turbocharger

Abstract

It helps to suppress the decline in reliability. [Solution] The supercharger 1 comprises a turbine housing 21 that houses a turbine impeller 22, a bearing housing 41 that rotatably supports a rotating shaft 11 to which the turbine impeller 22 is fixed, a nozzle plate 52 facing the turbine housing 21, and a fixed nozzle unit 5 having a plurality of nozzle vanes 51 arranged around the turbine impeller 22 and fixed to the nozzle plate 52, and a rotation restricting part 6 including a pin 61 and a pin insertion part 62 into which the pin 61 is inserted for restricting the position of the fixed nozzle unit 5 along the circumferential direction. The turbine housing 21 is provided with a pin 61. The nozzle plate 52 is provided with a pin insertion part 62.

Description

Technical Field

[0001] The present invention relates to a supercharger.

Background Art

[0002] Patent Document 1 discloses a technology related to a supercharger. The supercharger of Patent Document 1 includes a plurality of nozzle vanes. The plurality of nozzle vanes form a flow path for guiding gas to a turbine impeller. The flow path formed by the nozzle vanes has a constant cross-sectional area. The cross-sectional area of the flow path does not change according to the operating conditions of the supercharger. That is, the nozzle vanes are fixed to a ring member.

Prior Art Documents

Patent Documents

[0003]

Patent Document 1

Summary of the Invention

Problems to be Solved by the Invention

[0004] In the supercharger of Patent Document 1, the ring member to which the nozzle vanes are fixed is a component separated from the bearing housing and the turbine housing. Therefore, the ring member can move relative to the bearing housing and the turbine housing. When the components constituting the supercharger move relative to each other, wear occurs at the rubbing portions. The wear of the components may affect the reliability of the supercharger.

[0005] An object of the present invention is to provide a supercharger capable of suppressing a decrease in reliability.

Means for Solving the Problems

[0006] A supercharger according to one embodiment of the present invention comprises a turbine housing for housing a turbine impeller, a bearing housing that rotatably supports a rotating shaft to which the turbine impeller is fixed, a nozzle plate facing the turbine housing, and a fixed nozzle unit having a plurality of nozzle vanes arranged around the turbine impeller and fixed to the nozzle plate, and a rotation restricting part including a pin and a pin insertion part into which the pin is inserted for restricting the position of the fixed nozzle unit along the circumferential direction, wherein one of the turbine housing and the nozzle plate is provided with the pin and the pin insertion part, and the other of the turbine housing and the nozzle plate is provided with the pin and the pin insertion part.

[0007] This turbocharger is equipped with a rotation restricting unit. The rotation restricting unit restricts the position of the fixed nozzle unit along the circumferential direction. Therefore, the movement of the fixed nozzle unit relative to the turbine housing is suppressed. As a result, wear caused by relative movement between parts is suppressed, and thus the deterioration of the turbocharger's reliability can be suppressed.

[0008] The turbine housing of the supercharger described above may be provided with pins. The nozzle plate may be provided with a pin insertion portion. With this configuration, the nozzle plate can be easily attached to the turbine housing.

[0009] The nozzle plate of the supercharger described above may be provided with a first nozzle vane and a second nozzle vane adjacent to each other along the circumferential direction. The rotation restrictor may be positioned between the leading edge of the first nozzle vane and the leading edge of the second nozzle vane. Gas flows into the nozzle formed by the fixed nozzle unit. By positioning the rotation restrictor between the leading edge of the first nozzle vane and the leading edge of the second nozzle vane, the influence of the rotation restrictor on the gas flow can be suppressed.

[0010] The nozzle plate in the supercharger described above may have an annular nozzle vane arrangement section where nozzle vanes are arranged, and a regulating arrangement section where either a pin or a pin insertion section is provided. The distance from the central axis of the nozzle plate to the pin and pin insertion section provided in the regulating arrangement section may be greater than the distance from the central axis of the nozzle plate to the outer edge of the nozzle vane arrangement section. This configuration makes it possible to reduce the weight of the nozzle plate.

[0011] The pin insertion portion of the supercharger described above may be a through hole. With this configuration, the pin can be easily inserted into the pin insertion portion.

[0012] The pin insertion portion of the supercharger described above may be an elongated hole with one end open in the radial direction. This configuration also allows for easy insertion of the pin into the pin insertion portion.

[0013] The turbine housing of the supercharger described above may be provided with a pin insertion section. The nozzle plate may also be provided with a pin. This configuration also allows the nozzle plate to be easily attached to the turbine housing.

[0014] The nozzle plate of the supercharger described above may have an annular nozzle vane arrangement portion where nozzle vanes are arranged, and an annular rotation restricting portion where either a pin or a pin insertion portion is provided. The outer diameter of the rotation restricting portion may be larger than the outer diameter of the nozzle vane arrangement portion. This configuration also helps to suppress the influence of the rotation restricting portion on the gas flow. [Effects of the Invention]

[0015] According to the present invention, it is possible to provide a supercharger that can suppress a decrease in reliability. [Brief explanation of the drawing]

[0016] [Figure 1] Figure 1 is a cross-sectional view showing a supercharger according to an embodiment. [Figure 2]FIG. 2 is an enlarged view showing an enlarged view of the main part of the supercharger shown in FIG. 1. [Figure 3] FIG. 3 is a cross-sectional view of the supercharger shown in FIG. 1 viewed from the direction of the rotation axis. [Figure 4] FIG. 4 is a plan view for explaining the nozzle plate. [Figure 5] FIG. 5 is a cross-sectional view showing a supercharger of a modified example. [Figure 6] FIG. 6(a) is a cross-sectional view showing a first modified example of the rotation restricting portion. FIG. 6(b) is a cross-sectional view showing a second modified example of the rotation restricting portion. [Figure 7] FIG. 7(a) is a cross-sectional view showing a third modified example of the rotation restricting portion. FIG. 7(b) is a cross-sectional view showing a fourth modified example of the rotation restricting portion.

MODE FOR CARRYING OUT THE INVENTION

[0017] Hereinafter, embodiments for carrying out the present invention will be described in detail with reference to the accompanying drawings. In the description of the drawings, the same elements are denoted by the same reference numerals, and redundant descriptions are omitted.

[0018] Hereinafter, embodiments of the present invention will be described in detail while referring to the drawings. FIG. 1 is a cross-sectional view taken along a cross-section including the rotation axis H of the supercharger 1. The supercharger 1 is applied to, for example, an internal combustion engine of a ship or a vehicle.

[0019] As shown in FIG. 1, the supercharger 1 includes a turbine 2 and a compressor 3. The turbine 2 includes a turbine housing 21 and a turbine impeller 22 housed in the turbine housing 21. The turbine housing 21 has a scroll flow path 23 extending in the circumferential direction around the turbine impeller 22. The compressor 3 includes a compressor housing 31 and a compressor impeller 32 housed in the compressor housing 31. The compressor housing 31 has a scroll flow path 33 extending in the circumferential direction around the compressor impeller 32.

[0020] The turbine impeller 22 is provided at the first end of the rotating shaft 11, and the compressor impeller 32 is provided at the second end of the rotating shaft 11. A bearing housing 41 is provided between the turbine housing 21 and the compressor housing 31. The rotating shaft 11 is rotatably supported by the bearing housing 41 via a bearing 12. The rotating shaft 11, the turbine impeller 22, and the compressor impeller 32 rotate around the rotation axis H as an integral rotating body.

[0021] The turbine housing 21 is provided with an exhaust gas inlet 24 and an exhaust gas outlet 25. The exhaust gas discharged from the internal combustion engine flows into the turbine housing 21 through the exhaust gas inlet 24, flows into the turbine impeller 2 through the scroll flow path 23, and rotates the turbine impeller 22. Then, the exhaust gas flows out of the turbine housing 21 through the exhaust gas outlet 25.

[0022] The compressor housing 31 is provided with a suction port 34 and a discharge port 35. When the turbine impeller 22 rotates as described above, the compressor impeller 32 rotates via the rotating shaft 11. The rotating compressor impeller 32 sucks external air through the suction port 34. This air passes through the compressor impeller 32 and the scroll flow path 33, is compressed, and is discharged from the discharge port 35. The compressed air discharged from the discharge port 35 is supplied to the aforementioned internal combustion engine.

[0023] The turbine 2 of the supercharger 1 will be further described. In the following description, when simply referring to "axial direction", "radial direction", and "circumferential direction", they respectively mean the rotation axis direction (rotation axis H direction), the rotation radial direction, and the rotation circumferential direction of the turbine impeller 22. Also, when referring to "upstream", "downstream", etc., they mean the upstream and downstream of the exhaust gas in the turbine 2. Further, in the rotation axis H direction, the turbine 2 side (left side in FIG. 1) of the supercharger 1 may be simply referred to as the "turbine side", and the compressor 3 side (right side in FIG. 1) may be simply referred to as the "compressor side".

[0024] The turbine 2 of the supercharger 1 is provided with a nozzle passage 50 that connects the scroll passage 23 and the turbine impeller 22, which is located around the turbine impeller 22. The nozzle passage 50 is provided with a plurality of movable nozzle vanes 51. The plurality of nozzle vanes 51 are arranged at approximately equal intervals on a circumference centered on the rotation axis H. Each nozzle vane 51 is fixed to the nozzle plate 52. In other words, the gap between adjacent nozzle vanes 51 does not expand or contract according to the operating conditions of the supercharger 1, and remains constant regardless of the operating conditions.

[0025] The supercharger 1 is equipped with a fixed nozzle unit 5. The fixed nozzle unit 5 is fitted inside the turbine housing 21. The fixed nozzle unit 5 has the above-mentioned plurality of nozzle vanes 51 and a nozzle plate 52 on which the nozzle vanes 51 are provided. The nozzle plate 52 is ring-shaped with respect to the axis of rotation H.

[0026] As shown in Figure 2, the turbine 2 has a flow path that guides the gas flowing through the scroll flow path 23 to the turbine 2. This flow path is formed by the turbine housing flow path surface 211 of the turbine housing 21 and the bearing housing flow path surface 411 of the bearing housing 41. The turbine housing flow path surface 211 is provided with a protrusion 211A that projects toward the bearing housing flow path surface 411. The nozzle plate 52 is fitted into this protrusion 211A. More specifically, the protrusion 211A is fitted into the nozzle plate through hole 52H of the nozzle plate 52. This fitting defines the position of the nozzle plate 52 in a direction perpendicular to the rotation axis H. For example, the central axis of the nozzle plate 52 coincides with the rotation axis H.

[0027] When the nozzle plate 52 is fitted into the turbine housing 21, the turbine housing flow path surface 211 faces the nozzle plate back surface 522 of the nozzle plate 52. A gap is formed between the turbine housing flow path surface 211 and the nozzle plate 52. A disc spring 13 is positioned in this gap. The disc spring 13 generates a force along the axis of rotation H. In other words, the disc spring 13 presses the nozzle plate 52 toward the bearing housing 41. More specifically, the disc spring 13 presses the nozzle vane end faces 514 of the nozzle vanes 51 provided on the nozzle plate 52 toward the bearing housing flow path surface 411. As a result, the nozzle flow path 50 is formed as a region enclosed by the main nozzle plate surface 521 of the nozzle plate 52, the nozzle vane side surfaces 513 of adjacent nozzle vanes 51, and the bearing housing flow path surface 411.

[0028] As previously mentioned, the nozzle plate 52 is fitted into the protrusion 211A of the turbine housing 21. More specifically, the inner circumferential surface of the nozzle plate through-hole 52H contacts the outer circumferential surface of the protrusion 211A of the turbine housing 21. Since the inner circumferential surface of the nozzle plate through-hole 52H and the outer circumferential surface of the protrusion 211A are perpendicular to the radial direction, even if the nozzle plate 52 tries to move in the radial direction, the protrusion 211A of the turbine housing 21 generates a restraining force that prevents its movement. On the other hand, if the nozzle plate 52 tries to move in the circumferential direction, the protrusion 211A of the turbine housing 21 and the inner circumferential surface of the nozzle plate through-hole 52H do not generate a substantial restraining force.

[0029] The movement of the fixed nozzle unit 5 along the circumferential direction is constrained by the frictional force generated between the nozzle vane end face 514 and the bearing housing flow path surface 411. This frictional force is determined by the coefficient of friction between the nozzle vane end face 514 and the bearing housing flow path surface 411 and the magnitude of the pressing force exerted by the disc spring 13. When the supercharger 1 is in operation, hot gas flows from the scroll flow path 23 toward the turbine impeller 22. Consequently, the turbine housing 21, the fixed nozzle unit 5, and the bearing housing 41 are exposed to a high-temperature environment, causing the temperature of each component to rise. As the temperature of the components rises, thermal deformation occurs, changing the distance of the gap from the turbine housing flow path surface 211 to the back surface 522 of the nozzle plate. This change in the gap leads to a change in the compressed length of the disc spring 13, and this change in the compressed length of the disc spring 13 causes a change in the pressing force generated by the disc spring 13. Furthermore, the disc spring 13 is also exposed to the hot gas, causing its temperature to rise as well. As a result, the elastic modulus of the disc spring 13 changes, which in turn causes a change in the pressing force generated by the disc spring 13. This change in pressing force causes a change in the frictional force between the nozzle vane end face 514 and the bearing housing flow path surface 411. The decrease in frictional force reduces the restraining force on the movement of the fixed nozzle unit 5 along the circumferential direction, making it easier for the fixed nozzle unit 5 to move along the circumferential direction relative to the turbine housing 21.

[0030] Therefore, the supercharger 1 is equipped with a rotation restricting unit 6 to restrict the movement of the fixed nozzle unit 5 along the circumferential direction.

[0031] As shown in Figures 2 and 3, the rotation restricting section 6 includes a pin 61 and a pin insertion section 62. The pin 61 is fixed to the turbine housing 21. The pin insertion section 62 is provided on the nozzle plate 52. When the fixed nozzle unit 5 attempts to move along the circumferential direction, the wall surface of the pin insertion section 62 is pressed against the circumferential surface of the pin 61. Since the pin 61 is fixed to the turbine housing 21, it does not move even when pressed against it. As a result, the fixed nozzle unit 5 also does not move along the circumferential direction. In other words, the configuration in which the pin 61 fits into the pin insertion section 62 restricts the movement of the fixed nozzle unit 5 along the circumferential direction. The rotation restricting section 6 will be described in more detail below.

[0032] As shown in Figure 4, the rotation restricting section 6 is located on the outer circumference of the nozzle plate 52. The nozzle plate 52 is annular in shape when viewed from above. The main surface 521 of the nozzle plate 52 includes a nozzle vane arrangement section 521A and a restricting arrangement section 521B. The nozzle vane arrangement section 521A and the restricting arrangement section 521B are flush with each other, and there do not need to be any lines or other markings that explicitly distinguish the nozzle vane arrangement section 521A and the restricting arrangement section 521B. The nozzle vane arrangement section 521A is provided with a plurality of nozzle vanes 51. The inner circumferential edge of the nozzle vane arrangement section 521A may be defined by the trailing edge 512 of the nozzle vanes 51. The outer circumferential edge of the nozzle vane arrangement section 521A may be defined by the leading edge 511 of the nozzle vanes 51.

[0033] The restricting section 521B protrudes radially from the outer edge of the nozzle vane section 521A. In other words, the restricting section 521B is located outside the nozzle flow path 50 formed between adjacent nozzle vanes 51A and 51B. The gas gradually increases in velocity as it flows through the nozzle flow path 50. Since the restricting section 521B is located outside the nozzle flow path 50, the flow velocity of the gas passing through the restricting section 521B is slower than the flow velocity of the gas flowing through the nozzle flow path 50. The gas then flows into the nozzle flow path 50 after passing through the restricting section 521B. Therefore, the gas is not affected by the restricting section 521B while it is increasing in velocity.

[0034] The restricting section 521B is located approximately in the center of the arc connecting the leading edge 511 of nozzle vane 51A and the leading edge 511 of nozzle vane 51B in the circumferential direction. Therefore, the distance along the arc from the restricting section 521B to the leading edge 511 of nozzle vane 51A is approximately the same as the distance along the arc from the restricting section 521B to the leading edge 511 of nozzle vane 51B. The gas flow velocity between the leading edge 511 of nozzle vane 51A and the leading edge 511 of nozzle vane 51B is slower than the gas flow velocity in the vicinity of the leading edges 511 of nozzle vanes 51A and 51B. By positioning components that may affect the gas flow at locations where the gas flow velocity is slow, the impact on the gas flow can be suppressed.

[0035] Furthermore, the regulating section 521B may be positioned near the tongue section 212 (see Figure 3) of the turbine housing 21. The tongue section 212 is formed in the portion that defines the end of the scroll flow path 23.

[0036] As shown in Figure 2, the turbine housing 21 is provided with a pin hole 21H into which the base end 612 of the pin 61 is press-fitted. The opening of the pin hole 21H is formed in the turbine housing flow path surface 211. Since the restricting arrangement portion 521B is located outside the nozzle flow path 50, the pin hole 21H is also located outside the nozzle flow path 50 when viewed from above.

[0037] Since the pin 61 is located outside the nozzle flow path 50, the pin 61 does not come into contact with the disc spring 13. The pin 61 is positioned radially outward from the outer edge of the disc spring 13.

[0038] For example, suppose the turbine housing 21 is made of high-silicon ductile iron (HI-SI-FCD) and the pin 61 is made of stainless steel (SUS304). In this case, the coefficient of thermal expansion of the high-silicon ductile iron (HI-SI-FCD) is smaller than that of the stainless steel (SUS304). Therefore, even if thermal deformation occurs, the pin 61 will not fall out. Also, if a small gap (play) occurs between the pin 61 and the nozzle plate 52, wear of the parts may occur. In this case, the wear occurs on the nozzle plate 52. If the nozzle plate 52 is made of heat-resistant cast steel (SCH21), it is advantageous in terms of wear resistance.

[0039] The pin tip 611 does not protrude from the main surface 52K1 of the nozzle plate bulge 52K. The position of the pin tip 611 is closer to the turbine housing flow path surface 211 than to the main surface 52K1 of the nozzle plate bulge 52K. This positional relationship between the pin tip 611 and the main surface 52K1 of the bulge is maintained even when the supercharger 1 is not operating. Furthermore, this positional relationship between the pin tip 611 and the main surface 52K1 of the bulge is maintained even when the supercharger 1 is operating and thermal deformation is occurring.

[0040] As shown in Figure 4, the nozzle plate 52 of the supercharger 1 includes a nozzle plate base 520 including a nozzle vane arrangement portion 521A, and a nozzle plate bulge portion 52K that protrudes radially from the outer circumferential surface of the nozzle plate base 520. The nozzle plate bulge portion 52K is semicircular in plan view. The pin insertion portion 62 is provided in the nozzle plate bulge portion 52K. The pin insertion portion 62 extends radially from the outer circumferential surface of the nozzle plate bulge portion 52K along the nozzle plate base 520. In other words, the pin insertion portion 62 is a so-called elongated hole. One end of the pin insertion portion 62 is an opening formed on the outer circumferential surface of the nozzle plate bulge portion 52K. The other end of the pin insertion portion 62 is an arc-shaped inner circumferential surface. The inner circumferential surface is located outside the nozzle flow path 50. In other words, the pin insertion portion 62 does not extend to the nozzle flow path 50. For example, the other end of the pin insertion portion 62 may overlap with the outer edge of the nozzle vane arrangement portion 521A.

[0041] <Effects and Effects> The supercharger 1 comprises a turbine housing 21 that houses a turbine impeller 22, a bearing housing 41 that rotatably supports a rotating shaft 11 to which the turbine impeller 22 is fixed, a nozzle plate 52 facing the turbine housing 21, and a fixed nozzle unit 5 having a plurality of nozzle vanes 51 arranged around the turbine impeller 22 and fixed to the nozzle plate 52, and a rotation restricting unit 6 including a pin 61 and a pin insertion part 62 into which the pin 61 is inserted for restricting the position of the fixed nozzle unit 5 along the circumferential direction.

[0042] The turbocharger 1 is equipped with a rotation restricting unit 6. The rotation restricting unit 6 restricts the position of the fixed nozzle unit 5 along the circumferential direction. Therefore, the movement of the fixed nozzle unit 5 relative to the turbine housing 21 is suppressed. As a result, wear caused by relative movement between parts is suppressed, and thus a decrease in the reliability of the turbocharger 1 can be suppressed.

[0043] The turbine housing 21 is provided with a pin 61. The nozzle plate 52 is provided with a pin insertion portion 62. With this configuration, the nozzle plate 52 can be easily attached to the turbine housing 21.

[0044] The rotation restricting section 6 is positioned between the leading edge 511 of nozzle vane 51A and the leading edge 511 of nozzle vane 51B. Gas flows into the nozzle flow path 50 formed by the fixed nozzle unit 5. By positioning the rotation restricting section 6 between the leading edge 511 of nozzle vane 51A and the leading edge 511 of nozzle vane 51B, the influence of the rotation restricting section 6 on the gas flow can be suppressed.

[0045] The nozzle plate 52 has an annular nozzle vane arrangement section 521A where the nozzle vanes 51 are arranged, and a restricting arrangement section 521B where a pin insertion section 62 is provided. The distance from the central axis of the nozzle plate 52 to the pin insertion section 62 provided in the restricting arrangement section 521B is greater than the distance from the central axis of the nozzle plate 52 to the outer edge of the nozzle vane arrangement section 521A. This configuration makes it possible to reduce the weight of the nozzle plate 52.

[0046] The pin insertion portion 62 is a through hole. The pin insertion portion 62 is an elongated hole with one end open in the radial direction. With this configuration, the pin 61 can be easily inserted into the pin insertion portion 62.

[0047] <Variation> The compressor of the present invention is not limited to the embodiments described above, and does not depart from the spirit of the present invention. Various transformations are possible within the enclosure.

[0048] As shown in Figure 5, the nozzle plate 52A may include a nozzle plate base 520 and a nozzle plate outer periphery 52G. In the nozzle plate 52 of the embodiment, a restrictive arrangement portion 521B was provided on the nozzle plate bulge portion 52K that partially bulges out from the nozzle plate base 520. In the nozzle plate 52A of Modification 1, the nozzle plate outer periphery 52G that surrounds the entire circumference of the nozzle plate base 520 may be the restrictive arrangement portion 521B.

[0049] The outer periphery 52G of the nozzle plate is integrated with the base 520 of the nozzle plate, and there is no need for a configuration that explicitly distinguishes them. When a virtual circle 511C is defined that connects the leading edges 511 of multiple nozzle vanes 51, the inside of the virtual circle 511C may be considered the base 520 of the nozzle plate, and the outside of the virtual circle 511C may be considered the outer periphery 52G of the nozzle plate.

[0050] A pin insertion portion 62 is provided on the outer circumference 52G of the nozzle plate. The details of the pin insertion portion 62 are the same as those of the pin insertion portion 62 in the embodiment.

[0051] The nozzle plate 52A of the supercharger 1A in Modified Example 1 has a nozzle plate base 520 including an annular nozzle vane arrangement portion 52S on which the nozzle vanes 51 are arranged, and an annular nozzle plate outer periphery 52G. The outer diameter of the nozzle plate outer periphery 52G is larger than the outer diameter of the nozzle plate base 520. This configuration also makes it possible to suppress the influence of the nozzle plate outer periphery 52G on the gas flow.

[0052] <Modifications 2-4> In the embodiment, the pin insertion portion 62 was a through groove. Furthermore, the pin insertion portion 62 was a long groove with one end open. The pin insertion portion 62 is not limited to this configuration. Other examples of the pin insertion portion 62 will be described as Modifications 2 to 4. The pin insertion portions 62B, 62C, and 62D shown in Modifications 2 to 4 below can be provided on the nozzle plate bulge portion 52K exemplified in the embodiment. Furthermore, the pin insertion portions 62B, 62C, and 62D shown in Modifications 2 to 4 can also be provided on the outer circumference 52G of the nozzle plate exemplified in Modification 1.

[0053] As shown in Figure 6(a), the pin insertion portion 62B may be a groove with a bottom. Furthermore, the pin insertion portion 62B may be an elongated groove with one end open. As shown in Figure 6(b), the pin insertion portion 62C may be a groove with a bottom. Furthermore, the pin insertion portion 62C may be an elongated groove with both ends closed. As shown in Figure 7(a), the pin insertion portion 62D may be a blind hole. Furthermore, the pin insertion portion 62D may be a round hole with an inner diameter slightly larger than the outer diameter of the pin 61. With these configurations, the main surface 52K1 of the bulge becomes a flat surface. Therefore, the influence of the regulating arrangement portion 521B on the gas can be further suppressed.

[0054] <Modification 5> In this embodiment, the pin 61 was provided in the turbine housing 21, and the pin insertion portion 62 was provided in the nozzle plate 52. As illustrated in Modification 5, the pin 61 may be provided in the nozzle plate 52E. Furthermore, the pin insertion portion 62E may be provided in the turbine housing 21E. The nozzle plate bulge 52K is provided with a pin hole 52P having an opening on the bulge back surface 52K2. The pin hole 52P is an interference fit for the pin 61. In other words, the pin 61 is fixed to the nozzle plate 52E. The turbine housing 21E is provided with a pin insertion portion 62E having an opening on the turbine housing flow path surface 211. The pin insertion portion 62E is a blind hole. Also, as shown in Figure 7(b), the pin insertion portion 62E may be a round hole or an elongated hole.

[0055] [Note] This disclosure includes the following components:

[0056] This disclosure includes [1] a turbine housing that accommodates a turbine blade, A bearing housing that rotatably supports the rotating shaft to which the turbine blades are fixed, A nozzle plate facing the turbine housing, and a fixed nozzle unit having a plurality of nozzle vanes arranged around the turbine impeller and fixed to the nozzle plate, The device includes a pin for regulating the position of the fixed nozzle unit along the circumferential direction and a rotation restricting portion including a pin insertion portion into which the pin is inserted, The turbine housing and the nozzle plate are provided with either the pin or the pin insertion portion. A supercharger in which the other of the turbine housing and the nozzle plate is provided with the pin and the other of the pin insertion portion.

[0057] This disclosure includes [2] "The turbine housing is provided with the pin, The supercharger described in [1] above, wherein the nozzle plate is provided with the pin insertion portion.

[0058] This disclosure includes [3] "The nozzle plate is provided with a first nozzle vane and a second nozzle vane that are adjacent to each other along the circumferential direction, The rotation restricting unit is located between the leading edge of the first nozzle vane and the leading edge of the second nozzle vane in the supercharger described in [1] or [2] above.

[0059] This disclosure includes, [4] "the nozzle plate having an annular nozzle vane arrangement portion on which the nozzle vanes are arranged, and a regulating arrangement portion on which either the pin or the pin insertion portion is provided, The supercharger according to any one of the above [1] to [3], wherein the distance from the central axis of the nozzle plate to the pin and the pin insertion portion provided in the regulating arrangement portion is greater than the distance from the central axis of the nozzle plate to the outer edge of the nozzle vane arrangement portion.

[0060] This disclosure is [5] "a supercharger according to any one of the above [1] to [4], wherein the pin insertion portion is a through hole."

[0061] This disclosure is [6] "a supercharger according to any one of the above [1] to [5], wherein the pin insertion portion is an elongated hole with one radial end open."

[0062] This disclosure includes [7] "The turbine housing is provided with the pin insertion portion, The supercharger described in [1] above, wherein the nozzle plate is provided with the pin.

[0063] This disclosure includes [8] "the nozzle plate having an annular nozzle vane arrangement portion on which the nozzle vanes are arranged, and an annular rotation restricting portion on which either the pin or the pin insertion portion is provided, The supercharger described in [1] above, wherein the outer diameter of the rotation restricting portion is larger than the outer diameter of the nozzle vane arrangement portion. [Explanation of Symbols]

[0064] 1.1A turbocharger 11 Rotation axis 12 bearings 13 Disc springs 2 Turbines 21 Turbine Housing 21E Turbine Housing 21H pinhole 22 Turbine Blade Vehicle 23 Scroll channel 24 Exhaust gas inlet 25 Exhaust gas outlet 211 Turbine housing flow path surface 211A Convex part 212 Tongue 3 Compressors 31 Compressor Housing 32 Compressor Blade Car 33 Scroll channel 34 Inlet 35 Discharge port 41 Bearing Housing 411 Bearing housing flow path surface 5 Fixed nozzle unit 50 Nozzle Flow Channels 51, 51A, 51B Nozzle vanes 52S Nozzle vane arrangement section 52 Nozzle Plate 52A Nozzle Plate 52G Nozzle plate outer circumference 52H Nozzle plate through hole 52P pinhole 52K Nozzle Plate Bulge 52K1 Main surface of bulge 52K2 bulging back 511 Leading edge 511C Virtual Yen 512 Trailing edge 513 Nozzle vane side 514 Nozzle vane end face 520 Nozzle plate base 521 Nozzle plate main surface 521A Nozzle vane arrangement section 521B Regulation placement part 522 Nozzle plate back 6. Rotation restriction section 61 pins 62 Pin insertion section 62B, 62C, 62D, 62E Pin insertion section 611 Pin tip H rotation axis

Claims

1. A turbine housing that houses the turbine blades, A bearing housing that rotatably supports the rotating shaft to which the turbine blades are fixed, A nozzle plate facing the turbine housing, and a fixed nozzle unit having a plurality of nozzle vanes arranged around the turbine impeller and fixed to the nozzle plate, The device includes a pin for regulating the position of the fixed nozzle unit along the circumferential direction and a rotation restricting portion including a pin insertion portion into which the pin is inserted, The turbine housing and the nozzle plate are provided with either the pin or the pin insertion portion. A supercharger in which the other of the turbine housing and the nozzle plate is provided with the pin and the other of the pin insertion portion.

2. The turbine housing is provided with the pin, The supercharger according to claim 1, wherein the nozzle plate is provided with the pin insertion portion.

3. The nozzle plate is provided with a first nozzle vane and a second nozzle vane that are adjacent to each other along the circumferential direction. The supercharger according to claim 1, wherein the rotation restricting portion is disposed between the leading edge of the first nozzle vane and the leading edge of the second nozzle vane.

4. The nozzle plate has an annular nozzle vane arrangement portion on which the nozzle vanes are arranged, and a restricting arrangement portion on which either the pin or the pin insertion portion is provided. The supercharger according to claim 1, wherein the distance from the central axis of the nozzle plate to the pin and the pin insertion portion provided in the regulating arrangement portion is greater than the distance from the central axis of the nozzle plate to the outer edge of the nozzle vane arrangement portion.

5. The supercharger according to claim 1, wherein the pin insertion portion is a through hole.

6. The supercharger according to claim 1, wherein the pin insertion portion is an elongated hole with one end open in the radial direction.

7. The turbine housing is provided with the pin insertion portion, The supercharger according to claim 1, wherein the nozzle plate is provided with the pin.

8. The nozzle plate has an annular nozzle vane arrangement portion on which the nozzle vanes are arranged, and an annular rotation restricting portion on which either the pin or the pin insertion portion is provided. The supercharger according to claim 1, wherein the outer diameter of the rotation restricting portion is larger than the outer diameter of the nozzle vane arrangement portion.

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