Turbines and superchargers

Abstract

A turbine T comprises: housings 3, 5 including an accommodation space 29 that accommodates a turbine impeller 15, a turbine scroll flow path 31a disposed radially outside the turbine impeller 15, a communication flow path 33 through which the turbine scroll flow path 31a and the accommodation space 29 communicate, and a discharge flow path 27 that is continuous with the accommodation space 29 in the rotational axis direction of the turbine impeller 15; a vane member 35 that is provided in the communication flow path 33 and that includes a plurality of vane parts 35b opposite a first inner wall part W1 facing the communication flow path 33 from the side opposite to the discharge flow path 27; and an elastic member 39 enclosed between the vane member 35 and a second inner wall part W2 facing the communication flow path 33 from the side having the exhaust flow path 27.

Description

Technical Field

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[0001] The present disclosure relates to a turbine and a supercharger. This application claims the benefit of priority based on Japanese Patent Application No. 2022-085554 filed on May 25, 2022, the content of which is incorporated herein by reference.

Background Art

[0002] A turbine provided in a supercharger or the like has an accommodation space for accommodating a turbine impeller. For example, as disclosed in Patent Document 1, a vane member may be provided in a communication flow path that communicates the accommodation space and a turbine scroll flow path. The vane member includes a plurality of vane portions arranged at intervals in the circumferential direction of the turbine impeller. The flow rate of the exhaust gas flowing into the accommodation space of the turbine impeller is adjusted by the plurality of vane portions.

Prior Art Documents

Patent Documents

[0003]

Patent Document 1

[0006] To solve the above problems, the turbine of the present disclosure includes a housing that includes a housing space for housing a turbine impeller, a turbine scroll passage arranged radially outward from the turbine impeller, a communication passage connecting the turbine scroll passage and the housing space, and a discharge passage continuous with respect to the housing space in the direction of the rotation axis of the turbine impeller; a plurality of vane portions facing a first inner wall portion facing the communication passage from the side opposite to the discharge passage; and a base portion to which the plurality of vane portions are fixed; a vane member provided in the communication passage; a second inner wall portion facing the communication passage from the discharge passage side; and an elastic member sandwiched between the vane member, wherein the base portion abuts the elastic member, and a cylindrical wall portion extending in the direction of the rotation axis is formed in the portion of the housing facing the first inner wall portion, the base portion is annular, and the inner circumference of the base portion is fitted into the cylindrical wall portion. Furthermore, the outer periphery of the base portion is not fitted into the housing, the elastic member is a disc spring, and the elastic member and the base portion are in contact with each other over the entire circumference of the turbine blade. .

[0007] Be A sealing member may be provided between the part and the housing.

[0008] A heat shield having a first inner wall portion may be provided.

[0010] To solve the above problems, the supercharger of this disclosure comprises the turbine described above. [Effects of the Invention]

[0011] According to this disclosure, it is possible to suppress the decrease in turbine efficiency. [Brief explanation of the drawing]

[0012] [Figure 1] Figure 1 is a schematic cross-sectional view showing a turbocharger according to an embodiment of the present disclosure. [Figure 2] Figure 2 is a cross-sectional view of AA in Figure 1. [Figure 3] Figure 3 is a partially enlarged view showing a turbine according to an embodiment of the present disclosure. [Figure 4]Figure 4 is a partially enlarged view showing the turbine of the first modified example. [Figure 5] Figure 5 is a magnified view of a second modified turbine. [Modes for carrying out the invention]

[0013] An embodiment of this disclosure will be described below with reference to the attached drawings. The dimensions, materials, and other specific numerical values ​​shown in the embodiment are merely examples for the purpose of facilitating understanding and do not limit this disclosure unless otherwise specified. In this specification and drawings, elements having substantially the same function and configuration are denoted by the same reference numerals to avoid redundant explanations, and elements not directly related to this disclosure are omitted from the illustrations.

[0014] Figure 1 is a schematic cross-sectional view of the turbocharger TC. In the following description, the direction of arrow L in Figure 1 will be described as the left side of the turbocharger TC. The direction of arrow R in Figure 1 will be described as the right side of the turbocharger TC. As shown in Figure 1, the turbocharger TC comprises a turbocharger body 1. The turbocharger body 1 includes a bearing housing 3, a turbine 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 mechanism 9. The compressor housing 7 is connected to the right side of the bearing housing 3 by fastening bolts 11.

[0015] The supercharger TC comprises a turbine T and a centrifugal compressor C. The turbine T includes a bearing housing 3 and a turbine housing 5. In other words, the bearing housing 3 and the turbine housing 5 correspond to the housings of the turbine T. The centrifugal compressor C includes a bearing housing 3 and a compressor housing 7. In other words, the bearing housing 3 and the compressor housing 7 correspond to the housings of the centrifugal compressor C.

[0016] A projection 3a is provided on the outer circumferential surface of the bearing housing 3. The projection 3a is provided on the turbine housing 5 side. The projection 3a protrudes radially from the bearing housing 3. A projection 5a is provided on the outer circumferential surface of the turbine housing 5. The projection 5a is provided on the bearing housing 3 side. The projection 5a protrudes radially from the turbine housing 5. The bearing housing 3 and the turbine housing 5 are band-fastened by a fastening mechanism 9. The fastening mechanism 9 is, for example, a G-coupling. The fastening mechanism 9 clamps the projections 3a and 5a.

[0017] A bearing hole 3b is formed in the bearing housing 3. The bearing hole 3b penetrates the supercharger TC in the left-right direction. A bearing is placed in the bearing hole 3b. A shaft 13 is inserted through the bearing. The bearing rotatably supports the shaft 13. The bearing is a sliding bearing. However, it is not limited to this, and the bearing may be a rolling bearing. A turbine impeller 15 is provided at the left end of the shaft 13. The turbine impeller 15 is rotatably housed in the turbine housing 5. A compressor impeller 17 is provided at the right end of the shaft 13. The compressor impeller 17 is rotatably housed in the compressor housing 7.

[0018] An intake port 19 is formed in the compressor housing 7. The intake port 19 opens to the right of the supercharger TC. The intake port 19 is connected to an air cleaner (not shown). A diffuser passage 21 is formed by the opposing surfaces of the bearing housing 3 and the compressor housing 7. The diffuser passage 21 pressurizes the air. The diffuser passage 21 is formed in an annular shape. The diffuser passage 21 communicates with the intake port 19 radially inward via the compressor impeller 17.

[0019] In the compressor housing 7, a compressor scroll flow path 23 is formed. The compressor scroll flow path 23 is formed in an annular shape. The compressor scroll flow path 23 is located, for example, radially outside the shaft 13 relative to the diffuser flow path 21. The compressor scroll flow path 23 communicates with an intake port of an engine (not shown) and the diffuser flow path 21. When the compressor impeller 17 rotates, air is sucked into the compressor housing 7 from the intake port 19. The sucked air is pressurized and accelerated in the process of flowing through the spaces between the blades of the compressor impeller 17. The pressurized and accelerated air is further pressurized in the diffuser flow path 21 and the compressor scroll flow path 23. The pressurized air is guided to the intake port of the engine.

[0020] <了 In the turbine housing 5, an exhaust discharge port 25 is formed. The exhaust discharge port 25 opens to the left side of the supercharger TC. The exhaust discharge port 25 is connected to an exhaust gas purification device (not shown). In the turbine housing 5, a discharge flow path 27, a housing space 29, and an exhaust flow path 31 are formed. The discharge flow path 27 communicates the housing space 29 and the exhaust discharge port 25. The discharge flow path 27 is continuous with respect to the housing space 29 in the rotational axis direction of the turbine impeller 15. The housing space 29 houses the turbine impeller 15. The exhaust flow path 31 is formed radially outside the turbine impeller 15. The exhaust flow path 31 is formed in an annular shape. The exhaust flow path 31 includes a turbine scroll flow path 31a. The turbine scroll flow path 31a is arranged radially outside the turbine impeller 15. The turbine scroll flow path 31a communicates with the housing space 29 via a communication flow path 33. That is, the communication flow path 33 communicates the turbine scroll flow path 31a and the housing space 29. The communication flow path 33 is arranged radially outside the turbine impeller 15.

[0021] The exhaust flow path ३1 communicates with an exhaust manifold of an engine (not shown). The exhaust gas discharged from the exhaust manifold of the engine (not shown) is guided to the discharge flow path 27 through the exhaust flow path 31, the communication flow path 33, and the housing space 29. The exhaust gas guided to the discharge flow path 27 rotates the turbine impeller 15 in the process of flowing through.

[0022] The rotational force of the turbine impeller 15 is transmitted to the compressor impeller 17 via the shaft 13. When the compressor impeller 17 rotates, the air is pressurized as described above. Thus, the air is guided to the intake port of the engine.

[0023] A vane member 35 is provided in the communication flow path 33. The vane member 35 is provided to adjust the flow rate of the exhaust gas flowing into the accommodation space 29 of the turbine impeller 15. The vane member 35 has a substantially annular shape. The vane member 35 is arranged coaxially with the turbine impeller 15. The vane member 35 is arranged so as to cover the outer peripheral portion of the turbine impeller 15 over the entire circumference.

[0024] The vane member 35 includes a base portion 35a and a plurality of vane portions 35b. The base portion 35a has an annular flat plate shape. The base portion 35a is arranged coaxially with the turbine impeller 15. The vane portion 35b is attached to one side surface (in the example of FIG. 1, the right side surface) of the base portion 35a. The vane portion 35b is fixed to the base portion 35a. That is, in the vane member 35, the vane portion 35b is fixed. The base portion 35a and the vane portion 35b may be integrally formed by one member, or may be separated into separate members.

[0025] The plurality of vane portions 35b are arranged at intervals in the circumferential direction of the turbine impeller 15. For example, the plurality of vane portions 35b are arranged at equal intervals in the circumferential direction of the turbine impeller 15. Each vane portion 35b extends in the rotational axis direction of the turbine impeller 15 from the base portion 35a. Each vane portion 35b is inclined with respect to the circumferential direction of the turbine impeller 15.

[0026] Figure 2 is a cross-sectional view of section AA in Figure 1. In Figure 2, only the outer circumference of the turbine impeller 15 is shown as a circle. As shown in Figure 2, an exhaust passage 31 is formed on the radially outer side of the housing space 29 (i.e., radially outer side of the turbine impeller 15). The exhaust passage 31 comprises a turbine scroll passage 31a, an exhaust inlet 31b, and an exhaust inlet passage 31c. The exhaust passage 31 connects the housing space 29 and the exhaust inlet 31b.

[0027] The turbine scroll channel 31a is formed in an annular shape around the entire circumference of the housing space 29. A tongue portion 37 is formed in the turbine housing 5. The tongue portion 37 is provided at the downstream end of the turbine scroll channel 31a and separates the downstream portion from the upstream portion of the turbine scroll channel 31a.

[0028] The exhaust inlet 31b opens to the outside of the turbine housing 5. Exhaust gas discharged from the exhaust manifold of an engine (not shown) is introduced into the exhaust inlet 31b. An exhaust inlet passage 31c is formed between the exhaust inlet 31b and the turbine scroll passage 31a. The exhaust inlet passage 31c connects the exhaust inlet 31b and the turbine scroll passage 31a. The exhaust inlet passage 31c is formed, for example, in a straight shape. The exhaust inlet passage 31c guides the exhaust gas introduced from the exhaust inlet 31b to the turbine scroll passage 31a. The turbine scroll passage 31a guides the exhaust gas introduced from the exhaust inlet passage 31c to the containment space 29 via a communication passage 33. The communication passage 33 is formed around the entire circumference of the containment space 29. In the communication passage 33, multiple vane portions 35b of the vane member 35 are arranged at intervals in the circumferential direction of the turbine impeller 15. The exhaust gas sent from the turbine scroll passage 31a to the communication passage 33 passes between each vane section 35b before flowing into the containment space 29.

[0029] In a turbine T equipped with a vane member 35 in which the vane portion 35b is fixed, a gap may occur between the vane portion 35b and the inner wall of the turbine T housing when the components of the turbine T undergo thermal deformation. As a result, the flow of exhaust gas into the turbine blade 15 housing space 29 may be disturbed, potentially reducing the efficiency of the turbine T.

[0030] In the turbine T according to this embodiment, the method of attaching the vane members 35 to the housing of the turbine T is devised in order to suppress a decrease in the efficiency of the turbine T. The configuration around the vane members 35 will be described in detail below with reference to Figures 3 to 5.

[0031] Figure 3 is a partially enlarged view showing a turbine T according to an embodiment of the present disclosure. Figure 3 is a partially enlarged view of the area indicated by the dashed line in Figure 1. As shown in Figure 3, the vane member 35 is positioned between the first inner wall portion W1 and the second inner wall portion W2 of the housing of the turbine T.

[0032] The first inner wall W1 is the inner wall portion of the turbine T housing that faces the communication passage 33 from the side opposite the discharge passage 27 (the right side in the example of Figure 3). In the example of Figure 3, the left wall portion of the bearing housing 3 corresponds to the first inner wall portion W1. Thus, the first inner wall portion W1 is formed in the bearing housing 3, for example.

[0033] The second inner wall portion W2 is the inner wall portion of the turbine T housing that faces the communication passage 33 from the discharge passage 27 side (left side in the example of Figure 3). In the example of Figure 3, a groove portion 5b is formed in the portion of the turbine housing 5 that faces the first inner wall portion W1. The groove portion 5b is continuous with the turbine scroll passage 31a. The groove portion 5b extends radially toward the turbine impeller 15 from the turbine scroll passage 31a toward the turbine impeller 15. The groove portion 5b has an annular shape. The groove portion 5b is arranged coaxially with the turbine impeller 15. The bottom surface of the groove portion 5b corresponds to the second inner wall portion W2. The bottom surface of the groove portion 5b is the annular portion of the groove portion 5b that extends on a plane perpendicular to the rotation axis direction of the turbine impeller 15 and faces to the right. Thus, the second inner wall portion W2 is formed in the turbine housing 5, for example.

[0034] The vane portion 35b of the vane member 35 faces the first inner wall portion W1. Specifically, the right end face of the vane portion 35b faces the first inner wall portion W1 in the direction of the rotation axis of the turbine impeller 15. The base portion 35a of the vane member 35 fits into the cylindrical wall portion W3 of the groove portion 5b. The cylindrical wall portion W3 of the groove portion 5b is the cylindrical portion of the groove portion 5b that extends in the direction of the rotation axis of the turbine impeller 15. Specifically, the base portion 35a is positioned radially outward from the cylindrical wall portion W3 of the groove portion 5b and is positioned to cover the cylindrical wall portion W3 around its entire circumference. The inner circumference of the base portion 35a fits into the cylindrical wall portion W3.

[0035] The turbine T is provided with an elastic member 39 to press the vane portion 35b of the vane member 35 against the inner wall of the turbine T housing. In the example shown in Figure 3, the elastic member 39 is a disc spring. However, as will be described later, the elastic member 39 is not limited to a disc spring. The elastic member 39 has an annular shape. In detail, the elastic member 39 is inclined to the right as it extends radially outward.

[0036] The elastic member 39 is positioned between the second inner wall W2 and the vane member 35, and is sandwiched between the second inner wall W2 and the vane member 35 in the direction of the rotation axis of the turbine impeller 15. Specifically, the elastic member 39 is sandwiched between the second inner wall W2 and the left end face of the base portion 35a. The elastic member 39 is in a compressed state in the direction of the rotation axis of the turbine impeller 15. Therefore, a restoring force in the direction of the rotation axis of the turbine impeller 15 acts on the member in contact with the elastic member 39. The left portion of the inner circumference of the elastic member 39 is in contact with the second inner wall W2. The right portion of the outer circumference of the elastic member 39 is in contact with the base portion 35a. Therefore, the restoring force of the elastic member 39 acts on the vane member 35 in the right direction. As the vane member 35 is biased to the right by the elastic member 39, the right end surface of the vane portion 35b of the vane member 35 is pressed against the first inner wall portion W1.

[0037] As described above, the various components of the turbine T may undergo thermal deformation. For example, when the bearing housing 3 and the vane member 35 undergo thermal deformation, the contact between the right end surface of the vane portion 35b and the first inner wall portion W1 may cease to be surface contact and become line contact or point contact. In this case, a gap is created between the vane portion 35b and the first inner wall portion W1, and the flow of exhaust gas flowing from the communication passage 33 into the turbine blade housing space 29 becomes turbulent on the compressor side (right side in Figure 3).

[0038] On the other hand, unlike this embodiment, there is a case in which the vane portion 35b of the turbine T housing is biased to the left and pressed against the inner wall portion facing the communication passage 33 from the discharge passage 27 side (left side in the example of Figure 3). In this case, the vane portion 35b is positioned to the left of the base portion 35a, and the left end surface of the vane portion 35b is pressed against the inner wall portion of the housing. In this case, when a gap is created between the vane portion 35b and the housing due to thermal deformation of each component of the turbine T, the flow of exhaust gas flowing from the communication passage 33 into the accommodating space 29 of the turbine blade 15 is disturbed on the shroud side (left side in Figure 3), which is the opposite side from the compressor.

[0039] Of the exhaust gas flow from the communication channel 33 into the containment space 29, the flow on the shroud side has a greater impact on the efficiency of the turbine T compared to the flow on the compressor side. If the flow on the shroud side of the exhaust gas flow from the communication channel 33 into the containment space 29 is turbulent, the efficiency of the turbine T decreases significantly. On the other hand, even if the flow on the compressor side of the exhaust gas flow from the communication channel 33 into the containment space 29 is turbulent, the degree of decrease in the efficiency of the turbine T is small. As described above, in the turbine T of this embodiment, when a gap is created between the vane portion 35b and the housing due to thermal deformation of each component of the turbine T, the location where the exhaust gas flow from the communication channel 33 into the containment space 29 of the turbine impeller 15 becomes turbulent is on the compressor side. Therefore, the decrease in the efficiency of the turbine T can be suppressed.

[0040] The bearing housing 3 does not get as hot as the turbine housing 5. Therefore, the amount of thermal deformation of the bearing housing 3 is smaller than that of the turbine housing 5. Consequently, the gap between the vane portion 35b and the bearing housing 3 in the turbine T is smaller than the gap between the vane portion 35b and the turbine housing 5 in a turbine where the vane portion 35b is pressed against the turbine housing 5, unlike in this embodiment. Therefore, in the turbine T of this embodiment, the degree to which the exhaust gas flow is disturbed by the gap between the vane portion 35b and the housing can be reduced. This also contributes to suppressing the decrease in the efficiency of the turbine T.

[0041] As explained above, in the turbine T, the multiple vane portions 35b of the vane member 35 face the first inner wall portion W1, which faces the communication passage 33 from the side opposite the discharge passage 27 (the right side in the example of Figure 3). The elastic member 39 is sandwiched between the second inner wall portion W2, which faces the communication passage 33 from the discharge passage 27 side (the left side in the example of Figure 3), and the vane member 35. As a result, the gap created between the vane portion 35b and the housing due to the thermal deformation of each component of the turbine T is located near the first inner wall portion W1. Therefore, the position where the flow of exhaust gas flowing from the communication passage 33 into the turbine blade 15 housing space 29 is disturbed by the gap is on the compressor side. Thus, a decrease in the efficiency of the turbine T can be suppressed.

[0042] In particular, in the turbine T, the elastic member 39 is a disc spring. As a result, the elastic member 39 and the base portion 35a of the vane member 35 are in contact with each other over the entire circumference of the turbine impeller 15. For example, in the example in Figure 3, the right-hand portion of the outer circumference of the elastic member 39 has a circular shape and is positioned coaxially with the turbine impeller 15. The entire area of ​​this portion of the elastic member 39 is in contact with the base portion 35a. Therefore, the space between the elastic member 39 and the base portion 35a is sealed to some extent. In other words, the leakage of exhaust gas from the space between the elastic member 39 and the base portion 35a to the containment space 29 is suppressed to some extent. Thus, the unintended flow of exhaust gas from the communication passage 33 into the containment space 29 through the shroud side (left side in Figure 3) of the base portion 35a is suppressed. Therefore, the decrease in the efficiency of the turbine T can be suppressed more effectively.

[0043] Figure 4 is a partially enlarged view showing the turbine T1 of the first modified example. The first modified example of turbine T1 differs from the turbine T described above in that a sealing member 41 is added. The sealing member 41 is provided to seal the space between the base portion 35a of the vane member 35 and the housing of the turbine T1. In other words, the sealing member 41 is provided to prevent exhaust gas from leaking out from between the base portion 35a and the housing of the turbine T1 into the containment space 29.

[0044] The sealing member 41 is provided between the base portion 35a of the vane member 35 and the housing of the turbine T1. In the example shown in Figure 4, the sealing member 41 is provided between the inner circumference of the base portion 35a and the cylindrical wall portion W3 of the groove portion 5b of the turbine housing 5. The sealing member 41 has an annular shape and is arranged coaxially with the turbine impeller 15. For example, the sealing member 41 is sandwiched between an annular groove formed around the entire circumference of the inner circumference of the base portion 35a and an annular groove formed around the entire circumference of the cylindrical wall portion W3. The cross-sectional shape of the sealing member 41 may be rectangular, as in the example shown in Figure 4, or it may be a shape other than rectangular (for example, circular).

[0045] The space between the base portion 35a and the cylindrical wall portion W3 is sealed by the sealing member 41. Therefore, even if some exhaust gas leaks out to the containment space 29 side from between the elastic member 39 and the base portion 35a, the passage of exhaust gas between the base portion 35a and the cylindrical wall portion W3 is suppressed. Thus, the unintended flow of exhaust gas that would otherwise flow from the communication passage 33 into the containment space 29 through the shroud side (left side in Figure 3) of the base portion 35a is more effectively suppressed.

[0046] As explained above, in the turbine T1, a sealing member 41 is provided between the base portion 35a and the housing of the turbine T1. This more effectively suppresses the flow of unintended exhaust gas that would otherwise flow from the communication passage 33 into the containment space 29, passing through the shroud side (left side in Figure 3) of the base portion 35a. Therefore, the decrease in the efficiency of the turbine T1 can be more effectively suppressed.

[0047] In the above example, the sealing member 41 is provided between the inner circumference of the base portion 35a and the cylindrical wall portion W3 of the groove portion 5b of the turbine housing 5. However, the sealing member 41 is not limited to the above example and may be provided between the base portion 35a and the housing of the turbine T1. For example, the sealing member 41 may be provided between the left end face of the base portion 35a and the cylindrical wall portion W3 of the groove portion 5b of the turbine housing 5. For example, the sealing member 41 may be provided upstream of the contact point between the elastic member 39 and the base portion 35a in the exhaust gas flow.

[0048] Figure 5 is a partially enlarged view showing the turbine T2 of the second modified example. The turbine T2 of the second modified example differs from the turbine T described above in that a heat shield 43 is added. The heat shield 43 is provided to shield heat from entering the bearing housing 3 from the turbine housing 5 and its interior.

[0049] The turbine T2 housing includes a heat shield 43. The heat shield 43 is located in the part of the bearing housing 3 that faces the internal space of the turbine housing 5. In other words, the heat shield 43 corresponds to the left-side part of the bearing housing 3. In the example in Figure 5, the heat shield 43 extends radially from the inner circumference to the outer circumference of the bearing housing 3. However, the heat shield 43 does not have to extend to the inner circumference of the bearing housing 3, nor does it have to extend to the outer circumference of the bearing housing 3.

[0050] The heat shield 43 conducts heat less effectively than the other parts of the bearing housing 3. As a result, heat input from the turbine housing 5 and its interior into the bearing housing 3 is blocked, protecting the interior of the bearing housing 3 from heat. In the example shown in Figure 5, the left wall portion of the heat shield 43 corresponds to the first inner wall portion W1. Thus, the first inner wall portion W1 is formed in the heat shield 43.

[0051] As described above, the turbine T2 is equipped with a heat shield 43 having a first inner wall portion W1. This allows for protection of the inside of the bearing housing 3 from heat while suppressing a decrease in the efficiency of the turbine T2, similar to the turbine T described above.

[0052] In turbine T2, a sealing member 41 may be added, similar to turbine T1 described above.

[0053] While embodiments of this disclosure have been described above with reference to the attached drawings, it goes without saying that this disclosure is not limited to such embodiments. It will be obvious to those skilled in the art that various modifications or alterations can be conceived within the scope of the claims, and these will naturally also fall within the technical scope of this disclosure.

[0054] The above example describes an example where the elastic member 39 is a disc spring. However, the elastic member 39 is not limited to a disc spring. For example, the elastic member 39 may be a coil spring. For example, the elastic member 39 may be a metal gasket formed from a thin metal film.

[0055] The above describes an example where turbines T, T1, and T2 are single-scroll type (a type in which there is one turbine scroll flow path 31a), but the type of turbines T, T1, and T2 is not limited to the above example. For example, turbines T, T1, and T2 may be double-scroll type (a type in which two turbine scroll flow paths 31a are connected to the housing space 29 at different circumferential positions), or twin-scroll type (a type in which two turbine scroll flow paths 31a are arranged side by side in the rotation axis direction of the turbine impeller 15).

[0056] The above describes an example in which turbines T, T1, and T2 are installed on a supercharger TC. However, turbines T, T1, and T2 may be installed on devices other than the supercharger TC. [Explanation of symbols]

[0057] 3: Bearing housing (housing) 5: Turbine housing (housing) 15: Turbine blade 27: Discharge passage 29: Containment space 31a: Turbine scroll passage 33: Communication passage 35: Vane member 35a: Base part 35b: Vane part 39: Elastic member 41: Seal member 43: Heat shield T: Turbine T1: Turbine T2: Turbine TC: Supercharger W1: First inner wall W2: Second inner wall

Claims

1. A housing includes a housing space for accommodating a turbine impeller, a turbine scroll passage positioned radially outward from the turbine impeller, a communication passage connecting the turbine scroll passage and the housing space, and a discharge passage continuous with respect to the housing space in the direction of the rotation axis of the turbine impeller. The vane member provided in the communication passage includes a plurality of vane portions facing the first inner wall portion that faces the communication passage from the opposite side of the discharge passage, and a base portion to which the plurality of vane portions are fixed, An elastic member sandwiched between the second inner wall portion facing the communication channel from the discharge channel side and the vane member, Equipped with, The base portion comes into contact with the elastic member, A cylindrical wall portion extending in the direction of the rotation axis is formed in the portion of the housing facing the first inner wall portion. The aforementioned base portion is annular, The inner circumference of the base portion fits into the cylindrical wall portion, The outer periphery of the base portion is not fitted into the housing. The elastic member is a disc spring, The elastic member and the base portion are in contact with each other over the entire circumference of the turbine blade. Turbine.

2. A sealing member is provided between the base portion and the housing. The turbine according to claim 1.

3. A heat shield plate having the first inner wall portion is provided, The turbine according to claim 1.

4. A turbine comprising the turbine according to any one of claims 1 to 3, Supercharger.

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