Turbine and turbocharger

Abstract

A turbine is provided with: a first housing having a scroll flow path; a first plate-like member including an annular first plate portion; a second plate-like member including an annular second plate portion that forms a gas flow path between the first plate portion and the second plate portion; a second case having an opposing surface that opposes a rear surface of the first plate section on the opposite side of the gas flow path with a first space therebetween; an annular member disposed in the first space and rotating with respect to the first plate-like member; a link member, one end of which is connected to the annular member and the other end of which is connected to the variable nozzle vane; a positioning pin, one end of which is embedded into a first hole formed in the back surface of the first plate part, and the other end of which is embedded into a second hole formed in the opposite surface of the second housing; and a stopper portion that forms a first gap between the stopper portion and the facing surface or between the stopper portion and the first plate portion, the first gap being configured so as to be smaller than a second gap between the annular member and the facing surface and a third gap between the link member and the facing surface.

Description

Technical Field

[0001] The invention relates to a turbine and a turbocharger. Background Art

[0002] As a turbocharger (supercharger) that uses the energy of the exhaust gas of an internal combustion engine (engine) to supercharge the intake air of the internal combustion engine, a turbocharger with a variable capacity turbine is known (for example, refer to Patent Document 1). The variable capacity turbine has a plurality of nozzle blades arranged in a circumferential direction of the turbine impeller in an exhaust gas flow path for conveying exhaust gas from the vortex flow path of the turbine to the turbine impeller, and the flow path cross-sectional area of ​​the exhaust gas flow path (the flow path between adjacent nozzle blades) can be adjusted by changing the blade angle of these nozzle blades from the outside by an actuator. The variable capacity turbine improves the supercharging effect by adjusting the flow path cross-sectional area of ​​the exhaust gas flow path, changing the flow velocity or pressure of the exhaust gas guided by the turbine impeller.

[0003] Patent document 1 discloses a technology in which two plate-like components (nozzle mount and nozzle plate) forming an exhaust gas flow path are connected via a nozzle support, and a press-fit pin (positioning pin) for positioning the nozzle mount and a bearing housing is pressed into a press-fit hole formed on the nozzle mount.

[0004] Previous technical literature

[0005] Patent Literature

[0006] Patent Document 1: Japanese Patent Publication No. 2013-072401 Summary of the invention

[0007] Technical issues to be solved by the invention

[0008] Due to thermal deformation during operation of the variable capacity turbine, the nozzle mounting part attempts to approach the bearing housing side, and the press-in pin is excessively inserted into the press-in hole, increasing the friction resistance between the press-in pin and the press-in hole, and there is a possibility that the press-in pin is fixed to the press-in hole. If the press-in pin is fixed to the press-in hole, the variable nozzle mechanism's retaining structure cannot be maintained, and the variable nozzle mechanism floats, which may be exposed to the risk of wear due to vibration.

[0009] In view of the above circumstances, an object of at least one embodiment of the present invention is to provide a turbine and a turbocharger capable of stably maintaining a holding structure of a variable nozzle unit by suppressing fixation by a positioning pin.

[0010] Means for solving technical problems

[0011] A turbine according to at least one embodiment of the present invention includes:

[0012] A first housing having a vortex flow path;

[0013] A turbine impeller is arranged on the inner peripheral side of the vortex flow path;

[0014] A first plate-shaped member including a first annular plate portion;

[0015] a second plate-shaped member including an annular second plate portion, the second plate portion being arranged opposite to the first plate portion and forming a gas flow path from the vortex flow path toward the turbine impeller between the second plate portion and the first plate portion;

[0016] at least one variable nozzle vane disposed in the gas flow path;

[0017] a second housing having an opposing surface, the opposing surface being opposed to the back surface of the first plate portion on the side opposite to the flow path wall surface facing the gas flow path with a first space therebetween;

[0018] an annular member disposed in the first space and configured to rotate relative to the first plate-shaped member by a driving force from the outside;

[0019] at least one connecting rod member, one end of which is connected to the annular member and the other end of which is connected to the variable nozzle vane, wherein the at least one connecting rod member is linked to the rotation of the annular member to change the vane angle of the variable nozzle vane connected to the other end;

[0020] a biasing member disposed between the second housing and the first plate-shaped member and configured to bias the first plate portion toward the gas flow path;

[0021] at least one positioning pin, one end of which is embedded in a first hole formed on the back surface of the first plate portion, and the other end of which is embedded in a second hole formed on the opposite surface of the second shell; and

[0022] At least one stop portion is arranged on the opposing surface or the first plate portion, and a first gap is formed between the stop portion and the opposing surface, or between the stop portion and the first plate portion, and the first gap is constructed in a manner smaller than the second gap between the annular part and the opposing surface and the third gap between the at least one connecting rod part and the opposing surface.

[0023] A turbocharger according to at least one embodiment of the present invention includes: the turbine; and a centrifugal compressor configured to be driven by the turbine.

[0024] Effects of the Invention

[0025] According to at least one embodiment of the present invention, there is provided a turbine and a turbocharger capable of stably maintaining a holding structure of a variable nozzle unit by suppressing fixation of a positioning pin. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 It is a schematic diagram of an internal combustion engine system including a turbocharger according to an embodiment.

[0027] Figure 2 This is a schematic cross-sectional view along the axis of a turbine according to one embodiment.

[0028] Figure 3 This is a schematic diagram of a variable nozzle unit included in a turbine according to one embodiment.

[0029] Figure 4 This is a schematic cross-sectional view showing a cross section along an axis that is closer to one side than the axis of the turbine according to one embodiment.

[0030] Figure 5 This is a schematic cross-sectional view showing a cross section along an axis that is closer to one side than the axis of the turbine according to one embodiment.

[0031] Figure 6 This is a schematic cross-sectional view showing a cross section along an axis that is closer to one side than the axis of the turbine according to one embodiment.

[0032] Figure 7 This is a schematic cross-sectional view showing a cross section along an axis that is closer to one side than the axis of the turbine according to one embodiment.

[0033] Figure 8 This is an explanatory diagram for explaining the tongue vicinity side and the tongue distal side.

[0034] Fig. 9 This is a schematic diagram of a variable nozzle unit included in a turbine according to one embodiment.

[0035] Fig.10 This is a schematic cross-sectional view showing a cross section along an axis that is closer to one side than the axis of the turbine according to one embodiment. DETAILED DESCRIPTION

[0036] Hereinafter, several embodiments of the present invention will be described with reference to the accompanying drawings. However, the dimensions, materials, shapes, and relative arrangements of the components described as embodiments or shown in the accompanying drawings are not intended to limit the scope of the present invention, but are merely illustrative examples.

[0037] (Turbocharger)

[0038] Figure 1It is a schematic diagram of an internal combustion engine system 10 having a turbocharger 1 involved in one embodiment. The turbine 2 involved in the present invention can be mounted on a turbocharger (supercharger) 1 for automobiles, ships or industrial use (for example, for land power generation), etc. In the following embodiments, the turbine 2 mounted on the turbocharger 1 is used as an example for description, but the turbine 2 involved in the present invention is not limited to the turbine mounted on the turbocharger 1. In addition, it is not necessary to limit the working fluid of the turbine 2 to exhaust gas. That is, as long as the turbine 2 of the present invention can convert the energy of the working fluid into mechanical power (for example, rotational force), the turbine 2 can be constituted alone, or it can be constituted in combination with a mechanism or device other than the centrifugal compressor 12. In addition, it is not necessary to limit the use of the turbine 2, etc.

[0039] like Figure 1 As shown, a turbocharger 1 according to some embodiments is driven by the energy of exhaust gas discharged from an internal combustion engine (engine) 11 and is configured to compress a fluid (for example, air). The turbocharger 1 includes a turbine 2 and a centrifugal compressor 12 configured to be driven by the turbine 2.

[0040] The centrifugal compressor 12 includes an impeller 13 and a compressor housing 14 configured to rotatably accommodate the impeller 13. The turbine 2 includes at least a turbine impeller 3, a first housing (turbine housing) 4, and a second housing (bearing housing) 5 configured to rotatably accommodate the turbine impeller 3 between the first housing 4.

[0041] like Figure 1 As shown, the turbocharger 1 further includes: a rotating shaft 15, one end of which is connected to the turbine impeller 3, and the other end of which is connected to the impeller 13; and a bearing 16, which is configured to rotatably support the rotating shaft 15 between the turbine impeller 3 and the impeller 13. The second housing 5 is arranged between the first housing 4 and the compressor housing 14, and is respectively connected to the first housing 4 and the compressor housing 14 via fastening members (not shown), such as bolts or nuts. The second housing 5 can be configured to accommodate the bearing 16.

[0042] The turbine 2 of the turbocharger 1 is configured so that the turbine impeller 3 is rotated by the energy of the exhaust gas discharged from the internal combustion engine 11. Since the impeller 13 is coaxially connected to the turbine impeller 3 via the rotating shaft 15, it is driven to rotate around the axis LA in conjunction with the rotation of the turbine impeller 3. The centrifugal compressor 12 of the turbocharger 1 is configured so that air (supply air, gas) is sucked into the interior of the compressor housing 14 by driving the impeller 13 to rotate around the axis LA, the air is compressed, and the compressed air is delivered to the internal combustion engine 11.

[0043] The compressed air supplied from the centrifugal compressor 12 to the internal combustion engine 11 is provided for combustion in the internal combustion engine 11. The exhaust gas generated by the combustion in the internal combustion engine 11 is supplied from the internal combustion engine 11 to the turbine 2, and causes the turbine impeller 3 to rotate.

[0044] (impeller)

[0045] like Figure 1 As shown in the figure, the impeller 13 is connected to the other end side of the rotating shaft 15, and is therefore integrally rotatably provided with the rotating shaft 15 around the axis of the impeller 13. The impeller 13 is configured so as to guide the air introduced along the axial direction of the impeller 13 to the outer side in the radial direction of the impeller 13. In the illustrated embodiment, the impeller 13 is composed of an open impeller that does not include an annular member surrounding the outer periphery of the blades of the impeller 13.

[0046] (Compressor housing)

[0047] A gas introduction flow path 141 and a scroll flow path 142 are formed inside the compressor housing 14. In other words, the compressor housing 14 has the gas introduction flow path 141 and the scroll flow path 142.

[0048] The gas introduction flow path 141 is a flow path for sucking air (gas) from the outside of the compressor housing 14 (centrifugal compressor 12) and guiding the sucked air to the impeller 13. The gas introduction flow path 141 is provided on the side closer to the impeller 13 in the axial direction of the impeller 13 than the impeller 13, and extends along the axial direction of the impeller 13. By driving the impeller 13 to rotate, air is sucked from the outside of the compressor housing 14 into the gas introduction flow path 141, and the sucked air flows toward the impeller 13 through the gas introduction flow path 141 and is guided to the impeller 13.

[0049] The vortex flow path 142 is composed of a vortex flow path provided on the outer peripheral side of the impeller 13 and extending in the circumferential direction of the impeller 13. The air passing through the impeller 13 and compressed by the impeller 13 is guided to the vortex flow path 142. The compressed air passing through the vortex flow path 142 is guided to the internal combustion engine 11.

[0050] Figure 2 1 is a schematic cross-sectional view along the axis LA of the turbine 2 according to one embodiment. Hereinafter, the direction in which the axis LA of the turbine impeller 3 extends is referred to as the axial direction of the turbine impeller 3, the direction orthogonal to the axis LA is referred to as the radial direction of the turbine impeller 3, and the circumferential direction around the axis LA is referred to as the circumferential direction of the turbine impeller 3. Hereinafter, in the axial direction of the turbine impeller 3, the first housing 4 is disposed on the side where the second housing 5 is located ( Figure 2 The right side in the middle is defined as the front side, and the second housing 5 is opposite to the side where the first housing 4 is located (the side opposite to the front side, Figure 2 The left side of the middle is defined as the posterior side.

[0051] (Turbine impeller)

[0052] like Figure 2 As shown, the turbine impeller 3 includes a hub 31 having a substantially truncated cone shape and a plurality of turbine blades 32 provided on the outer peripheral surface of the hub 31. The plurality of turbine blades 32 are arranged at intervals from each other in the circumferential direction around the axis LA. The hub 31 and the plurality of turbine blades 32 are rotatably provided integrally with the rotating shaft 15 around the axis LA. The turbine impeller 3 is configured in such a manner that the exhaust gas introduced from the outer side in the radial direction of the turbine impeller 3 is guided to the front side of the turbine impeller 3 along the axial direction of the turbine impeller 3.

[0053] (vortex flow path, exhaust gas flow path)

[0054] A vortex flow path 41 for guiding the exhaust gas discharged from the internal combustion engine 11 to the turbine impeller 3 and an exhaust gas discharge flow path 42 for discharging the exhaust gas passing through the turbine impeller 3 to the outside of the first housing 4 (turbine 2) are formed inside the first housing 4. In other words, the first housing 4 has the vortex flow path 41 and the exhaust gas discharge flow path 42. The vortex flow path 41 is composed of a vortex-shaped flow path provided on the outer peripheral side of the turbine impeller 3 and extending along the circumferential direction of the turbine impeller 3. The exhaust gas discharge flow path 42 extends from the turbine impeller 3 toward the front side along the axial direction of the turbine impeller 3.

[0055] The first housing 4 and the second housing 5 are fastened to form an internal space 43 connecting the scroll flow path 41 and the exhaust gas discharge flow path 42 between the first housing 4 and the second housing 5. The turbine impeller 3 is accommodated in the internal space 43 so as to be rotatable relative to the first housing 4 and the second housing 5. The turbine impeller 3 is provided on the inner peripheral side of the scroll flow path 41.

[0056] The exhaust gas discharged from the internal combustion engine 11 is guided to the turbine impeller 3 via the swirl flow path 41 to rotate the turbine impeller 3. The exhaust gas that rotates the turbine impeller 3 is discharged to the outside of the first housing 4 (turbine 2) via the exhaust gas discharge flow path 42.

[0057] (Variable nozzle unit)

[0058] Figure 3 1 is a schematic diagram of a variable nozzle unit 6 provided in a turbine 2 according to an embodiment. Figure 2 As shown, the turbine 2 is further provided with a variable nozzle unit 6 on the outer peripheral side of the turbine impeller 3 accommodated in the above-mentioned internal space 43. The variable nozzle unit 6 forms a gas flow path (exhaust gas flow path) 43A for guiding the exhaust gas from the vortex flow path 41 to the turbine impeller 3, and is used to adjust the flow of the exhaust gas in the gas flow path 43A. The gas flow path 43A is a part of the internal space 43. The gas flow path 43A is formed between the vortex flow path 41 and the turbine impeller 3 in a manner surrounding the periphery of the turbine impeller 3 (outer side in the radial direction).

[0059] like Figure 2 As shown, the variable nozzle unit 6 includes a first plate-shaped member (nozzle mounting member) 7, a second plate-shaped member (nozzle plate) 8, at least one (plural in the illustrated example) variable nozzle blade 61, an annular member (drive ring) 62 and at least one (plural in the illustrated example) connecting rod member (rod plate) 63.

[0060] (First plate-shaped member)

[0061] The first plate-like member (nozzle mount) 7 includes an annular first plate portion 71 extending along the circumferential direction of the turbine impeller 3 on the outer peripheral side of the turbine impeller 3. A first flow path wall surface 72 facing the gas flow path 43A is formed on the front side of the first plate portion 71, and a back surface 73 is formed on the rear side of the first plate portion 71, that is, on the side opposite to the first flow path wall surface 72.

[0062] (Second plate-shaped member)

[0063] The second plate-shaped member (nozzle plate) 8 includes an annular second plate portion 81, which is arranged opposite to the first plate portion 71 and forms a gas flow path 43A from the swirl flow path 41 toward the turbine impeller 3 between the second plate portion 81 and the first plate portion. The second plate portion 81 is arranged on the front side of the first plate portion 71 and extends along the circumferential direction of the turbine impeller 3 on the outer peripheral side of the turbine impeller 3. A second flow path wall surface 82 facing the gas flow path 43A is formed on the rear side of the second plate portion 81.

[0064] The gas flow path 43A is formed between the first flow path wall surface 72 and the second flow path wall surface 82. The first flow path wall surface 72 is located at a position further rearward than the second flow path wall surface 82 and faces the second flow path wall surface 82. The exhaust gas introduced into the turbine 2 passes through the swirl flow path 41 and then passes through the gas flow path 43A, and then is guided to the turbine impeller 3, causing the turbine impeller 3 to rotate.

[0065] (Supporting parts)

[0066] like Figure 2 As shown, the variable nozzle unit 6 may further include at least one (for example, a plurality of) supporting members (nozzle supports) 64 that support the first plate-shaped member 7 and the second plate-shaped member 8 in a state separated from each other. The plurality of supporting members 64 are arranged at intervals in the circumferential direction of the turbine impeller 3. One side of each of the plurality of supporting members 64 is fixed to the first plate portion 71, and the other side is fixed to the second plate portion 81. The second plate-shaped member 8 is supported by the supporting member 64 so as to be separated from the first plate-shaped member 7 toward the front side.

[0067] (Space 1)

[0068] The second housing 5 has an opposing surface 51 that opposes the back surface 73 of the first plate portion 71 with the first space 43B interposed therebetween. The first space 43B is a part of the internal space 43 and is formed on the opposite side of the gas flow path 43A with the first plate portion 71 interposed therebetween.

[0069] (Variable nozzle vanes)

[0070] Each of the plurality of variable nozzle blades 61 is disposed in the gas flow path 43A and supported by the first plate portion 71 (first plate member 7 ) so as to be rotatable about its own rotation center RC. The plurality of variable nozzle blades 61 are disposed at intervals in the circumferential direction of the turbine impeller 3 .

[0071] (Ring-shaped parts)

[0072] The annular member (drive ring) 62 is disposed in the first space 43B, and is configured to rotate about the axis LB of the annular member 62 (variable nozzle unit 6 ) relative to the first plate member 7 by a drive force from the outside.

[0073] (Drive mechanism, control device)

[0074] like Figure 2 As shown, the turbine 2 further includes: a driving mechanism (actuator) 65, which transmits driving force to the annular member 62 so as to rotate the annular member 62 around its axis LB; and a control device (controller) 66, which controls the annular member 62 to rotate around the axis LB. The driving mechanism 65 includes an electric motor that generates driving force, a cylinder that transmits driving force, and the like.

[0075] (Connecting rod parts)

[0076] like Figure 3 As shown, the variable nozzle unit 6 includes the same number of link members (lever plates) 63 as the variable nozzle vanes 61. The plurality of link members 63 are respectively arranged in the first space 43B, one end 631 of which is connected to the annular member 62, and the other end 632 of which is connected to the variable nozzle vane 61, and is configured so as to change the vane angle of the variable nozzle vane 61 connected to the other end 632 in conjunction with the rotation of the annular member 62.

[0077] exist Figure 3In the embodiment shown, one end 631 of each connecting rod member 63 includes a fitting portion 631A that fits with the fitting portion 621 formed on the annular member 62. The fitting portion 621 includes a groove portion 621A formed on the outer peripheral edge of the annular member 62, and the fitting portion 631A is accommodated in the groove portion 621A and loosely fits with the groove portion 621A. A plurality of through holes 74 penetrating the first flow path wall surface 72 and the back surface 73 are provided on the first plate portion 71. The plurality of through holes 74 are arranged at intervals in the circumferential direction of the turbine impeller 3. The same number of through holes 74 as the variable nozzle blades 61 and the connecting rod member 63 are formed on the first plate portion 71. The above-mentioned other end of each connecting rod member 63 is inserted through the through holes 74 corresponding to the connecting rod member 63, and is connected to the variable nozzle blades 61 corresponding to the connecting rod member 63.

[0078] If the annular member 62 is rotated toward one side in the circumferential direction of the turbine impeller 3, the variable nozzle blades 61 adjacent in the circumferential direction move (rotate) in the direction of separation from each other, and the flow path cross-sectional area of ​​the gas flow path 43A between the variable nozzle blades 61 increases. Furthermore, if the annular member 62 is rotated toward the other side in the circumferential direction of the turbine impeller 3, the variable nozzle blades 61 adjacent in the circumferential direction move (rotate) in the direction of approaching each other, and the flow path cross-sectional area of ​​the gas flow path 43A between the variable nozzle blades 61 decreases.

[0079] The variable nozzle unit 6 transmits the driving force from the outside of the variable nozzle unit 6 (driving mechanism 65) to the plurality of variable nozzle blades 61 via the annular member 62 and the plurality of link members 63, so that the plurality of variable nozzle blades 61 rotate around the respective rotation centers RC, and the respective blade angles are changed, thereby adjusting the flow path cross-sectional area of ​​the gas flow path 43A. The turbine 2 can change the flow velocity or pressure of the exhaust gas guided to the turbine impeller 3 by increasing or decreasing the flow path cross-sectional area of ​​the gas flow path 43A by the variable nozzle unit 6, thereby controlling the boost pressure of the turbine 2.

[0080] (Force applying component)

[0081] Figure 4 1 is a schematic cross-sectional view showing a cross section along the axis LA which is closer to one side than the axis LA of the turbine 2 according to one embodiment. Figure 4 As shown, the turbine 2 further includes a biasing member 21 which is disposed between the second housing 5 and the first plate member 7 and is configured to bias the first plate portion 71 toward the gas flow path 43A side.

[0082] exist Figure 4In the illustrated embodiment, the urging member 21 includes a coil spring 21A, and the coil spring 21A abuts against an end surface 52 formed radially inward of the facing surface 51 of the second housing 5 and an end surface 75A of the inner peripheral edge portion 75 of the first plate portion 71 on the side opposite to the first flow path wall surface 72. The end surface 75A is formed radially inward of the back surface 73. By sealing between the end surface 52 of the second housing 5 and the end surface 75A of the first plate portion 71 by the coil spring 21A (urging member 21), the inflow of exhaust gas from the back side of the turbine impeller 3 into the first space 43B is suppressed.

[0083] The first housing 4 includes a locked portion 44 extending in the radial direction of the turbine impeller 3 and being locked by the outer peripheral edge portion 76 of the first plate portion 71. The locked portion 44 has a rear vortex flow path wall surface 441 extending radially outward from the rear end P1 of the vortex flow path 41, and a locked surface 442 located on the side opposite to the rear vortex flow path wall surface 441 in the axial direction and facing the first space 43B.

[0084] The first plate-shaped member 7 is forced forward by the force-applying member 21, so that the outer peripheral edge portion 76 of the first plate portion 71 is pressed against the clamped portion 44 of the first housing 4, and the front side clamping surface 76A of the outer peripheral edge portion 76 abuts against the clamped surface 442. Thus, the front side clamping surface 76A and the clamped surface 442 are sealed to suppress the inflow of exhaust gas from the vortex flow path 41 to the first space 43B. In the illustrated embodiment, the clamping surface 76A is composed of a step surface formed on the outer side and rear side of the first flow path wall surface 72 in the radial direction. In addition, in other embodiments, the outer peripheral edge portion 76 of the first plate portion 71 can also be clamped between the first housing 4 and the second housing 5.

[0085] exist Figure 4 In the illustrated embodiment, the first housing 4 includes a front facing surface 45 facing the second back surface 83 of the second plate portion 81, and a shroud portion 46 protruding radially inward from the second plate portion 81 and the front facing surface 45 and further rearward from the front facing surface 45. The shroud portion 46 has a shroud surface 46A that is curved in a convex shape so as to face the top side ends (front ends) of the plurality of turbine blades 32 and to form a gap (interval) with the top side ends.

[0086] (First embodiment)

[0087] like Figure 4 As shown, the turbine 2 according to the embodiments at least comprises the turbine wheel 3, the first housing 4, the second housing 5, the first plate member 7, the second plate member 8, the force applying member 21, at least one variable nozzle blade 61, the annular member 62 and at least one connecting rod member 63. Figure 4As shown, the turbine 2 further includes at least one positioning pin 9 and at least one stopper 22. In addition, this embodiment can be implemented independently of other embodiments.

[0088] (Location pin)

[0089] Regarding at least one positioning pin 9, Figure 4 As shown, one end 91 of the positioning pin 9 is embedded (for example, pressed) into the first hole 77 formed on the back surface 73 of the first plate portion 71, and the other end 92 of the positioning pin 9 is embedded (for example, pressed) into the second hole 53 formed on the opposing surface 51 of the second housing 5. The positioning pin 9 is formed in a rod shape having a length direction along the axial direction of the turbine 2. The positioning pin 9 is made of, for example, a metal material. In order to improve the assemblability of the turbine 2, the variable nozzle unit 6 is connected to the second housing 5 via the positioning pin 9 to prevent the variable nozzle unit 6 from falling off from the second housing 5.

[0090] (Stop)

[0091] At least one stopper 22 is disposed on the opposing surface 51 or the first plate portion 71. Figure 4 As shown, at least one stopper 22 may be integrally formed with the first plate portion 71 or integrally formed with the opposing surface 51. Furthermore, at least one stopper 22 may be a component different from the opposing surface 51 or the first plate portion 71 and mounted on the opposing surface 51 or the first plate portion 71.

[0092] like Figure 4 As shown, the turbine 2 has a first gap G1 formed between the stopper 22 and the facing surface 51 (illustrated example), or between the stopper 22 and the first plate portion 71. The first gap G1 is configured to be smaller than the second gap G2 between the annular member 62 and the facing surface 51, and the third gap G3 between the facing surface 51 and at least one connecting rod member 63.

[0093] According to the above structure, the first plate-shaped member 7 approaches the second housing 5 side due to thermal deformation during operation of the turbine 2, but the stopper 22 abuts against the opposing surface 51 of the second housing 5 or the first plate portion 71, thereby limiting the movement of the first plate-shaped member 7 toward the second housing 5 side. By limiting the movement of the first plate-shaped member 7 toward the second housing 5 side, the positioning pin 9 can be prevented from being excessively inserted into the first hole 77 or the second hole 53 and fixed to the first hole 77 or the second hole 53.

[0094] Here, assuming that the turbine 2 does not have the stopper 22, the first plate-shaped member 7 may be closer to the second housing 5 side than the first gap G1 due to thermal deformation during operation of the turbine 2. In this case, the positioning pin 9 is excessively inserted into the first hole 77 or the second hole 53, and the friction resistance between the first hole 77 or the second hole 53 and the positioning pin 9 increases. Therefore, the holding structure of the variable nozzle unit 6 cannot be maintained by the reaction force based on the force applying member 21 (the force that pushes the first plate-shaped member 7 back to the gas flow path 43A side), and a gap is generated between the outer peripheral edge portion 76 of the first plate-shaped member 7 and the locked portion 44 of the first housing 4, and the variable nozzle unit 6 may float in the first space 43B. In this case, there is a risk of wear and the like due to vibration of the variable nozzle unit 6.

[0095] According to the above structure, by limiting the movement of the first plate-shaped member 7 toward the second housing 5 side by the stopper 22, it is possible to suppress the positioning pin 9 from being fixed to the first hole 77 or the second hole 53 and hindering the reaction force of the force-applying member 21. In this case, the holding structure of the variable nozzle unit 6 (first plate-shaped member 7) can be stably maintained by the reaction force of the force-applying member 21. By stably maintaining the holding structure of the variable nozzle unit 6, the risk of wear and the like due to vibration of the variable nozzle unit 6 can be reduced.

[0096] In some embodiments, the at least one stopper 22 is formed integrally with the first plate-shaped member 7. In this case, compared with the case where the stopper 22 is a member different from the first plate-shaped member 7 or the second housing 5, the increase in the number of components can be suppressed, and the complexity of the structure of the turbine 2 can be suppressed. In addition, when the stopper 22 is formed integrally with the second housing 5, when the variable nozzle unit 6 is assembled to the second housing 5, the stopper 22 may interfere with the variable nozzle unit 6, but when the stopper 22 is formed integrally with the first plate-shaped member 7, this possibility is small. In addition, it is easier to form the stopper 22 on the first plate-shaped member 7 than to form the stopper 22 on the second housing 5.

[0097] In several embodiments, such as Figure 3 and Figure 4 As shown, the above-mentioned first plate-like component 7 includes: a cylindrical portion 78, which protrudes from the back side 73 of the first plate portion 71 and is inserted into the center hole of the annular component 62; and at least one claw portion 22A, which protrudes from the cylindrical portion 78 to the outer peripheral side than the inner peripheral edge of the annular component 62 and clamps the inner peripheral edge of the annular component 62 between the back side 73 of the first plate portion 71.

[0098] The at least one stopper 22 includes at least one claw 22A. That is, the claw 22A of the first plate-shaped member 7 is used as the stopper 22.

[0099] exist Figure 3 In the illustrated embodiment, at least one claw portion 22A includes a plurality of (three in the illustrated example) claw portions 22A arranged at intervals along the circumferential direction of the turbine impeller 3. The same number of recesses 622 as the claw portions 22A are formed on the inner circumference of the annular member 62 so that the claw portions 22A pass therethrough when the first plate-shaped member 7 and the annular member 62 are assembled.

[0100] According to the above structure, by utilizing at least one claw portion 22A of the inner peripheral edge of the clamping annular component 62 as the stopper portion 22, it is possible to avoid re-setting the stopper protrusion on the first plate-shaped component 7, thereby reducing the portion of the first plate-shaped component 7 that is changed from the existing shape, and suppressing the complexity of the structure of the first plate-shaped component 7.

[0101] exist Figure 4 , Figure 5 In the embodiment shown, the second housing 5 has a protrusion 54 protruding forward from the opposing surface 51 along the axial direction of the turbine impeller 3. The protrusion 54 may be formed in an arc shape or an annular shape extending along the circumferential direction of the turbine impeller 3. The turbine 2 forms a fourth gap G4 between the front end surface 54A of the protrusion 54 in the axial direction and the back surface 73 of the first plate portion 71. Figure 4 , Figure 5 In the illustrated embodiment, the protrusion 54 (end surface 54A) is a part of the facing surface 51, and is formed radially inward of the outer peripheral edge of the protrusion 54 where the facing surface 51 is not formed, and radially outward of the end surface 52. The back surface 73 of the first plate portion 71 includes an inner peripheral back surface 73A at its inner peripheral edge that forms a fourth gap G4 with the end surface 54A.

[0102] exist Figure 4 In the illustrated embodiment, the fourth gap G4 is configured to be larger than the second gap G2 and the third gap G3 .

[0103] In several embodiments, such as Figure 5 As shown in FIG. 1 , the fourth gap G4 is configured to be smaller than the second gap G2 and the third gap G3. In this case, the protrusion 54 can be used as the stopper 22. Figure 5 In the illustrated embodiment, the at least one stopper portion 22 is a protrusion 54 formed integrally with the second housing 5. The fourth gap G4 becomes the first gap G1.

[0104] According to the above structure, by using the protrusion 54 as the stopper 22, it is not necessary to newly set the stopper protrusion on the second shell 5, so that the parts of the second shell 5 that are changed from the existing shape can be reduced, and the complexity of the structure of the second shell 5 can be suppressed.

[0105] (Second embodiment)

[0106] Figure 5 1 is a schematic cross-sectional view showing a cross section along the axis LA which is closer to one side than the axis LA of the turbine 2 according to one embodiment. Figure 5 As shown, the turbine 2 according to the embodiments at least comprises the turbine wheel 3, the first housing 4, the second housing 5, the first plate member 7, the second plate member 8, the force applying member 21 and at least one variable nozzle blade 61. Figure 5 As shown, the turbine 2 further includes at least one positioning pin 9 and an adhesive layer 94. In addition, this embodiment can be implemented independently of other embodiments. For example, the turbine 2 may not include the above-mentioned stopper 22.

[0107] (Location pin)

[0108] Regarding at least one positioning pin 9, Figure 5 As shown, one end 91 of the positioning pin 9 is inserted into the first hole 77 formed on the back surface 73 of the first plate portion 71, and the other end 92 of the positioning pin 9 is inserted into the second hole 53 formed on the opposing surface 51 of the second housing 5. At least one of the one end 91 or the other end 92 of the positioning pin 9 is inserted in a state with gaps 93A and 93B. The positioning pin 9 is formed into a rod shape having a length direction along the axial direction of the turbine 2. The positioning pin 9 is made of, for example, a metal material. In the illustrated embodiment, one end 91 of the positioning pin 9 is loosely inserted into the first hole 77, and a gap 93A is formed between the outer peripheral surface of the one end 91 and the inner peripheral surface of the first hole 77. In addition, the other end 92 of the positioning pin 9 is loosely inserted into the second hole 53, and a gap 93B is formed between the outer peripheral surface of the other end 92 and the inner peripheral surface of the second hole 53.

[0109] (Adhesive layer)

[0110] The adhesive layer 94 is interposed in at least one of the gap 93A and the gap 93B. In the illustrated embodiment, the adhesive layer 94 is interposed in both the gap 93A and the gap 93B. The adhesive layer 94 is constructed in such a way that the adhesive strength is reduced due to the input heat when the turbine 2 is running. The gap 93A is more affected by the input heat when the turbine 2 is running than the gap 93B. Therefore, when the adhesive layer 94 is interposed in either the gap 93A or the gap 93B, it is preferred to interpose it in the gap 93A. In addition, the reduction in the adhesive strength of the adhesive layer 94 may be a temporary reduction when the turbine 2 is running, or it may be a permanent reduction. When the variable nozzle unit 6 is connected to the second housing 5 via the positioning pin 9 and the adhesive layer 94, since the adhesive strength of the adhesive layer 94 is not reduced, it is possible to prevent the variable nozzle unit 6 from falling off from the second housing 5.

[0111] According to the above structure, since the bonding strength of the bonding layer 94 is reduced due to the input heat when the turbine 2 is running, a gap is generated between at least one of the first hole 77 or the second hole 53 and the positioning pin 9. Therefore, when the first plate-shaped member 7 approaches the second housing 5 side due to thermal deformation when the turbine 2 is running, it is possible to suppress the positioning pin 9 from being fixed to the first hole 77 or the second hole 53. By suppressing the positioning pin 9 from being fixed to the first hole 77 or the second hole 53 and hindering the reaction force of the force applying member 21, the holding structure of the variable nozzle unit 6 (first plate-shaped member 7) can be stably maintained by the reaction force of the force applying member 21. By stably maintaining the holding structure of the variable nozzle unit 6, the risk of wear and the like caused by vibration of the variable nozzle unit 6 can be reduced.

[0112] In some embodiments, the adhesive layer 94 is made of a thermoplastic resin material, which may include at least one of phenoxy resin, polyurethane resin, polyester polyurethane resin, butyryl resin, acrylic resin, polyimide resin and polyamide resin.

[0113] According to the above structure, the adhesive layer 94 composed of thermoplastic resin material is softened (for example, liquefied) by the input heat when the turbine 2 is running, thereby reducing the bonding strength of the adhesive layer 94 and effectively generating gaps 93A, 93B between at least one of the first hole 77 or the second hole 53 and the positioning pin 9.

[0114] (Third embodiment)

[0115] Figure 6 1 is a schematic cross-sectional view showing a cross section along the axis LA which is closer to one side than the axis LA of the turbine 2 according to one embodiment. Figure 6 As shown, the turbine 2 according to the embodiments at least comprises the turbine wheel 3, the first housing 4, the second housing 5, the first plate member 7, the second plate member 8, the force applying member 21 and at least one variable nozzle blade 61. Figure 6 As shown, the turbine 2 further includes at least one positioning pin 9 and a sliding layer 95. In addition, this embodiment can be implemented independently of other embodiments. For example, the turbine 2 may not include the above-mentioned stopper 22.

[0116] (Location pin)

[0117] Regarding at least one positioning pin 9, Figure 6 As shown, one end 91 of the positioning pin 9 is inserted into the first hole 77 formed on the back surface 73 of the first plate portion 71, and the other end 92 of the positioning pin 9 is inserted into the second hole 53 formed on the opposing surface 51 of the second housing 5. The positioning pin 9 is formed into a rod shape having a length direction along the axial direction of the turbine 2. The positioning pin 9 is made of, for example, a metal material.

[0118] (Sliding layer)

[0119] The sliding layer 95 includes a solid lubricant covering at least one of the outer circumferential surface 911 of one end 91 of at least one positioning pin 9, the outer circumferential surface 921 of the other end 92 of at least one positioning pin 9, the inner circumferential surface 771 of the first hole 77, or the inner circumferential surface 531 of the second hole 53. The sliding layer 95 can be formed by applying or coating the solid lubricant to an object such as the outer circumferential surface 911, 921 of the positioning pin 9, the inner circumferential surface 771 of the first hole 77, or the inner circumferential surface 531 of the second hole 53. The solid lubricant can include at least one of molybdenum disulfide, graphite, and polytetrafluoroethylene (PTFE).

[0120] In the illustrated embodiment, the sliding layer 95 includes a first hole side sliding layer 95A covering at least one of the outer peripheral surface 911 of one end 91 of the positioning pin 9 or the inner peripheral surface 771 of the first hole 77, and a second hole side sliding layer 95B covering at least one of the outer peripheral surface 921 of the other end 92 of the positioning pin 9 or the inner peripheral surface 531 of the second hole 53. In addition, the sliding layer 95 may also be provided over the entire length of the positioning pin 9. The first hole side sliding layer 95A reduces the frictional resistance between the outer peripheral surface 911 of one end 91 of the positioning pin 9 and the inner peripheral surface 771 of the first hole 77. The second hole side sliding layer 95B reduces the frictional resistance between the outer peripheral surface 921 of the other end 92 of the positioning pin 9 and the inner peripheral surface 531 of the second hole 53.

[0121] According to the above structure, the friction resistance between at least one of the first hole 77 or the second hole 53 and the positioning pin 9 is reduced by the sliding layer 95, so that when the first plate-shaped member 7 approaches the second housing 5 side due to thermal deformation during the operation of the turbine 2, the positioning pin 9 can be prevented from being fixed to the first hole 77 or the second hole 53. By preventing the positioning pin 9 from being fixed to the first hole 77 or the second hole 53 and hindering the reaction force of the force-applying member 21, the holding structure of the variable nozzle unit 6 and the first plate-shaped member 7 can be stably maintained by the reaction force of the force-applying member 21. By stably maintaining the holding structure of the variable nozzle unit 6, the risk of wear and the like due to vibration of the variable nozzle unit 6 can be reduced.

[0122] Figure 7 It is a schematic cross-sectional view showing a cross section along the axis LA which is closer to one side than the axis LA of the turbine 2 according to one embodiment. Figure 8 This is an explanatory diagram for explaining the tongue proximal side S1 and the tongue distal side S2. Fig. 9 2 is a schematic diagram of a variable nozzle unit 6 provided in a turbine 2 according to an embodiment. Fig. 9 As shown, at least one of the first hole 77 and the second hole 53 has a length direction along the radial direction of the turbine impeller 3 .

[0123] The first plate portion 71 having the first hole 77 and the second housing 5 having the second hole 53 have a difference in thermal expansion when the turbine 2 is running, and a shear force caused by the difference in thermal expansion between the first plate portion 71 and the second housing 5 acts on the positioning pin 9.

[0124] According to the above configuration, by setting the hole shape of the first hole 77 or the second hole 53 to have a length direction along the radial direction of the turbine impeller 3, the first hole 77 or the second hole 53 is a circular hole (see Figure 3 ), since the positioning pin 9 does not restrict the thermal expansion between the first plate portion 71 and the second housing 5, it is possible to suppress the excessive load generated between the positioning pin 9 and the first hole 77 or between the positioning pin 9 and the second hole 53, thereby effectively suppressing the positioning pin 9 from being fixed to the first hole 77 or the second hole 53. In addition, according to the above-mentioned structure, since the shear force acting on the positioning pin 9 due to the difference in the thermal expansion between the first plate portion 71 and the second housing 5 can be reduced, it is possible to effectively suppress the positioning pin 9 from being fixed to the first hole 77 or the second hole 53.

[0125] like Figure 7 As shown, the second plate-shaped member 8 may include the second plate portion 81, a shroud surface 84 formed at the inner peripheral end of the second plate portion 81, and a cylindrical portion 85 protruding from the inner peripheral end of the second plate portion 81 toward the front side along the axial direction of the turbine impeller 3. The shroud surface 84 is curved in a convex shape in a manner opposed to the top side ends (front ends) of the plurality of turbine blades 32, and a gap (interval) is formed between the top side ends. The first housing 4 may include a front side facing surface 45 opposed to the second back side 83 of the second plate portion 81, and a step portion 47 connected to the inner peripheral end of the front side facing surface 45 and accommodating the cylindrical portion 85 of the second plate-shaped member 8.

[0126] like Figure 8 As shown, the tongue 48 of the vortex flow path 41 is formed between the winding start and the winding end of the vortex flow path 41. Figure 8 As shown, in a cross section perpendicular to the axial direction of the turbine impeller 3, a straight line passing through the axis LA of the turbine impeller 3 and the tongue 48, i.e., a first reference line, is defined as BL1, and a straight line passing through the axis LA of the turbine impeller 3 and perpendicular to the first reference line BL1, i.e., a second reference line, is defined as BL2. The side of the tongue 48 relative to the second reference line BL2 is defined as the tongue near side S1, and the side away from the tongue 48 relative to the second reference line BL2 is defined as the tongue far side S2.

[0127] In several embodiments, such as Fig. 9 As shown, the at least one positioning pin 9 includes a plurality of positioning pins 9 arranged at intervals along the circumferential direction of the turbine impeller 3. Fig. 9As shown, in a cross section perpendicular to the axis LA of the turbine impeller 3, a point CP having an equal distance from each center position LD (e.g., the centroid) of the plurality of positioning pins 9 is arranged closer to the tongue side (the tongue vicinity side S1) of the vortex flow path 41 than the axis LA of the turbine impeller 3.

[0128] The temperature of the gas flowing through the vortex flow path 41 is higher on the tongue 48 side of the variable nozzle unit 6 that is closer to the vortex flow path 41 than the axis LA of the turbine impeller 3, that is, the tongue near side S1, than the tongue far side S2 that is the opposite side that is farther from the tongue 48 than the axis LA of the turbine impeller 3. Therefore, between the tongue near side S1 and the tongue far side S2, the difference in thermal expansion due to the input heat from the gas flowing through the vortex flow path 41 is large, and the eccentricity of the axis LB of the variable nozzle unit 6 relative to the axis LA of the turbine impeller 3 may increase.

[0129] exist Figure 4 and Figure 7 In the embodiment shown, if the axis LB of the variable nozzle unit 6 is offset from the axis LA of the turbine impeller 3, the inner peripheral end of the first plate-shaped member 7 may contact the second housing 5. Figure 7 In the illustrated embodiment, the inner peripheral end portion of the second plate-shaped member 8 may come into contact with the turbine wheel 3 .

[0130] According to the above configuration, by eccentrically positioning the point CP (center point between the pins, centroid) at the same distance from each center position LD of the plurality of positioning pins 9 closer to the tongue vicinity side S1 than the axis LA of the turbine impeller 3, the positioning pin 9 on the tongue vicinity side S1 can suppress the above-mentioned thermal expansion of the tongue vicinity side S1, compared with the case where the center point CP between the pins is the same as the axis LA of the turbine impeller 3 or is eccentric to the tongue far side S2, so that the difference in the above-mentioned thermal expansion amount between the tongue vicinity side S1 and the tongue far side S2 can be reduced, and the increase in the eccentricity of the axis LB of the variable nozzle unit 6 with respect to the axis LA of the turbine impeller 3 can be suppressed. In this case, the variable nozzle unit 6 can be suppressed from contacting the first housing 4, the second housing 5, or the turbine impeller 3 due to the eccentricity of the axis LB of the variable nozzle unit 6 with respect to the axis LA of the turbine impeller 3, and the excessive contact load on the positioning action due to the contact can be suppressed. By suppressing the excessive contact load from acting on the positioning, it is possible to effectively suppress the positioning pin 9 from being fixed to the first hole 77 or the second hole 53 .

[0131] Fig.10 1 is a schematic cross-sectional view showing a cross section along the axis LA which is closer to one side than the axis LA of the turbine 2 according to one embodiment. Fig.10As shown, the urging member 21 ( 21B) includes at least a first urging plate portion 211 extending in the radial direction of the turbine impeller 3 and abutting against the second housing 5 , and a second urging plate portion 212 extending in the radial direction and abutting against the first plate-shaped member 7 .

[0132] In the illustrated embodiment, the first force plate portion 211 and the second force plate portion 212 are formed into an annular shape extending along the circumferential direction of the turbine impeller 3. The outer peripheral edge of the first force plate portion 211 abuts against the end surface 52 of the second housing 5, and the outer peripheral edge of the second force plate portion 212 abuts against the end surface 75A of the first plate portion 71. The force member 21 (21B) has an opening toward the outer side in the radial direction of the turbine impeller 3. Fig.10 In the illustrated embodiment, the urging member 21 ( 21B) has a V-shaped cross-section.

[0133] According to the above structure, compared with the case where a single plate member such as the coil spring 21A abuts against the second housing 5 and the first plate-shaped member 7, the force applying member 21 (21B) including the first force applying plate portion 211 and the second force applying plate portion 212 can increase the pushing force (reaction force) on the first plate portion 71. By increasing the pushing force (reaction force) of the force applying member 21 (21B) on the first plate portion 71, the holding structure of the variable nozzle unit 6 (first plate-shaped member 7) can be maintained more stably.

[0134] like Figure 1 As shown, the turbocharger 1 according to the embodiments includes the turbine 2 and the centrifugal compressor 12. In this case, since the holding structure of the variable nozzle unit 6 (the first plate-shaped member 7) can be stably maintained and the risk of wear and the like due to vibration of the variable nozzle unit 6 can be reduced, the reliability of the turbocharger 1 can be improved.

[0135] In this specification, expressions such as "in a certain direction", "along a certain direction", "parallel", "orthogonal", "center", "concentric" or "coaxial" that indicate a relative or absolute configuration not only indicate such a configuration in a strict sense, but also indicate a state of relative displacement at an angle or distance with a tolerance or to obtain the same degree of functionality.

[0136] For example, expressions such as “same”, “equal” and “homogeneous” that indicate a state of equality of objects not only indicate a state of equality in a strict sense, but also a state in which there are tolerances or differences in the degree to which the same functions can be obtained.

[0137] Furthermore, in this specification, expressions indicating shapes such as quadrilaterals and cylinders not only indicate shapes such as quadrilaterals and cylinders in a strict geometric sense, but also indicate shapes including concave-convex portions or chamfered portions within a range that can obtain the same effect.

[0138] Furthermore, in the present specification, the expression “having”, “including” or “having” one constituent element is not an exclusive expression excluding the presence of other constituent elements.

[0139] The present invention is not limited to the above-described embodiment, and includes a form in which modifications are added to the above-described embodiment, and a form in which these forms are appropriately combined.

[0140] The contents described in the above-mentioned several embodiments can be understood, for example, as follows.

[0141] 1) A turbine 2 according to at least one embodiment of the present invention includes:

[0142] The first housing 4 has a vortex flow path 41;

[0143] The turbine impeller 3 is arranged on the inner peripheral side of the vortex flow path 41;

[0144] The first plate-shaped member 7 includes a first annular plate portion 71;

[0145] The second plate-shaped member 8 includes an annular second plate portion 81, wherein the second plate portion 81 is disposed opposite to the first plate portion 71 and forms a gas flow path 43A from the swirl flow path 41 toward the turbine impeller 3 between the second plate portion 81 and the first plate portion 71;

[0146] at least one variable nozzle vane 61, disposed on the gas flow path 43A;

[0147] The second housing 5 has an opposing surface 51, and the opposing surface 51 is opposed to the back surface 73 of the first plate portion 71 on the side opposite to the flow path wall surface 72 facing the gas flow path 43A with the first space 43B interposed therebetween;

[0148] The annular member 62 is disposed in the first space 43B and is configured to rotate relative to the first plate-shaped member 7 by a driving force from the outside;

[0149] at least one connecting rod member 63, one end of which is connected to the annular member 62, and the other end of which is connected to the variable nozzle vane 61, wherein the at least one connecting rod member 63 rotates in conjunction with the annular member 62 to change the vane angle of the variable nozzle vane 61 connected to the other end;

[0150] The biasing member 21 is disposed between the second housing 5 and the first plate member 7 and is configured to bias the first plate portion 71 toward the gas flow path 43A.

[0151] at least one positioning pin 9, one end 91 of which is embedded in the first hole 77 formed on the back surface 73 of the first plate portion 71, and the other end 92 of which is embedded in the second hole 53 formed on the opposing surface 51 of the second housing 5; and

[0152] At least one stop portion 22 is arranged on the opposing surface 51 or the first plate portion 71, and a first gap G1 is formed between the stop portion 22 and the opposing surface 51, or between the stop portion 22 and the first plate portion 71, and the first gap G1 is configured to be smaller than the second gap G2 between the annular part 62 and the opposing surface 51 and the third gap G3 between the at least one connecting rod part 63 and the opposing surface 51.

[0153] According to the structure of 1) above, the first plate-shaped member 7 tends to approach the second housing 5 side due to thermal deformation during operation of the turbine 2, but the movement of the first plate-shaped member 7 toward the second housing 5 side can be restricted by making the stopper 22 abut against the opposing surface 51 of the second housing 5 or the first plate portion 71. By restricting the movement of the first plate-shaped member 7 toward the second housing 5 side, it is possible to suppress the positioning pin 9 from being excessively inserted into the first hole 77 or the second hole 53 and being fixed to the first hole 77 or the second hole 53. By suppressing the positioning pin 9 from being fixed to the first hole 77 or the second hole 53 and hindering the reaction force of the urging member 21, the holding structure of the variable nozzle unit 6 (first plate-shaped member 7) can be stably maintained by the reaction force of the urging member 21. By stably maintaining the holding structure of the variable nozzle unit 6, the risk of wear and the like due to vibration of the variable nozzle unit 6 can be reduced.

[0154] 2) In some embodiments, according to the turbine 2 described in 1) above, wherein:

[0155] The at least one stopper portion 22 is formed integrally with the first plate-shaped member 7 .

[0156] According to the structure of 2) above, compared with the case where the stopper 22 is a component different from the first plate-shaped member 7 or the second housing 5, the increase in the number of components can be suppressed, and the complexity of the structure of the turbine 2 can be suppressed. In addition, when the stopper 22 is formed integrally with the second housing 5, when the variable nozzle unit 6 is assembled to the second housing 5, the stopper 22 may interfere with the variable nozzle unit 6, but in the case where the stopper 22 is formed integrally with the first plate-shaped member 7, this possibility is small. In addition, it is easier to form the stopper 22 on the first plate-shaped member 7 than on the second housing 5.

[0157] 3) In some embodiments, according to the turbine 2 described in 1) or 2) above, wherein:

[0158] The first plate-shaped member 7 includes:

[0159] a cylindrical portion 78 protruding from the back surface 73 of the first plate portion 71 and inserted through the center hole of the annular member 62; and

[0160] At least one claw portion 22A protrudes from the cylindrical portion 78 toward the outer peripheral side of the inner peripheral edge of the annular member 62 and clamps the inner peripheral edge of the annular member 62 between the back surface 73 of the first plate portion 71.

[0161] The at least one stopper portion 22 includes the at least one claw portion 22A.

[0162] According to the structure of 3) above, by utilizing at least one claw portion 22A of the inner peripheral edge of the clamping annular member 62 as the stopper 22, it is possible to avoid re-setting the stopper (protrusion) on the first plate-like member 7, thereby reducing the portion that is changed from the existing shape of the first plate-like member 7 and suppressing the complication of the structure of the first plate-like member 7.

[0163] 4) A turbine 2 according to at least one embodiment of the present invention comprises:

[0164] The first housing 4 has a vortex flow path 41;

[0165] The turbine impeller 3 is arranged on the inner peripheral side of the vortex flow path 41;

[0166] The first plate-shaped member 7 includes a first annular plate portion 71;

[0167] The second plate-shaped member 8 includes an annular second plate portion 81, wherein the second plate portion 81 is disposed opposite to the first plate portion 71 and forms a gas flow path 43A from the swirl flow path 41 toward the turbine impeller 3 between the second plate portion 81 and the first plate portion 71;

[0168] at least one variable nozzle vane 61, disposed in the gas flow path 43A;

[0169] The second housing 5 has an opposing surface 51, and the opposing surface 51 is opposed to the back surface 73 of the first plate portion 71 on the side opposite to the flow path wall surface 72 facing the gas flow path 43A with the first space 43B interposed therebetween;

[0170] The biasing member 21 is disposed between the second housing 5 and the first plate member 7 and is configured to bias the first plate portion 71 toward the gas flow path 43A.

[0171] At least one positioning pin 9, one end 91 of which is inserted into the first hole 77 formed on the back surface 73 of the first plate portion 71, and the other end 92 of which is inserted into the second hole 53 formed on the opposing surface 51 of the second housing 5, and at least one of the one end 91 or the other end 92 of the at least one positioning pin 9 is inserted in a state with gaps 93A, 93B; and

[0172] The adhesive layer 94 is interposed between the gaps 93A and 93B, and the adhesive strength of the adhesive layer 94 is reduced due to input heat during operation of the turbine 2 .

[0173] According to the structure of 4) above, the bonding strength of the bonding layer 94 is reduced due to the input heat when the turbine 2 is running, thereby generating a gap between the positioning pin 9 and at least one of the first hole 77 or the second hole 53. Therefore, when the first plate-shaped member 7 approaches the second housing 5 side due to thermal deformation when the turbine 2 is running, it is possible to suppress the positioning pin 9 from being fixed to the first hole 77 or the second hole 53. By suppressing the positioning pin 9 from being fixed to the first hole 77 or the second hole 53 and hindering the reaction force of the force applying member 21, the holding structure of the variable nozzle unit 6 (first plate-shaped member 7) can be stably maintained by the reaction force of the force applying member 21. By stably maintaining the holding structure of the variable nozzle unit 6, the risk of wear and the like caused by vibration of the variable nozzle unit 6 can be reduced.

[0174] 5) In some embodiments, according to the turbine 2 described in 4) above, wherein:

[0175] The adhesive layer 94 is made of thermoplastic resin material.

[0176] According to the structure of 5) above, the adhesive layer 94 composed of thermoplastic resin material is softened (for example, liquefied) due to the input heat when the turbine 2 is running, thereby reducing the adhesive strength of the adhesive layer 94, and effectively generating gaps 93A, 93B between at least one of the first hole 77 or the second hole 53 and the positioning pin 9.

[0177] 6) A turbine 2 according to at least one embodiment of the present invention comprises:

[0178] The first housing 4 has a vortex flow path 41;

[0179] The turbine impeller 3 is arranged on the inner peripheral side of the vortex flow path 41;

[0180] The first plate-shaped member 7 includes a first annular plate portion 71;

[0181] The second plate-shaped member 8 includes an annular second plate portion 81, wherein the second plate portion 81 is disposed opposite to the first plate portion 71 and forms a gas flow path 43A from the swirl flow path 41 toward the turbine impeller 3 between the second plate portion 81 and the first plate portion 71;

[0182] at least one variable nozzle vane 61, disposed in the gas flow path 43A;

[0183] The second housing 5 has an opposing surface 51, and the opposing surface 51 is opposed to the back surface 73 of the first plate portion 71 on the side opposite to the flow path wall surface 72 facing the gas flow path 43A with the first space 43B interposed therebetween;

[0184] The biasing member 21 is disposed between the second housing 5 and the first plate member 7 and is configured to bias the first plate portion 71 toward the gas flow path 43A.

[0185] at least one positioning pin 9, one end 91 of which is inserted into the first hole 77 formed on the back surface 73 of the first plate portion 71, and the other end 92 of which is inserted into the second hole 53 formed on the opposing surface 51 of the second housing 5; and

[0186] The sliding layer 95 includes a solid lubricant covering at least one of the outer peripheral surface 911 of the one end 91 of the at least one positioning pin 9, the outer peripheral surface 921 of the other end 92 of the at least one positioning pin 9, the inner peripheral surface 771 of the first hole 77, or the inner peripheral surface 531 of the second hole 53.

[0187] According to the structure of 6) above, by reducing the friction resistance between at least one of the first hole 77 or the second hole 53 and the positioning pin 9 by the sliding layer 95, when the first plate-shaped member 7 approaches the second housing 5 side due to thermal deformation during the operation of the turbine 2, it is possible to suppress the positioning pin 9 from being fixed to the first hole 77 or the second hole 53. By suppressing the positioning pin 9 from being fixed to the first hole 77 or the second hole 53 and hindering the reaction force of the force applying member 21, the holding structure of the variable nozzle unit 6 (first plate-shaped member 7) can be stably maintained by the reaction force of the force applying member 21. By stably maintaining the holding structure of the variable nozzle unit 6, the risk of wear and the like caused by vibration of the variable nozzle unit 6 can be reduced.

[0188] 7) In some embodiments, according to the turbine 2 described in any one of 1) to 6) above, wherein:

[0189] At least one of the first hole 77 and the second hole 53 has a longitudinal direction along the radial direction of the turbine impeller 3 .

[0190] There is a difference in the amount of thermal expansion when the turbine 2 is running between the first plate portion 71 formed with the first hole 77 and the second housing 5 formed with the second hole 53, and a shear force caused by the difference in the amount of thermal expansion between the first plate portion 71 and the second housing 5 acts on the positioning pin 9. According to the structure of 7) above, by setting the hole shape of the first hole 77 or the second hole 53 to a hole shape having a length direction along the radial direction of the turbine impeller 3, compared with the case where the first hole 77 or the second hole 53 is a circular hole, since the positioning pin 9 does not restrict the thermal expansion between the first plate portion 71 and the second housing 5, it is possible to suppress the generation of an excessive load between the positioning pin 9 and the first hole 77, or between the positioning pin 9 and the second hole 53, thereby effectively suppressing the positioning pin 9 from being fixed to the first hole 77 or the second hole 53. Furthermore, according to the above-mentioned structure 7), the shear force acting on the positioning pin 9 due to the difference in thermal expansion between the first plate portion 71 and the second housing 5 can be reduced, thereby effectively preventing the positioning pin 9 from being fixed to the first hole 77 or the second hole 53 .

[0191] 8) In some embodiments, according to the turbine 2 described in any one of 1) to 7) above,

[0192] The at least one positioning pin 9 includes a plurality of positioning pins 9 arranged at intervals along the circumferential direction of the turbine impeller 3.

[0193] In a cross section perpendicular to the axis LA of the turbine impeller 3 , a point CP equidistant from the center positions LD of the plurality of positioning pins 9 is disposed closer to the tongue side S1 of the scroll flow path 41 than the axis LA of the turbine impeller 3 .

[0194] The temperature of the gas flowing through the vortex flow path 41 is higher on the tongue 48 side of the variable nozzle unit 6 that is closer to the vortex flow path 41 than the axis LA of the turbine impeller 3, that is, the tongue near side S1, than the tongue far side S2 that is the opposite side farther from the tongue 48 than the axis LA of the turbine impeller 3. Therefore, between the tongue near side S1 and the tongue far side S2, the difference in thermal expansion due to the input heat from the gas flowing through the vortex flow path 41 is large, and the eccentricity of the axis LB of the variable nozzle unit 6 relative to the axis LA of the turbine impeller 3 may increase.

[0195] According to the structure of 8), by eccentrically positioning the point (CP, the center point between the pins, the center of the figure) at the same distance from each center position LD of the plurality of positioning pins 9 closer to the tongue vicinity side S1 than the axis LA of the turbine impeller 3, the positioning pin 9 on the tongue vicinity side S1 can suppress the above-mentioned thermal expansion of the tongue vicinity side S1, compared with the case where the center point CP between the pins is the same as the axis LA of the turbine impeller 3 or is eccentric to the tongue far side S2, so that the difference in the above-mentioned thermal expansion amount between the tongue vicinity side S1 and the tongue far side S2 can be reduced, and the eccentricity of the axis LB of the variable nozzle unit 6 with respect to the axis LA of the turbine impeller 3 can be suppressed from increasing. In this case, the variable nozzle unit 6 can be suppressed from contacting the first housing 4, the second housing 5, or the turbine impeller 3 due to the eccentricity of the axis LB of the variable nozzle unit 6 with respect to the axis LA of the turbine impeller 3, and the excessive contact load on the positioning action caused by the contact can be suppressed. By suppressing excessive contact load on the positioning action, it is possible to effectively suppress the positioning pin 9 from being fixed to the first hole 77 or the second hole 53 .

[0196] 9) In some embodiments, according to the turbine 2 described in any one of 1) to 8) above,

[0197] The force applying component 21 (21B) at least includes:

[0198] The first force applying plate portion 211 extends along the radial direction of the turbine impeller 3 and abuts against the second housing 5; and

[0199] The second force applying plate portion 212 extends along the radial direction and abuts against the first plate-shaped member 7 .

[0200] According to the structure of 9) above, the force applying member 21 (21B) including the first force applying plate portion 211 and the second force applying plate portion 212 can increase the pushing force (reaction force) on the first plate portion 71, compared with the case where a single plate member such as the coil spring 21A abuts against the second housing 5 and the first plate-shaped member 7. By increasing the pushing force (reaction force) of the force applying member 21 (21B) on the first plate portion 71, the holding structure of the variable nozzle unit 6 (first plate-shaped member 7) can be maintained more stably.

[0201] 10) A turbocharger 1 according to at least one embodiment of the present invention comprises:

[0202] The turbine 2 described in any one of 1) to 9) above; and

[0203] The centrifugal compressor 12 is configured to be driven by the turbine 2 .

[0204] According to the structure of 10), the holding structure of the variable nozzle unit 6 (first plate-shaped member 7) can be stably maintained, and the risk of wear and the like due to vibration of the variable nozzle unit 6 can be reduced, thereby improving the reliability of the turbocharger 1.

[0205] Explanation of symbols

[0206] 1- turbocharger, 2- turbine, 3- turbine impeller, 4- first housing, 5- second housing, 6- variable nozzle unit, 7- first plate-shaped member, 8- second plate-shaped member, 9- positioning pin, 10- internal combustion engine system, 11- internal combustion engine, 12- centrifugal compressor, 13- impeller, 14- compressor housing, 15- rotating shaft, 16- bearing, 21- force member, 21A- disc spring, 22- stopper , 22A-claw, 31-hub, 32-turbine blade, 41-vortex flow path, 42-exhaust gas discharge flow path, 43-internal space, 43A-gas flow path, 43B-first space, 44-stuck portion, 45, 51-opposing surface, 46-shield portion, 46A, 84-shield surface, 47-step portion, 48-tongue, 52, 75A-end surface, 53-second hole, 54-protrusion, 61- Variable nozzle blade, 62-annular member, 63-connecting rod member, 64-support member, 65-driving mechanism portion, 71-first plate portion, 72-first flow path wall surface, 73-back surface, 74-through hole, 75-inner peripheral edge portion, 76-outer peripheral edge portion, 76A-stop surface, 77-first hole, 78, 85-cylindrical portion, 81-second plate portion, 82-second flow path wall surface, 83-second back surface, 93A, 93B-gap, 94-adhesive layer, 95-sliding layer, 95A-sliding layer on the 1st hole side, 95B-sliding layer on the 2nd hole side, BL1-1st reference line, BL2-2nd reference line, CP-center point, G1-1st gap, G2-2nd gap, G3-3rd gap, G4-4th gap, LA-axis line, LD-center position, P1-rear end, S1-near side of tongue, S2-far side of tongue.

Claims

1. A turbine comprising: A first housing having a vortex flow path; A turbine impeller is arranged on the inner peripheral side of the vortex flow path; A first plate-shaped member including a first annular plate portion; a second plate-shaped member including an annular second plate portion, the second plate portion being arranged opposite to the first plate portion and forming a gas flow path from the vortex flow path toward the turbine impeller between the second plate portion and the first plate portion; at least one variable nozzle vane disposed in the gas flow path; a second housing having an opposing surface, the opposing surface being opposed to the back surface of the first plate portion on the side opposite to the flow path wall surface facing the gas flow path with a first space therebetween; an annular member disposed in the first space and configured to rotate relative to the first plate-shaped member by a driving force from the outside; at least one connecting rod member, one end of which is connected to the annular member and the other end of which is connected to the variable nozzle vane, wherein the at least one connecting rod member is linked to the rotation of the annular member to change the vane angle of the variable nozzle vane connected to the other end; a biasing member disposed between the second housing and the first plate-shaped member and configured to bias the first plate portion toward the gas flow path; at least one positioning pin, one end of which is embedded in a first hole formed on the back surface of the first plate portion, and the other end of which is embedded in a second hole formed on the opposite surface of the second shell; and At least one stop portion is arranged on the opposing surface or the first plate portion, and a first gap is formed between the stop portion and the opposing surface, or between the stop portion and the first plate portion, and the first gap is constructed in a manner smaller than the second gap between the annular part and the opposing surface and the third gap between the at least one connecting rod part and the opposing surface.

2. The turbine according to claim 1, wherein: The at least one stopper is formed integrally with the first plate-shaped member.

3. The turbine according to claim 2, wherein: The first plate-shaped member comprises: a cylindrical portion protruding from the back surface of the first plate portion and inserted through the center hole of the annular member; and at least one claw portion protrudes from the cylindrical portion toward the outer peripheral side of the inner peripheral edge of the annular member and clamps the inner peripheral edge of the annular member between the back surface of the first plate portion, The at least one stopper portion includes the at least one claw portion.

4. A turbine comprising: A first housing having a vortex flow path; A turbine impeller is arranged on the inner peripheral side of the vortex flow path; A first plate-shaped member including a first annular plate portion; a second plate-shaped member including an annular second plate portion, the second plate portion being arranged opposite to the first plate portion and forming a gas flow path from the vortex flow path toward the turbine impeller between the second plate portion and the first plate portion; at least one variable nozzle vane disposed in the gas flow path; a second housing having an opposing surface, the opposing surface being opposed to the back surface of the first plate portion on the side opposite to the flow path wall surface facing the gas flow path with a first space therebetween; a biasing member disposed between the second housing and the first plate-shaped member and configured to bias the first plate portion toward the gas flow path; at least one positioning pin, one end of which is inserted into a first hole formed on the back surface of the first plate portion, and the other end of which is inserted into a second hole formed on the opposite surface of the second shell, and at least one of the one end or the other end of the at least one positioning pin is inserted with a gap; and The adhesive layer is interposed between the gaps, and the adhesive strength of the adhesive layer is reduced due to input heat during operation of the turbine.

5. The turbine according to claim 4, wherein: The adhesive layer is composed of thermoplastic resin material.

6. A turbine comprising: A first housing having a vortex flow path; A turbine impeller is arranged on the inner peripheral side of the vortex flow path; A first plate-shaped member including a first annular plate portion; a second plate-shaped member including an annular second plate portion, the second plate portion being arranged opposite to the first plate portion and forming a gas flow path from the vortex flow path toward the turbine impeller between the second plate portion and the first plate portion; at least one variable nozzle vane disposed in the gas flow path; a second housing having an opposing surface, the opposing surface being opposed to the back surface of the first plate portion on the side opposite to the flow path wall surface facing the gas flow path with a first space therebetween; a biasing member disposed between the second housing and the first plate-shaped member and configured to bias the first plate portion toward the gas flow path; at least one positioning pin, one end of which is inserted into a first hole formed on the back surface of the first plate portion, and the other end of which is inserted into a second hole formed on the opposite surface of the second shell; and The sliding layer includes a solid lubricant covering at least one of the outer peripheral surface of the one end of the at least one positioning pin, the outer peripheral surface of the other end of the at least one positioning pin, the inner peripheral surface of the first hole, or the inner peripheral surface of the second hole.

7. A turbine according to any one of claims 1 to 6, wherein: At least one of the first hole and the second hole has a longitudinal direction along the radial direction of the turbine impeller.

8. A turbine according to any one of claims 1 to 6, wherein: The at least one positioning pin includes a plurality of positioning pins arranged at intervals along the circumferential direction of the turbine impeller, In a cross section perpendicular to the axis of the turbine impeller, points at equal distances from the center positions of the plurality of positioning pins are arranged closer to the tongue portion of the scroll flow path than the axis of the turbine impeller.

9. A turbine according to any one of claims 1 to 6, wherein: The force applying component at least comprises: a first force applying plate portion extending in a radial direction of the turbine impeller and abutting against the second housing; and The second force applying plate portion extends along the radial direction and abuts against the first plate-shaped member.

10. A turbocharger comprising: A turbine as claimed in any one of claims 1 to 6; and The centrifugal compressor is configured to be driven by the turbine.

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