 76b is removed), and after the second casing 28 is pulled out in the axial direction, the one end side fixing portion with respect to the nozzle inner ring 14 The first casing 26 can be easily removed in the axial direction of the turbine rotor with respect to the nozzle inner ring 14 and the second casing 28 by releasing the fixed state of 52 (removing the bolt 76a). The maintainability is improved.

  In one embodiment, for example, as shown in FIG. 1, the second casing 28 includes a cylindrical first flow path forming portion 58 having a first opening 36, and the first flow path forming portion 58 to the first flow path. And a cylindrical second flow path forming portion 60 that branches and extends to the outer peripheral side of the forming portion 58 and has a second opening 38.

  The cylindrical first flow path forming portion 58 is connected to the one end side connecting portion 62 that is connected to the partition plate 20 at one end side in the axial direction of the turbine rotor 4, and the other in the axial direction of the turbine rotor 4. The other end side fixing | fixed part 64 fixed to the 1st casing 26 with the volt | bolt 76b at the end side. The first flow path forming portion 58 is configured to form the first flow path 32 between the first casing 26 and the first flow path forming portion 58.

  The cylindrical second flow path forming portion 60 is connected to the outlet side casing 12 by a bolt 76c at an end 66 opposite to the branch position P2 branched from the first flow path forming portion 58 in the axial direction of the turbine rotor 4. In addition to being fixed, the second flow path 34 is formed between the first flow path forming portion 58 and the part 68 on the exhaust gas outlet side.

  In one embodiment, for example, in the turbine nozzle 8 shown in FIGS. 1 and 2, the nozzle outer ring 16 is not joined to each of the nozzle vanes 18. Further, in the turbine nozzle 8 shown in FIGS. 1 and 2, the plurality of nozzle vanes 18 are joined to the nozzle inner ring 14 and the partition plate 20 by, for example, welding, and the plurality of nozzle vanes 18, the nozzle inner ring 14 and the partition plate 20 are joined. Integrally form the nozzle ring 21. Thus, the nozzle ring 21 is configured as a separate component (separately) from the nozzle outer ring 16.

  For this reason, when each of the nozzle vanes 18 and the partition plate 20 are welded together during the manufacture of the turbine nozzle 8, the outer peripheral side tip 18a of the nozzle vane 18 is exposed (see FIG. 3), that is, by the nozzle outer ring 16. Since welding can be performed in a state in which the outer peripheral side tip 18a of the nozzle vane 18 is not surrounded, welding work is facilitated, and the manufacturing cost of the turbine nozzle 8 can be reduced.

  Further, during the maintenance, the nozzle outer ring 16 is exposed by separating the nozzle outer ring 16 and the nozzle vane 18 in the axial direction from the state in which the outer peripheral side tip 18a of the nozzle vane 18 is surrounded by the nozzle outer ring 16. Thus, the portion 24a corresponding to the outer nozzle passage 24 can be easily cleaned in a state where the outer peripheral side tip 18a of the nozzle vane 18 is not surrounded (see FIG. 3).

  In one embodiment, for example, as shown in FIG. 1, the turbine 2 includes an outlet guide tube 44 for guiding the exhaust gas that has passed through the turbine rotor blade 6, and the nozzle outer ring 16 is separate from the outlet guide tube 44. It is configured as a part and is fixed to the outlet guide tube 44. For this reason, for example, the material of the nozzle outer ring 16 can be selected independently of the material of the outlet guide tube 44, and the degree of design freedom can be increased.

  In one embodiment, for example, as shown in FIG. 1, the outlet guide tube 44 includes a moving blade side flow path wall 46 facing the turbine rotor blade 6, and an outer peripheral side of the moving blade side flow path wall 46 from the moving blade side flow path wall 46. The nozzle outer ring 16 extends between the rotor blade-side flow path wall 46 and the outer peripheral side extending portion 48. It is provided so as to cover the space 50 to be formed. Thereby, the fall of the turbine efficiency resulting from the entrance of the exhaust gas into the space 50 can be suppressed.

  In one embodiment, for example, as shown in FIG. 4, at each position in the axial direction of the turbine rotor 4, the distance D <b> 1 between the partition plate 20 and the nozzle inner ring 14 in the radial direction of the turbine rotor 4 is the radial direction of the turbine rotor 4. It is larger than the distance D2 between the partition plate 20 and the nozzle outer ring 16.

  The turbocharger described in FIG. 1 and FIG. 2 of Patent Document 1 includes the partition wall (42) of the turbine nozzle (25) in both the open state and the closed state of the on-off valve (41). Since the exhaust gas is configured to flow on the outer peripheral side, the exhaust gas passing through the gap between the tip of the turbine rotor blade and the shroud wall facing the tip has a relatively large effect on the turbine efficiency reduction.

  On the other hand, according to the turbocharger 100 described with reference to FIGS. 1 to 4, only when the valve 40 is opened in the outer nozzle passage 24 on the outer peripheral side of the partition plate 20 in the turbine nozzle 8. When the exhaust gas is guided and the valve 40 is closed, the exhaust gas is not guided. For this reason, the influence which exhaust gas which passes along the crevice between the tip of turbine rotor blade 6 and the shroud wall (the above-mentioned rotor blade side channel wall in exit guide tube 44) 46 which counters the tip has an influence on turbine efficiency fall is made small. Can do. Further, since the interval between the adjacent nozzle vanes 18 increases toward the outside in the radial direction of the turbine rotor 4, the turbine nozzle is opened and closed with the opening and closing of the valve 40 even if the interval between the nozzle outer ring 16 and the partition plate 20 is relatively small. 8 channel area can be greatly changed.

  In one embodiment, for example, as shown in FIG. 4, the partition plate 20 is installed obliquely so that the distance D <b> 1 with the nozzle inner ring 14 in the radial direction of the turbine rotor 4 decreases as the turbine rotor blade 6 is approached. .

  As a result, the exhaust gas flowing along the partition plate 20 is directed toward the inner side in the radial direction of the turbine rotor 4 toward the downstream side. Therefore, in the state where the valve 40 is opened, the outer peripheral side tip and the tip of the turbine rotor blade 6 are opened. It is possible to reduce the amount of exhaust gas passing through the gap between the shroud wall (the above-described moving blade side flow path wall in the outlet guide tube 44) 46 and the shroud wall. Thereby, turbine efficiency can be improved.

  The present invention is not limited to the above-described embodiments, and includes forms obtained by modifying the above-described embodiments and forms obtained by appropriately combining these forms.

  For example, in the embodiment shown in FIG. 1, the nozzle outer ring 16 is configured as a separate part from the outlet guide tube 44 and is fixed to the outlet guide tube 44, but the form of the nozzle outer ring 16 is not limited thereto. Absent. For example, as shown in FIG. 5, the nozzle outer ring 16 may be constituted by a part of the outlet guide tube 44. Thereby, compared with the case where the nozzle outer ring | wheel 16 is comprised as an outlet guide cylinder 44 and another component, a number of parts can be reduced and the structure of the turbo supercharger 100 can be simplified.

  In the embodiment shown in FIG. 1, the form in which the valve 40 is opened and closed by the control unit 42 has been described. However, the valve 40 may be opened and closed manually. Further, in some embodiments, as shown in FIGS. 1 and 5, a heat insulating material 80 may be attached to each of the inlet side casing 10 and the outlet side casing 12.

2 Turbine 4 Turbine rotor 6 Turbine blade 8 Turbine nozzle 10 Inlet side casing 12 Outlet side casing 14 Nozzle inner ring 16 Nozzle outer ring 18 Nozzle vane 20 Partition plate 21 Nozzle ring 22 Inner nozzle passage 24 Outer nozzle passage 26 First casing 28 Second casing 28a outer peripheral surface 30 bypass pipe 32 first flow path 34 second flow path 36 first opening 38 second opening 40 valve 42 control section 44 outlet guide tube 46 rotor blade side flow path wall 48 outer peripheral extending section 50 space 52 One end side fixing portion 54 The other end side fixing portion 56 The diameter increasing portion 58 The first flow path forming portion 60 The second flow path forming portion 62 The one end side connecting portion 64 The other end side fixing portion 66 The end portion 68 Part 69 The exhaust gas inlet 70 Exhaust gas outlet 72 Space 74 Rotor lock tools 76a, 76b, 76c Bolt 78 Bearing 80 Heat insulation material 100 Bo supercharger

Claims (8)

A turbine rotor provided rotatably;
A turbine nozzle provided on the upstream side of the turbine rotor blade of the turbine rotor;
An inlet casing configured to direct exhaust gas to the turbine nozzle;
Including
The turbine nozzle is
Nozzle inner ring,
A nozzle outer ring,
A plurality of nozzle vanes disposed along the circumferential direction of the turbine rotor between the nozzle inner ring and the nozzle outer ring;
The nozzle vane is provided at an intermediate position in the blade height direction so as to intersect each of the nozzle vanes, and an inner nozzle passage is formed between the nozzle inner ring and an outer nozzle passage is formed between the nozzle outer ring and the nozzle outer ring. An annular partition plate;
Including
The inlet side casing is
A cylindrical first casing;
A second casing located on an outer peripheral side of the first casing, wherein a first passage for guiding the exhaust gas to the inner nozzle passage is formed between the first casing and the outer nozzle passage; A second casing for forming a second flow path for guiding the exhaust gas to the outer peripheral side of the first flow path;
The first casing is connected to the first flow path on one end side through a first opening provided on the outer peripheral surface of the second casing, and is connected to the second opening provided on the outer peripheral surface of the second casing. A bypass pipe configured to connect to the second flow path on the other end side;
Including
A turbine provided with a valve in the bypass pipe.   The distance between the partition plate and the nozzle inner ring in the radial direction of the turbine rotor at each position in the axial direction of the turbine rotor is greater than the distance between the partition plate and the nozzle outer ring in the radial direction of the turbine rotor. Item 2. The turbine according to Item 1.   The turbine according to claim 1, wherein the nozzle outer ring is not joined to the nozzle vane. The turbine includes an outlet guide cylinder for guiding the exhaust gas that has passed through the turbine rotor blade,
The turbine according to claim 3, wherein the nozzle outer ring is configured as a separate component from the outlet guide tube and is fixed to the outlet guide tube. The turbine further includes an outlet side casing for discharging the exhaust gas that has passed through the turbine rotor blade,
The outlet guide tube extends from the moving blade side flow path wall to the outer peripheral side of the moving blade side flow path wall and faces the turbine moving blade, and is fixed to the outlet casing. An outer peripheral side extending portion, and
The turbine according to claim 4, wherein the nozzle outer ring is provided so as to cover a space formed between the moving blade side flow path wall and the outer peripheral extending portion. The turbine includes an outlet guide cylinder for guiding the exhaust gas that has passed through the turbine rotor blade,
The turbine according to claim 3, wherein the nozzle outer ring is configured by a part of the outlet guide tube.   The turbine according to any one of claims 1 to 6, wherein the partition plate is installed obliquely so that an interval between the partition plate and the nozzle inner ring becomes smaller as the turbine moving blade is approached.   A turbocharger comprising a turbine driven by exhaust gas discharged from an internal combustion engine, wherein the turbine is the turbine according to any one of claims 1 to 7.

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