Turbine and supercharger

Abstract

A turbine is provided with: a turbine wheel; a turbine casing including a flow path for a gas flow received from an intake port; a variable capacity mechanism configured inside the turbine casing and receiving the gas to direct the turbine wheel, the variable capacity mechanism having a nozzle ring of a circular plate shape and a nozzle vane unit including: a nozzle vane configured on a main face side of the nozzle ring, a nozzle shaft extending from the nozzle vane and penetrating the nozzle ring, and a nozzle link plate configured on a back face side of the nozzle ring and linked to a front end of the nozzle shaft; and a butterfly spring applying a force in a direction of a nozzle axis line in a state of contacting the nozzle vane unit. The nozzle vane is brought into abutment with a portion facing the nozzle vane by the force.

Description

Technical Field

[0001] This disclosure relates to turbines and superchargers. Background Technology

[0002] Patent Document 1 discloses a turbocharger equipped with a variable capacity mechanism. The variable capacity mechanism controls the flow rate of the exhaust gas supplied from the vortex flow path to the turbine. The variable capacity mechanism adjusts the flow rate of the exhaust gas by changing the cross-sectional area of ​​the flow path supplying the exhaust gas through adjusting the angle of the nozzle blades.

[0003] Patent Document 1: Japanese Patent Application Publication No. 2006-207534

[0004] Turbines equipped with variable capacity mechanisms are expected to have improved reliability in order to achieve desired performance under various operating conditions. Applying irregular external forces to the variable capacity mechanism can reduce its reliability. For example, the variable capacity mechanism is positioned along the path that guides exhaust gas from the engine to the turbine impeller. The state of the exhaust gas changes depending on the engine's operating state. The components constituting the variable capacity mechanism are affected by these changes in the state of the exhaust gas. Furthermore, the components constituting the variable capacity mechanism are affected by vibrations or shocks experienced by the turbine. Summary of the Invention

[0005] This disclosure describes a turbine that can improve reliability and a turbocharger equipped with the turbine.

[0006] One aspect of the turbine disclosed herein includes: a turbine impeller; a housing including a flow path for gas flow received from an inlet; a variable capacity mechanism disposed inside the housing and receiving gas from the flow path and guiding it toward the turbine impeller, the variable capacity mechanism having a circular nozzle ring and a nozzle vane unit, the nozzle ring having a main face and a back face facing the turbine impeller, the nozzle vane unit including: a nozzle blade disposed on the main face side of the nozzle ring, a nozzle shaft extending from the nozzle blade and passing through the nozzle ring, and a nozzle connecting plate disposed on the back face side of the nozzle ring and connected to the front end of the nozzle shaft; and a force-applying member that applies a force axially along the nozzle shaft when in contact with the nozzle vane unit. The nozzle blade abuts against the portion facing the nozzle blade by means of the force.

[0007] The turbine and supercharger disclosed herein can improve reliability. Attached Figure Description

[0008] Figure 1 This is a cross-sectional view of a turbocharger equipped with a turbine according to the first embodiment.

[0009] Figure 2 It is Figure 1The variable capacity mechanism and force-applying components shown are presented in an exploded perspective view.

[0010] Figure 3 This is an enlarged cross-sectional view of the main parts of the variable capacity mechanism and force-applying components of the turbine in the first embodiment.

[0011] Figure 4 This is a top view of the variable capacity mechanism and force-applying components of the turbine according to the first embodiment.

[0012] Figure 5 This is an enlarged cross-sectional view of the main parts of the variable capacity mechanism and force-applying components of the turbine in the second embodiment.

[0013] Figure 6 This is a top view of the variable capacity mechanism and force-applying components of the turbine according to the second embodiment.

[0014] Figure 7 This is an enlarged cross-sectional view of the main parts of the variable capacity mechanism and force-applying components of the turbine in the third embodiment.

[0015] Figure 8 This is a top view of the variable capacity mechanism and force-applying components of the turbine according to the third embodiment.

[0016] Figure 9 This is an enlarged cross-sectional view of the main parts of the variable capacity mechanism and force-applying components of the turbine in the fourth embodiment.

[0017] Figure 10 This is a top view of the variable capacity mechanism and force-applying components of the turbine according to the fourth embodiment.

[0018] Figure 11 This is an enlarged cross-sectional view of the main parts of the variable capacity mechanism and force-applying components of the turbine in the first modified example.

[0019] Figure 12 This is an enlarged cross-sectional view of the main parts of the variable capacity mechanism and force-applying components of the turbine in the second variation.

[0020] Figure 13 This is a cross-sectional view of a turbocharger with a third variant of the turbine.

[0021] Figure 14 This is an enlarged cross-sectional view of the main parts of the variable capacity mechanism and force-applying components of the turbine in the fourth variation. Detailed Implementation

[0022] One aspect of the turbine disclosed herein includes: a turbine impeller; a housing including a flow path for gas flow received from an inlet; a variable capacity mechanism disposed inside the housing and receiving gas from the flow path and guiding it toward the turbine impeller, the variable capacity mechanism having a circular nozzle ring and a nozzle vane unit, the nozzle ring having a main face and a back face facing the turbine impeller, the nozzle vane unit including: a nozzle blade disposed on the main face side of the nozzle ring, a nozzle shaft extending from the nozzle blade and passing through the nozzle ring, and a nozzle connecting plate disposed on the back face side of the nozzle ring and connected to the front end of the nozzle shaft; and a force-applying member that applies a force axially along the nozzle shaft when in contact with the nozzle vane unit. The nozzle blade abuts against the portion facing the nozzle blade by means of the force.

[0023] The turbine includes a force-applying component that applies an axial force to the nozzle vane unit towards the nozzle axis. The nozzle vane unit, to which the force is applied, abuts against the portion facing the nozzle blades. The relative movement of the nozzle vane unit with respect to the nozzle ring can be limited to rotation about the nozzle axis. Undesirable movements of the nozzle vane unit, such as oscillations or rotations, can be suppressed. Therefore, even if the nozzle blades are subjected to irregular external forces, the nozzle vane unit will not produce irregular relative movement with respect to the nozzle ring. By maintaining the good condition of the component assembly constituting the variable capacity mechanism, the variable capacity mechanism can be maintained in a state where it can perform as desired. Therefore, the reliability of the turbine equipped with the variable capacity mechanism can be improved.

[0024] The variable capacity mechanism may also include a circular plate component that cooperates with the nozzle ring to clamp the nozzle blades. The portion facing the nozzle blades can also be a circular plate component. The distance from the circular plate component to the nozzle ring can be precisely set. The gap formed between the nozzle blades and the circular plate component can also be set with high precision. The circular plate component can also be configured to suppress irregular movement of the nozzle blades without hindering their rotational movement around the nozzle axis.

[0025] The housing may also include a flow surface that faces the end face opposite to the end face of the nozzle blade on which the nozzle shaft is mounted. The portion facing the nozzle blade can also be the flow surface of the housing. With this structure, no additional components are needed for contact between the nozzle blade and the housing. Therefore, the turbine can be simplified.

[0026] The axial distance from the nozzle ring to the nozzle connecting plate can also be greater than the axial distance from the nozzle blade to the part facing the nozzle blade. This ensures reliable contact between the nozzle blade and the part facing the nozzle blade.

[0027] The nozzle connecting plate may also include a first region that overlaps with the nozzle blades when viewed axially, and a second region that does not overlap with the nozzle blades. The part of the force-applying component that contacts the nozzle connecting plate may also be located in the first region. With this structure, the force of the force-applying component can be applied to a region close to the nozzle shaft. The distance from the connection between the nozzle connecting plate and the nozzle shaft to the position on the nozzle connecting plate where the force is applied is shortened. The moment required to tilt the nozzle blade unit relative to the rotation axis of the nozzle shaft is reduced. The friction between the nozzle shaft and the inner circumferential surface of the through hole of the nozzle ring is reduced, thus maintaining the movement of the nozzle blades used to control the flow path cross-sectional area is better.

[0028] The nozzle connecting plate may also include a first region that overlaps with the nozzle blades when viewed axially, and a second region that does not overlap with the nozzle blades. The part of the force-applying component that contacts the nozzle connecting plate may also be located in the second region. With this structure, the force can be applied to a region away from the nozzle axis. The distance from the point where the nozzle axis connects to the nozzle connecting plate to the point on the nozzle connecting plate where the force is applied increases. The moment required to tilt the nozzle blade unit relative to the rotation axis of the nozzle axis increases. The frictional force generated by the contact between the nozzle axis and the inner circumferential surface of the through hole of the nozzle ring increases. Therefore, unwanted oscillations and other movements can be further suppressed.

[0029] The turbine of other embodiments disclosed herein comprises: a turbine impeller; a housing including a flow path for gas flow received from an inlet; a variable capacity mechanism disposed within the housing and receiving gas from the flow path and guiding it toward the turbine impeller, the variable capacity mechanism having a circular nozzle ring and a nozzle vane unit, the nozzle ring having a main face and a back face facing the turbine impeller, the nozzle vane unit including a nozzle blade disposed on the main face side of the nozzle ring, a nozzle shaft extending from the nozzle blade and penetrating the nozzle ring, and a nozzle connecting plate disposed on the back face side of the nozzle ring and connected to the front end of the nozzle shaft; and a force-applying member that applies a force radially along the nozzle shaft when in contact with the nozzle vane unit. The nozzle shaft abuts against the inner circumferential surface of the through hole of the nozzle ring.

[0030] The nozzle shaft abuts against the inner circumferential surface of the through hole in the nozzle ring. As a result, the relative movement of the nozzle vane unit with respect to the nozzle ring can be limited to rotation about the nozzle shaft. That is, unwanted movements of the nozzle vane unit, such as wobbling or rotation, can be suppressed. Therefore, even if the nozzle blades are subjected to irregular forces, the nozzle vane unit will not produce irregular movement. The component assembly constituting the variable capacity mechanism can be kept in good condition, thus maintaining the variable capacity mechanism in a state where it can perform as desired. Therefore, the reliability of the turbine equipped with the variable capacity mechanism can be improved.

[0031] Another aspect of the invention is a supercharger incorporating the aforementioned turbine. The supercharger, incorporating the aforementioned turbine, can improve reliability.

[0032] Hereinafter, a turbocharger equipped with the turbine of this disclosure will be described in detail with reference to the accompanying drawings. In the description of the drawings, the same reference numerals are used to refer to the same elements and overlapping descriptions are omitted.

[0033] <First Implementation>

[0034] like Figure 1 As shown, the turbocharger 1 is a variable capacity type. The turbocharger 1 is, for example, suitable for an internal combustion engine in a ship or vehicle. The turbocharger 1 has a turbine 10 and a compressor 20. The turbine 10 has a turbine housing 11, a turbine impeller 12, a variable capacity mechanism 30, and a bearing housing 3. The compressor 20 has a compressor housing 21 and a compressor impeller 22.

[0035] Turbine impeller 12 is disposed at the first end of shaft 2. Compressor impeller 22 is disposed at the second end of shaft 2. Bearing housing 3 is disposed between turbine housing 11 and compressor housing 21. Bearing 4 is disposed in bearing housing 3. Shaft 2 is rotatably supported in bearing housing 3 via bearing 4.

[0036] The turbine housing 11 has an inlet 11R, a vortex flow path 13, and an outlet 14. The inlet 11R receives exhaust gas from the internal combustion engine within the turbine housing 11. The vortex flow path 13 extends circumferentially around the turbine impeller 12, centered on the axis of rotation AX. The vortex flow path 13 guides the gas received from the inlet 11R toward the turbine impeller 12. The exhaust gas, guided by the variable capacity mechanism 30, causes the turbine impeller 12 to rotate. After the turbine impeller 12 is rotated, the exhaust gas flows out of the turbine housing 11 through the outlet 14.

[0037] More specifically, the turbine 10 has a connecting flow path S. The connecting flow path S guides exhaust gas from the vortex flow path 13 to the turbine impeller 12. The connecting flow path S includes multiple nozzles. The multiple nozzles are formed by multiple nozzle blades 34. More specifically, a nozzle is a space surrounded by a pair of nozzle blades 34, a CC plate 31 (described later), and a nozzle ring 32. The multiple nozzle blades 34 are arranged at equal intervals on a reference circle centered on the rotation axis AX. The nozzle blades 34 rotate about a nozzle axis NX that is parallel to the rotation axis AX. The rotation of the multiple nozzle blades 34 allows for adjustment of the nozzle cross-sectional area. As a mechanism for adjusting the nozzle cross-sectional area, the turbine 10 has a variable capacity mechanism 30.

[0038] The compressor housing 21 has a vortex flow path 23, an intake 24, and an outlet 21R. The compressor impeller 22 rotates via the shaft 2 in conjunction with the rotation of the turbine impeller 12. The rotating compressor impeller 22 draws in external air through the intake 24. The drawn-in air is compressed by the compressor impeller 22 and the vortex flow path 23. The compressed air is discharged from the outlet 21R. The compressed air is supplied to the internal combustion engine.

[0039] The variable capacity mechanism 30 includes a clearance control plate and a nozzle ring 32. Hereinafter, the clearance control plate will be referred to as "CC plate 31". CC plate 31 has a circular plate shape. The nozzle ring 32 also has a circular plate shape. The central axis of CC plate 31 overlaps with the central axis of nozzle ring 32. The central axis of CC plate 31 overlaps with the rotation axis AX. The central axis of nozzle ring 32 overlaps with the rotation axis AX. CC plate 31 is located on the turbine housing 11 side in the direction of the rotation axis AX. The nozzle ring 32 is located on the bearing housing 3 side in the direction of the rotation axis AX. The spacing between CC plate 31 and nozzle ring 32 is the connecting flow path S. Multiple nozzle blades 34 are arranged between CC plate 31 and nozzle ring 32.

[0040] like Figure 2 As shown, the variable capacity mechanism 30 includes: a CC plate 31, a nozzle ring 32, a clearance control pin, and a drive ring 35. Hereinafter, the clearance control pin will be referred to as "CC pin 33". Furthermore, the variable capacity mechanism 30 includes a nozzle wing unit 300.

[0041] CC plate 31 has a main surface 31a, a back surface 31b, and a hole 31h. The main surface 31a faces the inner surface of the turbine housing 11 (see reference). Figure 1 The back side 31b of the plate faces the nozzle ring 32. The plate hole 31h is a through hole from the main surface 31a of the plate to the back side 31b of the plate. A plate pin hole 31p is provided in the CC plate 31. The plate pin hole 31p includes an opening formed at least in the back side 31b of the plate. The CC pin 33 is inserted into the plate pin hole 31p through the opening formed in the back side 31b of the plate.

[0042] The nozzle ring 32 has a nozzle ring body 32d and a nozzle ring flange 32f. The nozzle ring body 32d is a cylindrical portion. The nozzle ring body 32d has a plurality of nozzle shaft holes 32s. The nozzle shaft holes 32s are through holes. The circumferential spacing of the plurality of nozzle shaft holes 32s is equal to that of each other. The nozzle ring flange 32f protrudes radially from the outer peripheral side of the nozzle ring body 32d. The nozzle ring flange 32f has a flange pin hole 32p. The central axis of the flange pin hole 32p overlaps with the central axis of the plate pin hole 31p.

[0043] The nozzle ring 32 includes a main nozzle ring face 32a, a back nozzle ring face 32b, and an annular hole 32h. The main nozzle ring face 32a faces the CC plate 31. The main nozzle ring face 32a faces the turbine impeller 12. The back nozzle ring face 32b includes a main body back face 32b1 and a flange back face 32b2. The main body back face 32b1 is the end face of the main nozzle ring body 32d. The main body back face 32b1 faces the bearing housing 3. An opening for the nozzle shaft hole 32s is formed on the main body back face 32b1. A portion of the nozzle connecting plate 36 is disposed on the main body back face 32b1. Therefore, a portion of the main body back face 32b1 faces the nozzle connecting plate 36. The flange back face 32b2 is the end face of the nozzle ring flange 32f. The flange back face 32b2 also faces the bearing housing 3. A drive ring 35, described later, is disposed on the flange back face 32b2. Therefore, the flange back face 32b2 faces the drive ring 35.

[0044] CC pin 33 connects CC plate 31 to nozzle ring 32. CC pin 33 is inserted into plate pin hole 31p. CC pin 33 is also inserted into flange pin hole 32p. CC pin 33 defines the gap between CC plate 31 and nozzle ring 32.

[0045] A drive ring 35 is disposed on the nozzle ring flange 32f. More specifically, the drive ring 35 is disposed on the back surface 32b2 of the flange. The drive ring 35 is an annular component centered on the rotation axis AX. The drive ring 35 has a drive ring hole 35h. The drive ring 35 circumferentially surrounds the nozzle ring body 32d disposed in the drive ring hole 35h. The drive ring 35 is coaxial with respect to the nozzle ring 32. The drive ring 35 is capable of rotating relative to the nozzle ring 32 about the rotation axis AX.

[0046] The drive ring 35 has a drive ring main surface 35a and a drive ring back surface 35b. The drive ring main surface 35a faces the nozzle ring 32. More specifically, the drive ring main surface 35a faces the flange back surface 32b2 of the nozzle ring 32. A plurality of nozzle connecting plates 36 are disposed on the drive ring back surface 35b. A portion of the drive ring back surface 35b faces the nozzle connecting plates 36. In addition, a drive connecting plate 38 is also disposed on the drive ring back surface 35b.

[0047] The drive ring 35 includes a connector 35J. A nozzle connecting plate 36 is embedded in the connector 35J. Multiple connectors 35J are arranged at equal intervals in the circumferential direction. The connector 35J includes a pair of upright portions 35J1. The upright portions 35J1 protrude from the back side 35b of the drive ring. The upright portions 35J1 protrude toward the bearing housing 3. The front end 36e of the connecting plate 36 of the nozzle connecting plate is embedded between the pair of upright portions 35J1.

[0048] The nozzle wing unit 300 includes a nozzle blade 34, a nozzle shaft 37, and a nozzle connecting plate 36. The nozzle wing unit 300 is disposed in the nozzle shaft hole 32s of each nozzle ring 32. The nozzle wing unit 300 is disposed in each joint 35J of the drive ring 35. The nozzle wing units 300 are evenly spaced in the circumferential direction.

[0049] like Figure 3 As shown, the nozzle blade 34 is disposed between the CC plate 31 and the nozzle ring 32. The nozzle blade 34 includes a blade main surface 34a and a blade back surface 34b. The blade main surface 34a faces the back surface 31b of the CC plate 31. The blade back surface 34b faces the nozzle ring main surface 32a of the nozzle ring 32. Furthermore, the length from the blade main surface 34a to the blade back surface 34b along the nozzle axis NX is defined as the nozzle blade width. The distance from the back surface 31b of the CC plate 31 to the nozzle ring main surface 32a is defined as the connecting flow path width. The connecting flow path width is slightly larger than the nozzle blade width. Therefore, a small first gap C1 exists between the blade main surface 34a and the plate back surface 31b. Additionally, a small second gap C2 also exists between the blade back surface 34b and the nozzle ring main surface 32a. The nozzle blade 34 is capable of moving relative to the CC plate 31 by the length of the first gap C1 along the rotation axis AX. The nozzle blade 34 is capable of moving relative to the nozzle ring 32 by the length of the second gap C2 along the rotation axis AX.

[0050] A nozzle shaft 37 is mounted on the back surface 34b of the blade. More specifically, the nozzle shaft 37 includes a nozzle shaft base end 37f and a nozzle shaft front end 37e. The nozzle shaft base end 37f is fixed to the back surface 34b of the blade. The nozzle shaft 37 is inserted through the nozzle shaft hole 32s of the nozzle ring 32. The nozzle shaft front end 37e is positioned to protrude from the back surface 32b1 of the main body of the nozzle ring 32. The nozzle shaft 37 includes an outer peripheral surface 37s. The outer peripheral surface 37s of the nozzle shaft faces the inner peripheral surface 32s1 of the nozzle shaft hole 32s. A small third gap C3 exists between the inner peripheral surface 32s1 and the outer peripheral surface 37s of the nozzle shaft, allowing for a degree of rotation of the nozzle shaft 37. A nozzle connecting plate 36 is fixed to the nozzle shaft front end 37e.

[0051] The nozzle connecting plate 36 is a rod-shaped component. The nozzle connecting plate 36 includes a main connecting plate surface 36a and a back connecting plate surface 36b. The nozzle connecting plate 36 is disposed on the back surface 32b of the nozzle ring. More specifically, the nozzle connecting plate 36 includes a portion disposed on the back surface 32b1 of the main body and a portion disposed on the back surface 32b2 of the flange. The main connecting plate surface 36a faces the back surface 32b2 of the flange of the nozzle ring 32, faces the back surface 35b of the drive ring, and faces the back surface 32b1 of the main body of the nozzle ring 32. The back connecting plate surface 36b faces the main bearing housing surface 3a of the bearing housing 3. The back connecting plate surface 36b also faces the disc spring 39, which will be described later.

[0052] The nozzle connecting plate 36 includes a connecting plate base end 36f as a first end and a connecting plate front end 36e as a second end. The connecting plate base end 36f is disposed on the back surface 32b1 of the main body. A connecting plate hole 36s is provided in the connecting plate base end 36f. The nozzle shaft front end 37e of the nozzle shaft 37 is inserted into the connecting plate hole 36s. The nozzle shaft front end 37e is fixed relative to the nozzle connecting plate 36 by a slit machining process. The connecting plate front end 36e is disposed on the back surface 32b2 of the flange. The connecting plate front end 36e is embedded in the connector 35J (see reference). Figure 2 More specifically, the front end 36e of the connecting plate is positioned between a pair of upright portions 35J1. The front end 36e of the connecting plate is not fixed relative to the pair of upright portions 35J1. The nozzle connecting plate 36 is not fixed relative to the drive ring 35.

[0053] As described above, the nozzle shaft 37 is fixed relative to the nozzle blade 34. The nozzle connecting plate 36 is fixed relative to the nozzle shaft 37. The nozzle blade 34, the nozzle shaft 37, and the nozzle connecting plate 36 can be considered as a single component, the nozzle wing unit 300.

[0054] The nozzle connecting plate 36 oscillates around the nozzle axis NX according to the rotational position of the drive ring 35 relative to the nozzle ring 32. The nozzle shaft 37 rotates around the nozzle axis NX according to the oscillation of the nozzle connecting plate 36. The nozzle blade 34, fixed to the nozzle shaft 37, oscillates around the nozzle axis NX according to the oscillation of the nozzle connecting plate 36.

[0055] On the other hand, the nozzle vane unit 300 can also perform actions different from those described above. A small gap exists between the nozzle vane unit 300 and other components adjacent to it. The nozzle vane unit 300 is allowed to move relative to this gap. The nozzle vane unit 300 is subjected not only to forces from the drive ring 35, but also to undesirable external forces. For example, the nozzle vane unit 300 may be subjected to external forces caused by pulsations of exhaust gas via the nozzle blades 34. Furthermore, the variable capacity mechanism 30, including the nozzle vane unit 300, may also receive random vibrations or impacts from other devices such as internal combustion engines. If these random vibrations or impacts act on adjacent components, they become undesirable external forces. The nozzle vane unit 300 may experience undesirable actions due to the gaps between components and the effects of undesirable external forces.

[0056] An example of an undesirable action is the oscillating rotation of the nozzle wing unit 300. Undesirable actions are not limited to oscillating rotation. Oscillating rotation of the nozzle wing unit 300 means that the nozzle shaft 37 moves in a wobbling manner. Due to oscillating rotation, for example, the front end 36e of the nozzle connecting plate 36 may experience irregular and intermittent collisions relative to the joint 35J of the drive ring 35.

[0057] The oscillating rotation is caused by the presence of three gaps. The first is the first gap C1 between the main surface 34a of the nozzle blade 34 and the back surface 31b of the CC plate 31. The second is the second gap C2 between the back surface 34b of the nozzle blade 34 and the main surface 32a of the nozzle ring. The third is the third gap C3 between the outer circumferential surface 37s of the nozzle shaft and the inner circumferential surface 32s1 of the nozzle shaft hole 32s.

[0058] The description explains that undesirable motion occurs due to the presence of gaps and the action of external forces. Oscillating rotation occurs when all of the aforementioned first gap C1, second gap C2, and third gap C3 are present. Therefore, the turbine 10 of the first embodiment includes a mechanism for eliminating at least one of the first gap C1, second gap C2, and third gap C3. The turbine 10 of the first embodiment suppresses the generation of undesirable oscillating rotation by eliminating the first gap C1. As a component for eliminating the first gap C1, the turbine 10 includes a disc spring 39 as a force-applying component.

[0059] "Clear elimination" does not require the entire surface of the blade main face 34a to contact the back surface of the plate 31b. Oscillating rotation occurs when the entire surface of the blade main face 34a is separated from the back surface of the plate 31b. If a portion of the blade main face 34a contacts the back surface of the plate 31b, the movement of the nozzle blade 34 can be restricted, thus preventing oscillation rotation. The state where a portion of the blade main face 34a contacts the back surface of the plate 31b is also the state of clear elimination.

[0060] "Gap" means a state in which facing components are completely out of contact with each other. For example, "the existence of a first gap C1" means that the blade's main surface 34a and the plate's back surface 31b are completely out of contact. Therefore, as... Figure 3 As shown, the state in which a portion of the blade's main surface 34a contacts the back surface 31b of the plate cannot strictly be described as a state where the first gap C1 exists. Figure 3 For ease of explanation, “first gap C1” is shown.

[0061] like Figure 3 as well as Figure 4As shown, a disc spring 39 is disposed between the bearing housing 3 and the variable capacity mechanism 30. The disc spring 39 is formed in a ring shape centered on the rotation axis AX. The shape of the disc spring 39 slopes from the outer diameter to the inner diameter. The outer diameter of the disc spring 39 is smaller than the outer diameter of the drive ring 35. One disc spring 39 is disposed relative to the entire nozzle connecting plate 36.

[0062] The disc spring 39 includes a main spring surface 39a and a back spring surface 39b. The main spring surface 39a faces the variable capacity mechanism 30. More specifically, the main spring surface 39a faces the drive ring 35, the nozzle connecting plate 36, and the nozzle ring 32. The disc spring 39 is circular. Therefore, the disc spring 39 faces all the nozzle wing units 300 of the variable capacity mechanism 30. One disc spring 39 presses against multiple nozzle wing units 300. In addition, the main spring surface 39a faces the back spring surface 35b of the drive ring 35. The main spring surface 39a also faces the back spring surface 36b of the connecting plate of the nozzle connecting plate 36. The main spring surface 39a also faces the back spring surface 32b1 of the main body of the nozzle ring 32. The main spring surface 39a includes an outer peripheral portion 39a1 and an inner peripheral portion 39a2. The outer peripheral portion 39a1 contacts the nozzle wing unit 300. More specifically, the outer periphery 39a1 of the spring main surface contacts the back surface 36b of the nozzle connecting plate 36. The inner periphery 39a2 of the spring main surface does not contact the nozzle wing unit 300. The inner periphery 39a2 of the spring main surface is separated from the back surface 36b of the connecting plate. For example, the inner periphery 39a2 of the spring main surface is separated from the front end 37e of the nozzle shaft and faces the front end 37e of the nozzle shaft.

[0063] The back surface of the spring 39b faces the main surface of the bearing housing 3a. The back surface of the spring 39b includes an outer peripheral portion 39b1 and an inner peripheral portion 39b2. The outer peripheral portion 39b1 is separated from the main surface of the bearing housing 3a. The inner peripheral portion 39b2 is in contact with the main surface of the bearing housing 3a.

[0064] The disc spring 39 is held between the nozzle connecting plate 36 and the bearing housing 3. The distance from the nozzle connecting plate 36 to the bearing housing 3 is shorter than the natural length of the disc spring 39. Therefore, the disc spring 39 is compressed in the direction of the rotation axis AX. Through the compression of the disc spring 39, the disc spring 39 generates an elastic force as an action force. The elastic force acts on the nozzle connecting plate 36 with the point of application PA where the outer periphery 39a1 of the spring's main surface contacts the back surface 36b of the connecting plate.

[0065] If a force is applied to the nozzle wing unit 300, the nozzle shaft 37 moves axially. Along with the movement of the nozzle shaft 37, the nozzle blade 34 moves axially. The nozzle blade 34 abuts against the portion facing the nozzle blade 34, i.e., the CC plate 31. As a result, the first gap C1 is eliminated.

[0066] The magnitude of force F determines the degree to which the action required by the nozzle blade unit 300 is not hindered. Ideally, the magnitude of force F determines the degree to which the blade main surface 34a of the nozzle blade 34 contacts the back surface 31b of the CC plate 31. This is because if the blade main surface 34a is pressed by the back surface 31b, friction is generated between the blade main surface 34a and the back surface 31b. If the friction generated by the contact between the blade main surface 34a and the back surface 31b does not hinder the oscillation of the nozzle blade 34 corresponding to the action of the drive ring 35, this is also permissible. The elastic force can also be set to the magnitude of the pressure exerted from the blade main surface 34a on the back surface 31b. Depending on the state of the pressure exerted from the blade main surface 34a on the back surface 31b, it is possible to counteract irregular external forces acting on the nozzle blade 34 due to the pulsation of the exhaust gas. The elastic force can also be set based on the magnitude of an assumed external force.

[0067] To eliminate the aforementioned first gap C1, in addition to the elastic force provided by the disc spring 39, the position of the components constituting the variable capacity mechanism 30 is also relevant. To eliminate the first gap C1 by applying a force F to the nozzle connecting plate 36, the blade main surface 34a needs to be able to move to contact the plate back surface 31b. This can be achieved by satisfying a relationship where the fourth gap C4 between the connecting plate main surface 36a and the main body back surface 32b1 is greater than the first gap C1 between the blade main surface 34a and the plate back surface 31b. For example, even when the blade main surface 34a is in contact with the plate back surface 31b, a fourth gap C4 still exists between the connecting plate main surface 36a and the main body back surface 32b1.

[0068] The location of the point of action PA will be described in further detail.

[0069] The back surface 36b of the nozzle connecting plate 36 has a first region S1 and a second region S2. The first region S1 overlaps with the projected region SB of the nozzle blade 34 as viewed axially along the nozzle axis NX. The first region S1 includes the base end 36f of the connecting plate. The first region S1 is the region near the front end 37e of the nozzle shaft. The second region S2 is the remaining portion of the back surface 36b of the connecting plate excluding the first region S1. The second region S2 does not overlap with the projected region SB of the nozzle blade 34 as viewed axially along the nozzle axis NX. The second region S2 is the region of the nozzle connecting plate 36 away from the base end 36f of the connecting plate. The second region S2 includes the region extending up to the front end 36e of the connecting plate of the nozzle connecting plate 36. The second region S2 is the region away from the nozzle shaft 37. The area of ​​the second region S2 may also be larger than the area of ​​the first region S1.

[0070] In the first embodiment, the point of action PA of the disc spring 39 is located in the second region S2 described above. The point of action PA is located in the region of the nozzle connecting plate 36 away from the base end 36f of the connecting plate.

[0071] According to the turbine 10 of the first embodiment described above, the relative movement of the nozzle vane unit 300 with respect to the nozzle ring 32 is limited to rotation around the nozzle axis NX. Therefore, unwanted movements of the nozzle vane unit 300, such as oscillations or rotations, can be suppressed. Thus, even if the nozzle blade 34 is subjected to irregular external forces, the nozzle vane unit 300 does not produce irregular relative movement with respect to the nozzle ring 32. Since the state of the component assembly constituting the variable capacity mechanism 30 can be maintained in good condition, the variable capacity mechanism 30 can maintain the desired performance. Therefore, the reliability of the turbine 10 equipped with the variable capacity mechanism 30 can be improved.

[0072] The device includes a CC plate 31, which allows for precise setting of the distance from the CC plate 31 to the nozzle ring 32. It also allows for high-precision setting of the gap between the nozzle blade 34 and the circular plate component (CC plate 31 or nozzle ring 32). The device can easily set forces that do not impede the rotational movement of the nozzle blade 34 around the nozzle shaft 37, while suppressing forces generated by irregular movement of the nozzle blade 34.

[0073] Furthermore, the distance from the nozzle ring 32 to the nozzle connecting plate 36 along the rotation axis AX (fourth gap C4) is greater than the distance from the nozzle blade 34 to the CC plate 31 facing the nozzle blade 34 along the rotation axis AX (first gap C1). With the aid of force F, the nozzle blade 34 abuts against the CC plate 31 before the nozzle connecting plate 36 abuts against the nozzle ring 32. This ensures reliable contact between the nozzle blade 34 and the portion facing the nozzle blade 34, i.e., the CC plate 31.

[0074] A force F is applied to the nozzle shaft 37 at a position offset from the nozzle axis NX. With this structure, the force F of the disc spring 39 can be applied to a region (second region S2) away from the nozzle shaft 37. The distance from the position on the nozzle connecting plate 36, where the force F is applied, to the portion of the nozzle connecting plate 36 connected to the nozzle shaft 37, increases. A torque is generated that tilts the nozzle shaft 37 of the nozzle vane unit 300. Due to the frictional force generated from the contact with the inner circumferential surface 32s1 of the nozzle shaft hole 32s, unwanted movements such as oscillations and rotations can be further suppressed.

[0075] Eliminating the first gap C1 between the nozzle blade 34 and the CC plate 31 not only suppresses oscillation and rotation but also has a further effect.

[0076] like Figure 1As shown, the exhaust gas discharged from the variable capacity mechanism 30 is received by the blade portion 12s of the turbine impeller 12. Ideally, the state of the exhaust gas delivered from the variable capacity mechanism 30 to the turbine impeller 12 should always be the same regardless of the location. However, due to the structure of the connecting flow path S in the variable capacity mechanism 30, there are cases where the state of the exhaust gas delivered to the turbine impeller 12 varies depending on the location. For example, the first gap C1 between the nozzle blade 34 and the CC plate 31 and the second gap C2 between the nozzle blade 34 and the nozzle ring 32 affect the state of the exhaust gas. To make the exhaust gas approach a good state, it is best if the first gap C1 and the second gap C2 are not present.

[0077] In the first embodiment, the nozzle blade 34 is brought into contact with the CC plate 31, thereby eliminating the first gap C1. The second gap C2 between the nozzle blade 34 and the nozzle ring 32 still exists.

[0078] Focusing on the turbine impeller 12, the flow path of the exhaust gas is the space surrounded by the turbine impeller 12 and the turbine housing 11. A small gap C5 is formed at the portion where the turbine impeller 12 and the turbine housing 11 face each other. The gap C5 easily affects the flow state. Therefore, it is desirable to provide exhaust gas with a near-ideal state to the portion where the gap C5 is formed. The portion where the turbine impeller 12 and the turbine housing 11 face each other is located downstream of the portion where the nozzle blade 34 and the CC plate 31 face each other. At the portion where the nozzle blade 34 and the CC plate 31 face each other, the first gap C1 is eliminated. Therefore, there is a tendency for disturbances in the exhaust gas to be suppressed. The exhaust gas with suppressed disturbances is supplied to the portion where the nozzle blade 34 and the CC plate 31 face each other. As a result, exhaust gas with a near-ideal state is provided to the turbine impeller 12. Therefore, the energy of the exhaust gas can be efficiently recovered through the turbine impeller 12, thus contributing to the improvement of the performance of the turbocharger 1.

[0079] [Second Implementation]

[0080] Figure 5 This is an enlarged cross-sectional view showing the main part of the turbine 10A in the second embodiment. Figure 6 This is a top view showing the force-applying components of the turbine 10A in the second embodiment. The turbine 10A in the second embodiment differs from the turbine 10 in the first embodiment in that it has a heat shield 41 instead of a disc spring 39.

[0081] The heat shield 41 shields the turbine housing 11 from heat. Additionally, the heat shield 41 also functions as a disc spring 39. The heat shield 41 presses against the nozzle vane unit 300. The heat shield 41 includes a circular plate portion 42 and a spring portion 43.

[0082] The circular plate portion 42 is shaped like a circular plate centered on the rotation axis AX. The circular plate portion 42 is disposed on the bearing housing 3 side relative to the nozzle ring 32. The circular plate portion 42 is separated from the nozzle connecting plate 36 along the rotation axis AX. The circular plate portion 42 includes a main circular plate surface 42a and a back circular plate surface 42b. The main circular plate surface 42a faces the nozzle connecting plate 36. The back circular plate surface 42b can also contact the bearing housing 3. The circular plate portion 42 helps to suppress the temperature rise of the bearing housing 3.

[0083] Spring portion 43 protrudes from the main surface 42a of the circular plate. The circular plate portion 42 and spring portion 43 are formed integrally. Spring portion 43 is annular about the axis of rotation AX. The cross-sectional shape of spring portion 43 is not particularly limited as long as it can generate a restoring force when compressed. Similar to the disc spring 39 of the first embodiment, one spring portion 43 contacts multiple nozzle connecting plates 36. By appropriately setting the diameter of spring portion 43, the position of the point of action PA can be arbitrarily set. Figure 5 In the example shown, the position where the spring part 43 contacts the nozzle connecting plate 36 (the position of the point of action PA) is the second region S2. For example, if the diameter is smaller than Figure 5 The spring section 43 shown can also set the position of the point of action PA in the first region S1.

[0084] Like the disc spring 39 in the first embodiment, the heat shield 41 applies force to the nozzle connecting plate 36 while in contact with it. The turbine 10A according to the second embodiment achieves the same effect as the turbine 10 in the first embodiment.

[0085] [Third Implementation Method]

[0086] Figure 7 This is an enlarged cross-sectional view showing the main part of the turbine 10B in the third embodiment. Figure 8 This is a top view showing the force-applying component of the turbine 10B according to the third embodiment. In the first embodiment, a disc spring 39 is exemplified as the force-applying component. In the first embodiment, a structure in which a disc spring 39 presses against multiple nozzle vane units 300 is illustrated. However, the force-applying component is not limited to the disc spring 39. Nor is the force-applying component limited to a structure in which a single force-applying component presses against multiple nozzle vane units 300. In the third embodiment, a helical spring 51 is exemplified as the force-applying component. Furthermore, in the third embodiment, a structure in which a single helical spring 51 (force-applying component) presses against one nozzle vane unit 300 is illustrated.

[0087] A helical spring 51 is disposed between the nozzle connecting plate 36 and the bearing housing 3. Furthermore, the helical spring 51 and the nozzle shaft 37 are mounted on the same shaft. One helical spring 51 is disposed relative to each nozzle connecting plate 36 (see reference). Figure 8 ).

[0088] More specifically, the front end 51a of the helical spring 51 contacts the back end 36b of the nozzle connecting plate 36. The back end 36b of the connecting plate is a flat surface, thus facilitating the precise setting of the distance from the back end 36b of the connecting plate to the main surface 3a of the bearing housing. This distance affects the magnitude of the force F generated by the helical spring 51. If the distance from the back end 36b of the connecting plate to the main surface 3a of the bearing housing can be set with high precision, the magnitude of the force F generated by the helical spring 51 can also be set with high precision. The rear end 51b of the helical spring 51 contacts the main surface 3a of the bearing housing.

[0089] Furthermore, the spring tip 51a is configured to surround the nozzle shaft tip 37e. The nozzle shaft tip 37e is disposed inside the helical spring 51. The spring tip 51a is said to contact the first region S1 of the nozzle connecting plate 36. The line of action of the force F generated by the helical spring 51 is also said to coincide with the nozzle axis NX. When the line of action of the force F does not coincide with the nozzle axis NX, a torque corresponding to the distance from the line of action to the nozzle axis NX is generated. This torque corresponding to the distance from the line of action to the nozzle axis NX causes the nozzle shaft 37 to tilt (see reference). Figure 3 This creates a force that presses the outer circumferential surface 37s of the nozzle shaft against the inner circumferential surface 32s1 of the nozzle shaft hole 32s. On the other hand, when the line of action of the force F is aligned with the nozzle axis NX, no torque is generated that causes the nozzle shaft 37 to tilt. Therefore, only a force that moves the nozzle blade unit 300 along the nozzle axis NX can be applied.

[0090] In the turbine 10B of the third embodiment, the force of the helical spring 51 is applied to the region near the nozzle shaft 37. Therefore, it is possible to suppress the tilting of the force F relative to the nozzle axis NX of the nozzle shaft 37. It is possible to suppress contact between the nozzle shaft 37 and the inner circumferential surface 32s1 of the nozzle shaft hole 32s.

[0091] [Fourth Implementation Method]

[0092] In the first embodiment, a structure is employed to eliminate the first gap C1 in order to suppress oscillation rotation. Suppression of oscillation rotation can also be achieved by eliminating the third gap C3 between the outer circumferential surface 37s of the nozzle shaft and the inner circumferential surface 32s1 of the nozzle shaft hole 32s. In the fourth embodiment, a force-applying component for eliminating the third gap C3 is illustrated.

[0093] Figure 9 This is an enlarged cross-sectional view showing the main parts of the turbine 10C according to the fourth embodiment. Additionally, Figure 10This is a top view showing the force-applying component of the turbine 10C according to the fourth embodiment. The turbine 10C of the fourth embodiment differs from the turbine 10 of the first embodiment in that it has a ring spring 61 instead of a disc spring 39.

[0094] The ring spring 61 is a spring component. A piston ring or washer can also be used as the force-applying component. The ring spring 61 is wheel-shaped with a portion of its circumference cut off around its axis of rotation AX. Therefore, when viewed from above, the ring spring 61 appears C-shaped. The cut portion of the ring spring 61 has a pair of separate spring ends 61e1 and 61e2. If the first spring end 61e1 is deformed to bring the second spring end 61e2 closer together, the diameter of the ring spring 61 decreases. This generates a restoring force in the ring spring 61 to its original diameter. The direction of this restoring force can also be considered to be the same as the direction of the diameter of the ring spring 61.

[0095] The annular spring 61 includes an outer peripheral surface 61a and an inner peripheral surface 61b. The outer peripheral surface 61a contacts the base end 36f of the nozzle connecting plate 36. More specifically, the outer peripheral surface 61a contacts the base end face of the base end 36f of the connecting plate. Furthermore, the annular spring 61 is C-shaped when viewed from above. Therefore, one annular spring 61 presses multiple nozzle connecting plates 36 radially outward. The inner peripheral surface 61b is disposed in a spring groove 3g provided in the bearing housing 3. The spring groove 3g is provided on the outer peripheral surface of the insert 3s protruding from the main surface 3a of the bearing housing towards the turbine housing 11. This structure allows for deformation of the annular spring 61, allowing its diameter to expand or shrink. Additionally, it restricts the movement of the annular spring 61 in the direction of the rotation axis AX. Therefore, it prevents the position of the annular spring 61 from shifting in the direction of the rotation axis AX, thus maintaining the pressed state of the nozzle connecting plates 36.

[0096] The annular spring 61, in contact with the nozzle connecting plate 36, applies a radial force to the nozzle shaft 37. If a radial force is applied to the nozzle connecting plate 36, the nozzle connecting plate 36 moves radially. If the nozzle connecting plate 36 moves, the nozzle shaft 37, mounted on the base end 36f of the connecting plate, moves radially. Then, the nozzle shaft 37 abuts against the inner circumferential surface 32s1 of the nozzle shaft hole 32s of the nozzle ring 32. The radial third gap C3 between the nozzle blade 34 and the nozzle ring 32 is eliminated.

[0097] According to the turbine 10C of the fourth embodiment, the relative movement of the nozzle vane unit 300 with respect to the nozzle ring 32 is limited to rotation about the nozzle shaft 37, suppressing other unwanted movements such as oscillations and rotations. Therefore, even if the nozzle blade 34 is subjected to irregular forces, the nozzle vane unit 300 does not produce irregular movement. The state of the component assembly constituting the variable capacity mechanism 30 can be maintained in good condition, thus maintaining the variable capacity mechanism 30 in a state where it can perform the desired performance. Therefore, the reliability of the turbine 10C equipped with the variable capacity mechanism 30 can be improved.

[0098] This disclosure is not limited to the embodiments described above, and various modifications can be made without departing from the spirit of this disclosure. For example, the manner of the force-applying component is not limited to the manner described in the embodiments.

[0099] <First Variation>

[0100] Figure 11 This is an enlarged cross-sectional view showing the main part of the turbine 10D in the first modified example. The turbine 10D in the first modified example differs from the turbine 10B in the third embodiment in that it has a spring 71 instead of a helical spring 51.

[0101] The spring 71 can be, for example, a helical spring or a disc spring. The spring 71 is disposed between the nozzle ring 32 and the nozzle connecting plate 36. Specifically, the spring 71 is disposed between the back surface 32b1 of the main body of the nozzle ring 32 and the main surface 36a of the connecting plate of the nozzle connecting plate 36. Furthermore, the spring 71 and the nozzle shaft 37 are configured to be substantially coaxial. One spring 71 is disposed relative to one nozzle connecting plate 36. For example, if the spring 71 is a helical spring, the nozzle shaft 37 is inserted inside the helical spring.

[0102] When the spring 71 is in contact with the nozzle connecting plate 36, it applies a force F in the direction of the nozzle axis NX. The direction of the force F generated by the spring 71 is opposite to the direction of the force F generated by the helical spring 51 in the third embodiment. If an axial force F is applied to the nozzle connecting plate 36, the nozzle connecting plate 36 moves along the nozzle axis NX. The nozzle connecting plate 36 separates from the nozzle ring 32. If the nozzle connecting plate 36 separates from the nozzle ring 32, the nozzle shaft 37 mounted on the connecting plate base end 36f of the nozzle connecting plate 36 moves axially. The nozzle blade 34 mounted on the nozzle shaft base end 37f moves along the nozzle axis NX. The back surface 34b of the nozzle blade 34 abuts against the main surface 32a of the nozzle ring. The second gap C2 between the nozzle blade 34 and the nozzle ring 32 is eliminated.

[0103] The turbine 10D of the first modified example, like the turbine 10 of the first embodiment, can suppress unwanted oscillations and rotations.

[0104] <Second Variation>

[0105] Figure 12 This is an enlarged cross-sectional view showing the main parts of the turbine 10E in the second modified example. The turbine 10E in the second modified example differs from the turbine 10B in the third embodiment in that it also includes a heat shield 81. A helical spring 51 is disposed between the nozzle connecting plate 36 and the heat shield 81. Figure 12 As shown, the helical spring 51 contacts the nozzle connecting plate 36. The other end of the helical spring 51 contacts the heat shield 81. When the helical spring 51 is in contact with the first region of the nozzle connecting plate 36, it applies a force F in the direction of the nozzle axis NX. The turbine 10E according to the second modification example has the same effect as the turbine 10B of the third embodiment.

[0106] <Third Variation>

[0107] Figure 13 This is a cross-sectional view of the turbocharger 1F of the turbine 10F with the third variant. For example, in the first embodiment, the case where the CC plate 31 faces the nozzle blade 34 is described. Figure 13 As shown, the portion facing the nozzle blade 34 can also be the turbine housing 11A. The turbine housing 11A includes a flow surface 11s that faces the end face opposite to the end face of the nozzle blade 34 on which the nozzle shaft 37 is mounted. The nozzle blade 34 can also abut against the flow surface 11s of the turbine housing 11A. With this structure, other components for contact between the nozzle blade 34 and the turbine housing 11A, namely the CC plate 31, are not required. Therefore, the turbine 10 can be configured with a simplified structure.

[0108] <Fourth Variation>

[0109] Figure 14 This is an enlarged cross-sectional view showing the main parts of the variable capacity mechanism 30G of the turbine 10G in the fourth modified example. For example, in the first embodiment, a structure is shown in which a nozzle shaft 37 is provided on the back surface 34b of the nozzle blade 34. The support structure of the first embodiment is a so-called one-end support. Figure 14 As shown, the support structure of the nozzle blade 34G can also be a so-called two-end support. In the fourth variation, the nozzle blade 34G can also have a nozzle shaft 37K on the main surface 34a of the blade opposite to the back surface 34b of the blade on which the nozzle shaft 37 is provided. The nozzle shaft 37K and the nozzle shaft 37 are formed on the same axis. The nozzle shaft 37K is inserted into the hole 31q formed in the CC plate 31. The nozzle blade 34 is supported on both sides of the CC plate 31G and the nozzle ring 32 by the nozzle shafts 37 and 37K.

[0110] Explanation of reference numerals in the attached figures

[0111] 10, 10A, 10B, 10C, 10D, 10E, 10F, 10G… Turbine; 11… Turbine housing (casing); 11R… Inlet; 11s… Flow path; 12… Turbine impeller; 30, 30G… Variable capacity mechanism; 31… CC plate (circular plate component); 32… Nozzle ring; 32b1… Back side of main body; 32s1… Inner circumferential surface; 34, 34G… Nozzle blade; 36… Nozzle connecting plate; 37… Nozzle shaft; 39… Butterfly spring (force-applying component); 61… Ring spring (force-applying component); 300… Nozzle wing unit; F… Force (applying force); S1… First region; S2… Second region.

Claims

1. A turbine, characterized in that, have: Turbine impeller; The housing includes a flow path for gas flow received from the air inlet; A variable capacity mechanism, disposed within the housing and receiving gas from the flow path and guiding it to the turbine impeller, comprises a circular nozzle ring and a nozzle vane unit. The nozzle ring has a main face and a back face facing the turbine impeller. The nozzle vane unit includes: a nozzle blade disposed on the main face side of the nozzle ring, a nozzle shaft extending from the nozzle blade and passing through the nozzle ring, and a nozzle connecting plate disposed on the back face side of the nozzle ring and connected to the front end of the nozzle shaft. The force-applying component applies a force axially along the nozzle axis while in contact with the nozzle wing unit. The nozzle blade comes into contact with the part facing the nozzle blade by means of the force. The nozzle connecting plate includes: a first region that overlaps with the nozzle blade when viewed from the axial direction, and a second region that does not overlap with the nozzle blade. The part of the force-applying component that contacts the nozzle connecting plate is located in the second region.

2. The turbine according to claim 1, characterized in that, The variable capacity mechanism also includes a circular plate component that cooperates with the nozzle ring to clamp the nozzle blades. The part facing the nozzle blade is the circular plate component.

3. The turbine according to claim 1, characterized in that, The housing includes a flow surface that faces an end face opposite to the end face of the nozzle blade on which the nozzle shaft is disposed. The portion facing the nozzle blade is the flow path of the housing.

4. The turbine according to any one of claims 1 to 3, characterized in that, The axial distance from the nozzle ring to the nozzle connecting plate is greater than the axial distance from the nozzle blade to the portion facing the nozzle blade.

5. A turbine, characterized in that, have: Turbine impeller; The housing includes a flow path for gas flow received from the air inlet; A variable capacity mechanism, disposed within the housing and receiving gas from the flow path and guiding it to the turbine impeller, comprises a circular nozzle ring and a nozzle vane unit. The nozzle ring has a main face and a back face facing the turbine impeller. The nozzle vane unit includes: a nozzle blade disposed on the main face side of the nozzle ring, a nozzle shaft extending from the nozzle blade and passing through the nozzle ring, and a nozzle connecting plate disposed on the back face side of the nozzle ring and connected to the front end of the nozzle shaft. The force-applying component applies a force radially along the nozzle axis while in contact with the nozzle connecting plate of the nozzle wing unit. The nozzle shaft abuts against the inner circumferential surface of the through hole of the nozzle ring.

6. A booster, characterized in that, It has a turbine as described in any one of claims 1 to 5.

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