JP2020051384A - Turbine and supercharger - Google Patents

Abstract

To reduce exhaust interference.SOLUTION: A turbine includes: a first turbine scroll channel 31a and a second turbine scroll channel 31b which communicate with a storage portion S for storing a turbine wheel 17; s first partition wall 37a which is provided in the first turbine scroll channel 31a, disposes one end 37aa at a position where a channel cross-sectional area becomes minimum in a part facing a second tongue portion 35b of the first turbine scroll channel 31a, and arranges the other end 37ab on the upstream side of the furst turbine scroll channel 31a from the one end 37aa; and a second partition wall 37b which is provided in the second turbine scroll channel 31b, disposes one end 37ba at a position where a channel cross-sectional area becomes minium in a part facing a first tongue portion 35a of the second turbine scroll channel 31b, and arranges the other end 37bb on the upstream side of the second turbine scroll channel 31b from the one end 37ba.SELECTED DRAWING: Figure 2

Description

  The present disclosure relates to turbines and superchargers.

  Patent Literature 1 discloses an engine and a supercharger. The engine includes a cylinder block and a cylinder head. A plurality of cylinders are formed in the cylinder block. An in-head manifold is formed in the cylinder head. The supercharger includes a turbine. The turbine is connected to the cylinder head. The manifold in the head communicates with a plurality of cylinders. The in-head manifold has a collecting part that combines exhaust discharged from a plurality of cylinders. The exhaust gas joined by the manifold in the head is introduced into the turbine.

Japanese Patent No. 6139463

  Exhaust gas discharged from a plurality of cylinders is likely to sneak into other flow paths at a portion where the flow paths join in the manifold in the head, causing exhaust interference. Exhaust interference is more likely to occur as the exhaust merging position approaches a plurality of cylinders (exhaust ports).

  An object of the present disclosure is to provide a turbine and a supercharger capable of reducing exhaust interference.

  In order to solve the above-described problems, a turbine according to an embodiment of the present disclosure includes a housing having a housing portion that houses a turbine wheel, a first turbine scroll passage formed in the housing, and communicating with the housing portion. A second turbine scroll passage formed in the housing and communicating with the housing at a different position in the circumferential direction of the turbine wheel with respect to a position in which the housing communicates with the first turbine scroll passage; A first tongue portion provided at a position facing the downstream end of the first turbine scroll flow path and separating the first turbine scroll flow path and the second turbine scroll flow path; A second tongue provided at a position facing the downstream end and dividing the second turbine scroll flow path and the first turbine scroll flow path; One end is provided at a position where the cross-sectional area of the flow passage is minimized in a portion of the first turbine scroll flow passage that faces the second tongue portion, and the other end of the first turbine scroll flow passage is located in the first turbine scroll flow passage. A first partition wall provided on the upstream side of the turbine scroll flow path, and a flow path formed in a portion of the second turbine scroll flow path facing the first tongue in the second turbine scroll flow path; A second partition wall, one end of which is provided at a position where the cross-sectional area is minimized, and the other end of which is disposed upstream of the one end in the second turbine scroll flow path.

  The first partition wall and the second partition wall may extend in the axial direction of the turbine wheel.

  The first partition wall is spaced apart from the center axis of the turbine wheel with respect to the center position in the width direction of the first turbine scroll flow path at one end than at the other end. The other end may be further away from the center axis of the turbine wheel with respect to the center position in the width direction of the second turbine scroll flow path than the other end.

  In order to solve the above problem, a supercharger according to an embodiment of the present disclosure includes the turbine.

  According to the present disclosure, it is possible to reduce exhaust interference.

FIG. 1 is a schematic sectional view of the supercharger. FIG. 2 is a sectional view of the turbine housing. FIG. 3A is a sectional view taken along the line IIIA-IIIA of FIG. 2. FIG. 3B is a sectional view taken along the line IIIB-IIIB of FIG. 2. FIG. 3C is a sectional view taken along the line IIIC-IIIC in FIG. 2. FIG. 4 is a schematic diagram showing a connection relationship between a turbine housing, an exhaust manifold, and an engine.

  Hereinafter, an embodiment of the present disclosure will be described with reference to the accompanying drawings. The dimensions, materials, other specific numerical values, and the like shown in the embodiments are merely examples for facilitating understanding, and do not limit the present disclosure unless otherwise specified. In the specification and the drawings, elements having substantially the same function and configuration are denoted by the same reference numerals, and redundant description will be omitted. Elements not directly related to the present disclosure are not shown.

  FIG. 1 is a schematic sectional view of the supercharger TC. 1 will be described as the left side of the supercharger TC. The direction of arrow R shown in FIG. 1 will be described as the right side of the supercharger TC. As shown in FIG. 1, the supercharger TC includes a supercharger main body 1. The supercharger main body 1 includes a bearing housing 3, a turbine housing (housing) 5, and a compressor housing 7. The turbine housing 5 is connected to the left side of the bearing housing 3 by a fastening bolt 9. The compressor housing 7 is connected to the right side of the bearing housing 3 by a fastening bolt 11.

  The bearing housing 3 has a bearing hole 3a. The bearing hole 3a penetrates in the left-right direction of the supercharger TC. A bearing 13 is provided in the bearing hole 3a. In the present embodiment, the bearing 13 is a full floating bearing. However, the bearing 13 may be another radial bearing such as a semi-floating bearing or a rolling bearing. The shaft 15 is inserted through the bearing 13. The bearing 13 rotatably supports the shaft 15. A turbine wheel 17 is provided at the left end of the shaft 15. The turbine wheel 17 is rotatably accommodated in the turbine housing 5. A compressor impeller 19 is provided at the right end of the shaft 15. The compressor impeller 19 is rotatably accommodated in the compressor housing 7.

  An intake port 21 is formed in the compressor housing 7. The intake port 21 opens to the right of the supercharger TC. The intake port 21 is connected to an air cleaner (not shown). A diffuser channel 23 is formed by the facing surfaces of the bearing housing 3 and the compressor housing 7. The diffuser channel 23 pressurizes air. The diffuser channel 23 is formed in an annular shape. Further, the diffuser passage 23 communicates with the intake port 21 via the compressor impeller 19 on the radially inner side of the shaft 15.

  Further, a compressor scroll flow path 25 is formed in the compressor housing 7. The compressor scroll channel 25 is formed in an annular shape. The compressor scroll channel 25 is located, for example, radially outside the shaft 15 from the diffuser channel 23. The compressor scroll passage 25 communicates with an intake port of an engine (not shown) and the diffuser passage 23. When the compressor impeller 19 rotates, air is drawn into the compressor housing 7 from the intake port 21. The intake air is pressurized and accelerated in a process of flowing between the blades of the compressor impeller 19. The pressurized and accelerated air is pressurized in the diffuser channel 23 and the compressor scroll channel 25. The pressurized air is led to the intake port of the engine.

  In the turbine housing 5, a discharge port 27, a housing portion S, a communication channel 29, and a turbine scroll channel 31 are formed. The discharge port 27 opens on the left side of the supercharger TC. The discharge port 27 is connected to an exhaust gas purification device (not shown). The storage section S communicates with the discharge port 27. The accommodation part S accommodates the turbine wheel 17. The communication flow path 29 connects the storage section S and the turbine scroll flow path 31. The turbine scroll channel 31 is formed in an annular shape. The turbine scroll passage 31 is located, for example, radially outside the turbine impeller 17 with respect to the communication passage 29. The turbine scroll flow path 31 communicates with the storage section S via the communication flow path 29.

  The turbine scroll passage 31 communicates with a gas inlet 33 (see FIG. 2). Exhaust gas exhausted from an exhaust manifold EM (see FIG. 4) of the engine E (see FIG. 4) is led to the gas inlet 33. The exhaust gas guided from the gas inlet 33 to the turbine scroll flow path 31 is guided to the discharge port 27 via the communication flow path 29 and the storage section S (turbine wheel 17). The exhaust gas guided to the discharge port 27 rotates the turbine wheel 17 in the flow process.

  As described above, the supercharger TC of the present embodiment includes the turbine T. The turbine T includes a turbine housing 5, a turbine wheel 17, and a turbine scroll passage 31. The torque of the turbine wheel 17 is transmitted to the compressor impeller 19 via the shaft 15. When the compressor impeller 19 rotates, the air pressure is increased as described above. In this way, air is guided to the intake port of the engine.

  FIG. 2 is a sectional view of the turbine housing 5. FIG. 2 shows a view in which the turbine housing 5 is cut on a plane perpendicular to the axial direction of the shaft 15 (see FIG. 1) and passing through the communication flow path 29 (see FIG. 1). 2, only the outer periphery of the turbine wheel 17 is indicated by a circle.

  As shown in FIG. 2, a gas inlet 33 is formed in the turbine housing 5. The gas inlet 33 opens outside the turbine housing 5. The gas inlet 33 includes an inner gas inlet 33a and an outer gas inlet 33b. The inner diameter gas inlet 33a is located radially inward (hereinafter, simply referred to as radial direction) of the turbine wheel 17 with respect to the outer diameter gas inlet 33b. The inner diameter gas inlet 33a is formed radially in line with the outer diameter gas inlet 33b.

  The turbine scroll flow path 31 is formed radially outside the storage section S (turbine wheel 17). The turbine scroll flow path 31 is formed over the entire circumference of the housing section S (turbine wheel 17). The turbine scroll channel 31 includes a first turbine scroll channel 31a and a second turbine scroll channel 31b.

  The first turbine scroll passage 31a communicates with the inner gas inlet 33a and the storage section S. In the first turbine scroll passage 31a, the radial width of the turbine wheel 17 decreases as the distance from the inner gas inlet 33a increases. Hereinafter, the side of the first turbine scroll passage 31a that is close to the inner diameter gas inlet 33a is referred to as the upstream side of the first turbine scroll passage 31a. Further, the side of the first turbine scroll flow path 31a that is separated from the inner diameter side gas inlet 33a is referred to as a downstream side of the first turbine scroll flow path 31a. In the first turbine scroll channel 31a, the radial width of the turbine wheel 17 decreases from the upstream side to the downstream side. The first turbine scroll passage 31a is located radially inward of the second turbine scroll passage 31b. The first turbine scroll passage 31a is formed radially in line with the second turbine scroll passage 31b.

  The second turbine scroll flow path 31b communicates with the outer diameter side gas inflow port 33b and the storage section S. The radial width of the turbine wheel 17 decreases in the second turbine scroll passage 31b as the distance from the outer diameter gas inlet 33b increases. Hereinafter, the side of the second turbine scroll channel 31b that is close to the outer diameter gas inlet 33b is referred to as the upstream side of the second turbine scroll channel 31b. Further, the side of the second turbine scroll flow path 31b that is separated from the outer diameter side gas inlet 33b is referred to as the downstream side of the second turbine scroll flow path 31b. In the second turbine scroll channel 31b, the radial width of the turbine wheel 17 decreases from the upstream side to the downstream side.

  The accommodation section S communicates with the first turbine scroll flow path 31a on the left half of FIG. The accommodation section S communicates with the second turbine scroll flow path 31b in the right half of FIG. As described above, the position of the storage section S that communicates with the first turbine scroll flow path 31 a is different from the position that communicates with the second turbine scroll flow path 31 b in the circumferential direction of the turbine wheel 17.

  A first tongue 35a and a second tongue 35b are formed in the turbine housing 5. The first tongue 35a is provided at a position facing a downstream end (downstream end) of the first turbine scroll flow path 31a. The first tongue portion 35a partitions the first turbine scroll passage 31a and the second turbine scroll passage 31b.

  The second tongue 35b is provided at a position facing a downstream end (downstream end) of the second turbine scroll flow path 31b. The second tongue portion 35b partitions the second turbine scroll passage 31b and the first turbine scroll passage 31a.

  A first partition wall 37a is provided in the first turbine scroll passage 31a. One end 37aa of the first partition wall 37a is arranged on the downstream side of the first turbine scroll passage 31a, and the other end 37ab is arranged on the upstream side of the first turbine scroll passage 31a. One end 37aa of the first partition wall 37a is located at a position (hereinafter, referred to as a second tongue minimum flow path) where the cross-sectional area of the flow path is minimum in a portion of the first turbine scroll flow path 31a facing the second tongue 35b. (Referred to as a sectional area) P1. The other end 37ab of the first partition wall 37a is arranged upstream of the one end 37aa of the first turbine scroll flow path 31a. In the present embodiment, the other end 37ab of the first partition wall 37a is disposed at the upstream end of the first turbine scroll passage 31a, that is, at the inner gas inlet 33a.

  The first partition wall 37a extends in the axial direction of the turbine wheel 17. That is, the first partition wall 37a divides the first turbine scroll passage 31a in the radial direction of the turbine wheel 17. The first partition wall 37a divides the first turbine scroll flow path 31a into an inner diameter side first divided flow path 31aa and an outer diameter side first divided flow path 31ab. The inner diameter side first divided flow path 31aa is formed in the outer diameter side first divided flow path 31ab in a radial direction.

  A second partition wall 37b is provided in the second turbine scroll channel 31b. One end 37ba of the second partition wall 37b is disposed downstream of the second turbine scroll flow channel 31b, and the other end 37bb is disposed upstream of the second turbine scroll flow channel 31b. One end 37ba of the second partition wall 37b is located at a position (hereinafter, referred to as a first tongue minimum flow path) where the flow path cross-sectional area is the minimum in a portion of the second turbine scroll flow path 31b facing the first tongue 35a. P2). The other end 37bb of the second partition wall 37b is disposed upstream of the one end 37ba of the second turbine scroll flow path 31b. In the present embodiment, the other end 37bb of the second partition wall 37b is disposed at the upstream end of the second turbine scroll flow path 31b, that is, at the outer diameter side gas inlet 33b.

  The second partition wall 37 b extends in the axial direction of the turbine wheel 17. That is, the second partition wall 37b divides the second turbine scroll passage 31b in the radial direction of the turbine wheel 17. The second partition wall 37b divides the second turbine scroll flow path 31b into an inner diameter side second divided flow path 31ba and an outer diameter side second divided flow path 31bb. The inner diameter side second divided flow path 31ba is formed in a radial direction along with the outer diameter side second divided flow path 31bb.

  FIG. 3A is a sectional view taken along the line IIIA-IIIA of FIG. 2. FIG. 3A illustrates the cross-sectional shape of the upstream side of the first turbine scroll channel 31a and the second turbine scroll channel 31b. In FIG. 3A, the center line (center position) CL in the width direction (radial direction of the turbine impeller 17) of the first turbine scroll passage 31a and the second turbine scroll passage 31b is indicated by a broken line.

  As shown in FIG. 3A, the cross-sectional shapes of the first turbine scroll flow channel 31a and the second turbine scroll flow channel 31b are substantially rectangular. The cross-sectional shape of the first turbine scroll flow channel 31a is substantially equal to the cross-sectional shape of the second turbine scroll flow channel 31b. The first partition wall 37a is arranged such that the center in the width direction of the first partition wall 37a is located at the center line CL of the first turbine scroll flow path 31a. Thereby, the flow path cross-sectional area of the inner diameter side first divided flow path 31aa becomes approximately equal to the flow path cross-sectional area of the outer diameter side first divided flow path 31ab.

  The second partition wall 37b is disposed such that the center in the width direction of the second partition wall 37b is located at the center line CL of the second turbine scroll flow path 31b. Thereby, the flow path cross-sectional area of the inner diameter side second divided flow path 31ba is substantially equal to the flow path cross-sectional area of the outer diameter side second divided flow path 31bb.

  FIG. 3B is a sectional view taken along the line IIIB-IIIB of FIG. 2. FIG. 3B shows a flow path cross-sectional shape on the downstream side of the first turbine scroll flow path 31a. In FIG. 3B, the center axis CA of the turbine wheel 17 is indicated by a chain line. As shown in FIG. 3B, the cross-sectional shape of the first turbine scroll flow channel 31a is substantially trapezoidal. Specifically, the length in the depth direction (the axial direction of the turbine wheel 17 (vertical direction in FIG. 3B)) of the inner diameter side first divided flow path 31aa is determined by the depth of the outer diameter side first divided flow path 31ab. Shorter than the length in the direction. That is, the axial length of the turbine wheel 17 becomes longer toward the radially outer side of the first turbine scroll channel 31a.

  The first partition wall 37a is disposed such that the center in the width direction of the first partition wall 37a is separated from the center axis CA of the turbine wheel 17 with respect to the center line CL of the first turbine scroll flow path 31a. Thereby, even if the cross-sectional shape of the first turbine scroll flow channel 31a is substantially trapezoidal, the flow cross-sectional areas of the inner diameter side first split flow channel 31aa and the outer diameter side first split flow channel 31ab are approximately equal. can do.

  FIG. 3C is a sectional view taken along the line IIIC-IIIC in FIG. 2. FIG. 3C shows a flow path cross-sectional shape on the downstream side of the second turbine scroll flow path 31b. In FIG. 3C, the central axis CA of the turbine wheel 17 is indicated by a chain line. As shown in FIG. 3C, the cross-sectional shape of the second turbine scroll flow channel 31b is substantially trapezoidal. Specifically, the length of the inner diameter side second divided flow path 31ba in the depth direction (the axial direction of the turbine wheel 17 (vertical direction in FIG. 3C)) is equal to the depth of the outer diameter side second divided flow path 31bb. Shorter than the length in the direction. That is, the axial length of the turbine wheel 17 becomes longer toward the radially outer side of the second turbine scroll passage 31b. The cross-sectional shape of the second turbine scroll flow channel 31b illustrated in FIG. 3C is substantially equal to the cross-sectional shape of the first turbine scroll flow channel 31a illustrated in FIG. 3B.

  The second partition wall 37b is disposed such that the center in the width direction of the second partition wall 37b is separated from the center axis CA of the turbine wheel 17 with respect to the center line CL of the second turbine scroll flow path 31b. Thereby, even if the cross-sectional shape of the second turbine scroll flow channel 31b is substantially trapezoidal, the flow channel cross-sectional areas of the inner diameter side second split flow channel 31ba and the outer diameter side second split flow channel 31bb are approximately equal. can do.

  FIG. 4 is a schematic diagram showing a connection relationship among the turbine housing 5, the exhaust manifold EM, and the engine E. As shown in FIG. 4, the engine E includes a first cylinder E1, a second cylinder E2, a third cylinder E3, and a fourth cylinder E4. The exhaust manifold EM includes a first pipe EM1, a second pipe EM2, a third pipe EM3, and a fourth pipe EM4.

  The first pipe EM1 allows the first cylinder E1 to communicate with the outer diameter side second divided flow path 31bb. The second pipe EM2 communicates the second cylinder E2 with the first inner-diameter flow path 31aa. The third pipe EM3 communicates the third cylinder E3 with the outer diameter side first divided flow path 31ab. The fourth pipe EM4 communicates the fourth cylinder E4 with the inner diameter side second divided flow path 31ba.

  The ignition order of the engine E is, for example, the order of the first cylinder E1, the third cylinder E3, the fourth cylinder E4, and the second cylinder E2. The exhaust gas discharged from the first cylinder E1 is supplied to the outer diameter side second divided flow path 31bb through the first pipe EM1. The exhaust gas discharged from the third cylinder E3 is supplied to the outer diameter side first divided flow path 31ab through the third pipe EM3. The exhaust gas discharged from the fourth cylinder E4 is supplied to the inner diameter side second divided flow path 31ba through the fourth pipe EM4. The exhaust gas discharged from the second cylinder E2 is supplied to the inner diameter side first divided flow path 31aa through the second pipe EM2.

  As described above, the exhaust gas discharged from the plurality of cylinders of the engine E is alternately supplied to the first turbine scroll passage 31a and the second turbine scroll passage 31b. As a result, exhaust gas is alternately supplied to the storage section S (turbine wheel 17) from different positions in the circumferential direction. Therefore, a load is applied to the turbine wheel 17 in a well-balanced manner. As a result, shortening of the life of the turbine wheel 17 can be suppressed.

  The turbine housing 5 of the present embodiment includes a first partition wall 37a and a second partition wall 37b. The first partition wall 37a extends from the inner gas inlet 33a to the second tongue minimum flow path cross-sectional area P1. That is, the inner diameter side first divided flow path 31aa and the outer diameter side first divided flow path 31ab extend from the inner diameter side gas inflow port 33a to the second tongue minimum flow path cross-sectional area P1. The second partition wall 37b extends from the outer diameter side gas inlet 33b to the first tongue minimum flow path cross-sectional area P2. That is, the inner diameter side second divided flow path 31ba and the outer diameter side second divided flow path 31bb extend from the outer diameter side gas inflow port 33b to the first tongue minimum flow path sectional area P2.

  Here, the first split flow path 31aa on the inner diameter side communicates with any one of the cylinders E1 to E4 (here, the second cylinder E2). The outer-diameter first divided flow path 31ab communicates with any one of the plurality of cylinders E1 to E4 (here, the third cylinder E3). The inner diameter side second divided flow path 31ba communicates with any one of the plurality of cylinders E1 to E4 (here, the fourth cylinder E4). The outer-diameter second divided flow path 31bb communicates with any one of the plurality of cylinders E1 to E4 (here, the first cylinder E1).

  Therefore, as is clear from FIG. 2, the exhaust gas discharged from any one of the plurality of cylinders is different from the exhaust gas discharged from the other cylinder in the second tongue minimum flow path cross-sectional area P1, The first tongue merges on the downstream side of the minimum flow path cross-sectional area P2. Thus, the merging position of the exhaust discharged from any one of the plurality of cylinders and the exhaust discharged from the other cylinder can be separated from the plurality of cylinders (exhaust ports). As a result, the turbine T of the present embodiment can reduce exhaust interference.

  Also, one end 37aa of the first partition wall 37a is not disposed downstream of the second tongue minimum flow path cross-sectional area P1 in the first turbine scroll flow path 31a. When the first partition wall 37a is disposed downstream of the second tongue minimum flow path cross-sectional area P1, one end 37aa of the first partition wall 37a is separate from the first tongue portion 35a and the second tongue portion 35b. Can be a new tongue.

  Similarly, one end 37ba of the second partition wall 37b is not disposed downstream of the first tongue minimum flow path cross-sectional area P2 in the second turbine scroll flow path 31b. When the second partition wall 37b is disposed downstream of the first tongue minimum flow path cross-sectional area P2, one end 37ba of the second partition wall 37b is separate from the first tongue 35a and the second tongue 35b. Can be a new tongue.

  When the number of tongues arranged around the turbine wheel 17 increases, the blades of the turbine wheel 17 are likely to vibrate, and the durability of the turbine wheel 17 may be reduced. Therefore, in this embodiment, the one end 37aa of the first partition wall 37a is not disposed downstream of the second tongue minimum flow path cross-sectional area P1. In addition, one end 37ba of the second partition wall 37b is not arranged downstream of the first tongue minimum flow path cross-sectional area P2. As a result, the life of the turbine wheel 17 can be suppressed from being shortened.

  When the first partition wall 37a and the second partition wall 37b extend in the radial direction of the turbine wheel 17 (that is, the turbine scroll flow path 31 is divided in the axial direction), the turbine wheel 17 has an axial direction. Exhaust is supplied from different locations. Then, the exhaust gas is supplied to the turbine wheel 17 unevenly in the axial direction. When the exhaust gas is supplied unevenly in the axial direction, the rotation efficiency of the turbine wheel 17 decreases.

  On the other hand, when the first partition wall 37a and the second partition wall 37b extend in the axial direction of the turbine wheel 17, the exhaust is supplied to the turbine wheel 17 substantially uniformly in the axial direction. Thus, the rotation efficiency of the turbine wheel 17 can be improved when the first partition wall 37a and the second partition wall 37b extend in the axial direction rather than in the radial direction.

  Further, as described with reference to FIGS. 3A, 3B, and 3C, the cross-sectional shapes of the first turbine scroll flow channel 31a and the second turbine scroll flow channel 31b change as they progress from the upstream side to the downstream side. Therefore, the first partition wall 37a is farther away from the center axis CA of the turbine wheel 17 at the one end 37aa than at the other end 37ab with respect to the center position in the width direction of the first turbine scroll flow path 31a. Thereby, the first partition wall 37a can make the flow path cross-sectional areas of the inner diameter side first divided flow path 31aa and the outer diameter side first divided flow path 31ab approximately equal from the upstream side to the downstream side. Further, the second partition wall 37b has one end 37ba separated from the center axis CA of the turbine wheel 17 with respect to the center position in the width direction of the second turbine scroll passage 31b than the other end 37bb. Accordingly, the second partition wall 37b can make the flow path cross-sectional areas of the inner diameter side second divided flow path 31ba and the outer diameter side second divided flow path 31bb approximately equal from the upstream side to the downstream side.

  As described above, one embodiment of the present disclosure has been described with reference to the accompanying drawings, but it is needless to say that the present disclosure is not limited to such an embodiment. It will be apparent to those skilled in the art that various changes or modifications can be made within the scope of the appended claims, and those modifications naturally belong to the technical scope of the present disclosure. Is done.

  In the above-described embodiment, an example in which the other end 37ab of the first partition wall 37a and the other end 37bb of the second partition wall 37b are disposed in the gas inlet 33 has been described. However, the present invention is not limited to this, and the other end 37ab of the first partition wall 37a and the other end 37bb of the second partition wall 37b may not be arranged at the gas inlet 33. For example, the other end 37ab of the first partition wall 37a may be disposed between the gas inlet 33 and the second tongue minimum flow path cross-sectional area P1. Further, the other end 37bb of the second partition wall 37b may be disposed between the gas inlet 33 and the first tongue minimum flow passage sectional area P2. In that case, each of the pipes EM1 to EM4 of the exhaust manifold EM may extend from the gas inlet 33 to the other end 37ab of the first partition wall 37a and the other end 37bb of the second partition wall 37b.

  In the above embodiment, the example in which the first partition wall 37a and the second partition wall 37b extend in the axial direction of the turbine wheel 17 has been described. However, the invention is not limited thereto, and the first partition wall 37a and the second partition wall 37b may extend in the radial direction of the turbine wheel 17.

  In the above embodiment, an example in which the one end 37aa of the first partition wall 37a is more distant from the center axis CA of the turbine wheel 17 with respect to the center position in the width direction of the first turbine scroll flow path 31a than the other end 37ab. Was explained. However, the positions of the one end 37aa and the other end 37ab of the first partition wall 37a are not limited thereto. For example, the first partition wall 37a may have one end 37aa closer to the center axis of the turbine wheel 17 with respect to the center position in the width direction of the first turbine scroll passage 31a than the other end 37ab. At this time, the flow path cross-sectional areas of the inner diameter side first divided flow path 31aa and the outer diameter side first divided flow path 31ab may be equal or different. However, the load is applied to the turbine impeller 17 in a well-balanced manner by equalizing the cross-sectional areas of the inner diameter side first divided flow path 31aa and the outer diameter side first divided flow path 31ab. As a result, shortening of the life of the turbine wheel 17 can be suppressed.

  In the above embodiment, an example in which the one end 37ba of the second partition wall 37b is more distant from the center axis of the turbine wheel 17 with respect to the center position in the width direction of the second turbine scroll flow path 31b than the other end 37bb. explained. However, the positions of the one end 37ba and the other end 37bb of the second partition wall 37b are not limited to this. For example, even if the one end 37ba of the second partition wall 37b is closer to the center axis CA of the turbine wheel 17 with respect to the center position in the width direction of the second turbine scroll flow path 31b than the other end 37bb. Good. At this time, the flow path cross-sectional areas of the inner diameter side second divided flow path 31ba and the outer diameter side second divided flow path 31bb may be equal or different. However, the load is applied to the turbine wheel 17 in a well-balanced manner by equalizing the cross-sectional areas of the inner diameter side second divided flow path 31ba and the outer diameter side second divided flow path 31bb. As a result, shortening of the life of the turbine wheel 17 can be suppressed.

  The present disclosure can be used for turbines and superchargers.

5 Turbine housing (housing)
17 Turbine impeller 31 Turbine scroll passage 31a First turbine scroll passage 31b Second turbine scroll passage 35a First tongue 35b Second tongue 37a First partition wall 37aa One end 37ab Other end 37b Second partition wall 37ba One end 37bb Other end P1 position (2nd tongue minimum flow path cross section)
P2 position (first tongue minimum flow path cross-sectional area)
S Housing T Turbine TC Turbocharger

Claims (4)

A housing in which a housing portion for housing the turbine wheel is formed,
A first turbine scroll passage formed in the housing and communicating with the housing portion;
A second turbine scroll passage formed in the housing and communicating with the housing at a different position in a circumferential direction of the turbine wheel with respect to a position where the housing and the first turbine scroll flow communicate with each other;
A first tongue provided in the housing at a position facing a downstream end of the first turbine scroll flow path, and separating the first turbine scroll flow path and the second turbine scroll flow path;
A second tongue provided in the housing at a position facing a downstream end of the second turbine scroll flow path, and separating the second turbine scroll flow path and the first turbine scroll flow path;
One end is provided in the first turbine scroll flow path, and one end is provided at a position where a flow path cross-sectional area is minimized in a portion of the first turbine scroll flow path facing the second tongue; A first partition wall having an end disposed upstream of the one end in the first turbine scroll flow path;
One end is provided in the second turbine scroll flow path, and one end is provided at a position where the flow path cross-sectional area is minimized in a portion of the second turbine scroll flow path facing the first tongue portion, A second partition wall having an end disposed upstream of the one end in the second turbine scroll flow path;
A turbine comprising: The turbine according to claim 1, wherein the first partition wall and the second partition wall extend in an axial direction of the turbine wheel. The first partition wall is separated from the center axis of the turbine wheel with respect to the center position in the width direction of the first turbine scroll flow path at the one end than the other end,
3. The second partition wall according to claim 2, wherein the one end is more distant from the center axis of the turbine wheel with respect to the center position in the width direction of the second turbine scroll flow path than the other end. 4. Turbine.   A supercharger comprising the turbine according to any one of claims 1 to 3.

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