Nozzle ring and turbine end structure

Abstract

The utility model provides a nozzle ring and a turbine end structure, the nozzle ring realizes the installation of a plurality of blade assemblies through a fixed part and a movable part, and the movement of the blade assemblies is controlled through the rotation of the movable part; and due to the design of the two-way supporting assembly, the movable part is stressed more uniformly when working in a high-temperature environment. The elastic ring provides uniform support from one side, the spacer sleeve provides uniform support from the other side, and the deformation risk of the movable part can be reduced through the combined action. Therefore, the problems of fatigue cracks, thermal deformation clamping stagnation and insufficient vibration suppression capability caused by uneven stress of the movable part of the nozzle ring are solved, the service life of the nozzle ring is effectively prolonged, and the stability of the nozzle ring is effectively improved; the turbine end structure comprises the nozzle ring, and when the nozzle ring is stressed more evenly under the high-temperature working condition and is not prone to damage, the whole turbine end structure can still keep the long service life.

Description

Technical Field

[0001] This utility model relates to the field of turbocharging technology, specifically to a nozzle ring and turbine end structure. Background Technology

[0002] The nozzle ring is a crucial component of a turbocharger. It consists of a set of movable blades with variable cross-sections. A power source can control the rotation of these blades, thereby controlling the flow rate of exhaust gas and ultimately the turbine speed. The movable blades can close at low engine speeds and low exhaust volume, using a smaller cross-sectional area to increase the engine's intake pressure. This allows the turbine to start smoothly even at low speeds, mitigating turbo lag. At high engine speeds, the larger cross-sectional area increases the intake pressure, boosting the boost pressure and thus increasing the engine's maximum power and torque. The nozzle ring effectively addresses turbo lag and non-linear power delivery issues in turbochargers.

[0003] Existing nozzle rings often suffer from fatigue cracks, thermal deformation and jamming, and insufficient vibration suppression during airflow pulsation. This is because the moving part of the nozzle ring is not subjected to uniform stress when working in a high-temperature environment. Areas with less stress on the moving part are prone to deformation, which ultimately leads to the above problems. This makes the entire nozzle ring and turbine end structure prone to damage and reduces service life. Utility Model Content

[0004] The problem to be solved by this utility model is to provide a nozzle ring that is more uniformly stressed and less prone to damage when the moving part works in a high-temperature environment, and a turbine end structure with such a nozzle ring.

[0005] The technical solution adopted by this utility model to solve the above problems is: a nozzle ring, comprising:

[0006] One fixed part;

[0007] Multiple blade assemblies, wherein each blade assembly includes a rocker arm; the multiple blade assemblies are circumferentially disposed on the fixing portion via one end of the rocker arm;

[0008] A movable part; a plurality of the blade assemblies are disposed on the movable part via the other end of the rocker arm; and

[0009] A bidirectional support assembly, wherein the bidirectional support assembly includes an elastic ring disposed on one side of the movable part and a plurality of spacer sleeves disposed circumferentially on the other side of the movable part.

[0010] Compared with existing technologies, this invention achieves the installation of multiple blade assemblies through a fixed part and a movable part, and controls the movement of the blade assemblies by rotating the movable part. The design of the bidirectional support assembly makes the movable part more evenly stressed when working in high-temperature environments. The elastic ring provides uniform support from one side, and the spacer sleeve provides uniform support from the other side, which together reduces the risk of deformation of the movable part. This solves the problems of fatigue cracks, thermal deformation jamming, and insufficient vibration suppression capability caused by uneven stress on the movable part of the nozzle ring, effectively improving the service life and stability of the nozzle ring.

[0011] The present invention provides a nozzle ring, wherein the movable part includes an outer ring, a middle ring and an inner ring arranged sequentially from the outside to the inside; a plurality of blade assemblies are disposed on the middle ring, a plurality of spacer sleeves are disposed on the outer ring, and an elastic ring is disposed on the inner ring.

[0012] The present invention provides a nozzle ring, wherein the outer ring has a plurality of fixing holes distributed circumferentially; the spacer sleeve includes a fixing section and a supporting section connected to each other; the fixing section is configured to cooperate with the fixing holes.

[0013] The present invention discloses a nozzle ring, wherein the thickness of the middle ring is set to be greater than the thickness of the outer ring, and the thickness of the outer ring is set to be greater than the thickness of the inner ring; an outer receiving groove is formed on the outer side of the middle ring to accommodate the fixing part; and an inner receiving groove is formed on the inner side of the middle ring to accommodate the elastic ring.

[0014] The present invention provides a nozzle ring, wherein five spacer sleeves are evenly distributed in the inner ring; the elastic ring includes a first annular contact portion and a second annular contact portion respectively disposed at both ends; the first annular contact portion is configured to abut against the inner ring.

[0015] The present invention provides a nozzle ring, wherein the blade assembly includes a connecting shaft and a blade; the connecting shaft is disposed between the rocker arm and the blade; the middle ring has a movable hole; and the connecting shaft is configured to pass through the movable hole.

[0016] The present invention provides a nozzle ring, which further includes a vortex end heat insulation cover disposed in the inner reservoir; one end of the vortex end heat insulation cover is configured to abut against the inner ring.

[0017] A turbine end structure, including the aforementioned nozzle ring, further includes:

[0018] An intermediate; and

[0019] A vortex housing, wherein the vortex housing is disposed in the intermediate body;

[0020] The nozzle ring is disposed between the intermediate body and the vortex housing.

[0021] According to the present invention, a turbine end structure is provided, wherein the intermediate body includes a support portion extending into the internal storage groove; the support portion includes a first step and a second step; the second annular contact portion is configured to abut against the first step, and the other end of the turbine end heat shield is configured to abut against the second step.

[0022] The present invention provides a turbine end structure, wherein the vortex shell includes an outer wall of the vortex shell, an inner wall of the vortex shell, an exhaust gas flow channel disposed between the outer wall of the vortex shell and the inner wall of the vortex shell, a turbine housing cavity surrounded by the inner wall of the vortex shell, and a transition flow channel disposed between the exhaust gas flow channel and the turbine housing cavity.

[0023] The blades are evenly distributed in the transition channel; the support section is evenly distributed in the transition channel. Attached Figure Description

[0024] Figure 1 This is a perspective view of a nozzle ring according to a preferred embodiment of the present invention from one side.

[0025] Figure 2 This is a perspective view of the nozzle ring from another side according to a preferred embodiment of the present invention;

[0026] Figure 3 This is a side-view cross-sectional schematic diagram of a nozzle ring according to a preferred embodiment of the present invention;

[0027] Figure 4 This is a cross-sectional view of the nozzle ring from another side according to a preferred embodiment of the present invention;

[0028] Figure 5 This is a perspective view of a turbine end structure according to a preferred embodiment of the present invention.

[0029] Figure 6 This is a perspective view of the turbine end structure according to a preferred embodiment of the present invention from another side.

[0030] Figure 7 This is an exploded view of the turbine end structure according to a preferred embodiment of the present invention;

[0031] Figure 8 This is a cross-sectional schematic diagram of a turbine end structure according to a preferred embodiment of the present invention;

[0032] In the figure, fixing part 1;

[0033] Blade assembly 2; rocker arm 21, connecting shaft 22, blade 23;

[0034] Activity section 3; outer ring 31, middle ring 32, inner ring 33, outer receiving groove 34, inner receiving groove 35; fixing hole 311, movable hole 321;

[0035] Bidirectional support assembly 4; elastic ring 41, spacer sleeve 42; first annular contact part 411, second annular contact part 412; fixed section 421, support section 422;

[0036] 5. Vortex end heat shield;

[0037] Intermediate body 6; Support part 61; First step 611, Second step 612;

[0038] 7. Vortex casing; 71. Outer wall of vortex casing; 72. Inner wall of vortex casing; 73. Exhaust gas flow channel; 74. Turbine housing cavity; 75. Transition flow channel. Detailed Implementation

[0039] Before describing any embodiment of this invention in detail, it should be understood that the invention is not limited in its application to the details of the construction and arrangement of the components set forth in the following description or illustrated in the following figures. The invention is capable of other embodiments and can be practiced or carried out in various ways. Furthermore, it should be understood that the wording and terminology used herein are for descriptive purposes and should not be considered limiting. The use of “comprising” or “having” and variations thereof herein is intended to cover the items set forth below and their equivalents, as well as any additional items. Unless otherwise specified or limited, the terms “installation,” “connection,” “support,” and “linkage,” and variations thereof are used broadly and cover both direct and indirect installation, connection, support, and linking. Moreover, “connection” and “linkage” are not limited to physical or mechanical connections or links.

[0040] Furthermore, firstly, in the disclosure of this utility model, the terms "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, the above terms should not be construed as a limitation on this utility model. Secondly, the term "a" should be understood as "at least one" or "one or more," that is, in one embodiment, the number of an element can be one, while in another embodiment, the number of the element can be multiple. The term "a" should not be construed as a limitation on the quantity.

[0041] Those skilled in the art should understand that the embodiments of the present invention described below and shown in the accompanying drawings are merely examples and do not limit the present invention. The purpose of the present invention has been fully and effectively achieved. The function and structural principles of the present invention are shown and described in the following embodiments. Without departing from the stated principles, the implementation of the present invention may have any variations or modifications.

[0042] The embodiments of this utility model will be further described below with reference to the accompanying drawings.

[0043] Please see Figure 1-4 The nozzle ring shown includes a fixed part 1, a plurality of blade assemblies 2, a movable part 3, and a bidirectional support assembly 4; the blade assembly 2 includes a rocker arm 21; the plurality of blade assemblies 2 are circumferentially disposed on the fixed part 1 via one end of the rocker arm 21; the plurality of blade assemblies 2 are disposed on the movable part 3 via the other end of the rocker arm 21; the bidirectional support assembly 4 includes an elastic ring 41 disposed on one side of the movable part 3 and a plurality of spacer sleeves 42 disposed circumferentially on the other side of the movable part 3.

[0044] In practical use, this invention uses the fixed part 1 and the movable part 3 to install multiple blade assemblies 2, and controls the movement of the blade assemblies 2 by rotating the movable part 3. The design of the bidirectional support assembly 4 makes the movable part 3 more evenly stressed when working in high-temperature environments. The elastic ring 41 provides even support from one side, and the spacer sleeve 42 provides even support from the other side, which together reduce the risk of deformation of the movable part 3. This solves the problems of fatigue cracks, thermal deformation jamming, and insufficient vibration suppression caused by uneven stress on the movable part 3 of the nozzle ring, effectively improving the service life and stability of the nozzle ring.

[0045] Please continue reading. Figure 3 , Figure 4 The movable part 3 includes an outer ring 31, a middle ring 32 and an inner ring 33 arranged sequentially from the outside to the inside; a plurality of blade assemblies 2 are arranged in the middle ring 32, a plurality of spacer sleeves 42 are arranged in the outer ring 31, and the elastic ring 41 is arranged in the inner ring 33.

[0046] In some embodiments, the outer ring 31, middle ring 32, and inner ring 33 adopt a concentric ring structure, and the division of different functional areas is achieved through a layered design. The outer ring 31 is mainly used to support the spacer sleeve 42, the middle ring 32 serves as the mounting carrier for the blade assembly 2, and the inner ring 33 is used to fix the elastic ring 41. This stepped thickness design can optimize the distribution of structural strength. The spacer sleeves 42 can be arranged at equal angular intervals on the outer ring 31, for example, one spacer sleeve is set every 72 degrees, with a total of 5 spacer sleeves 42 evenly distributed. The fit between the elastic ring 41 and the inner ring 33 can be achieved by interference fit or snap-fit ​​connection.

[0047] In use, this invention optimizes the force transmission path by dividing the movable part 3 into a three-layer structure: an outer ring 31, a middle ring 32, and an inner ring 33. The outer ring 31 bears external loads through the spacer sleeve 42, the middle ring 32 concentrates the load of the blade assembly 2's motion, and the inner ring 33 provides support through the elastic ring 41. This layered design allows the movable part 3 to maintain a uniform stress state under high-temperature working conditions, avoiding deformation problems caused by local stress concentration, significantly improving the stability of the nozzle ring under high-temperature conditions, effectively solving the problems of thermal deformation jamming and insufficient vibration suppression, and ensuring the reliability and durability of the movable part 3 under complex working conditions through the clear division and targeted design of each functional area.

[0048] Please continue reading. Figure 3 The outer ring 31 has a plurality of fixing holes 311 distributed circumferentially; the spacer sleeve 42 includes a fixing section 421 and a supporting section 422 connected to each other; the fixing section 421 is configured to cooperate with the fixing holes 311.

[0049] In some embodiments, fixing holes 311 are evenly distributed circumferentially on the outer ring 31 for precise installation of the spacer sleeve 42. The fixing section 421 has a cylindrical structure, and its diameter forms a transition fit or interference fit with the fixing holes 311 to ensure assembly stability. The support section 422 may have a solid columnar structure, and its length is determined according to the distance between the movable part 3 and the outer ring 31. As a preferred embodiment, the fixing section 421 and the support section 422 are connected by threads or integrally formed, wherein the threaded connection facilitates adjustment of the length of the support section 422, and the integral forming can improve structural strength. The fixing holes 311 may be designed as through holes or blind holes. Through holes facilitate machining and assembly positioning, while blind holes can prevent impurities from entering.

[0050] In use, this invention achieves precise support and positioning of the outer ring 31 of the movable part 3 through the mating structure of the fixing hole 311 and the spacer sleeve 42. Specifically, the mating of the fixing section 421 and the fixing hole 311 effectively limits radial displacement, while the support section 422 ensures axial positioning accuracy through length control. This structure allows the movable part 3 to maintain uniform stress under high-temperature operating conditions, avoiding jamming problems caused by local deformation. The circumferentially distributed fixing holes 311, in conjunction with the spacer sleeve 42, form multi-point support, significantly improving the structural stability of the movable part 3. Simultaneously, the modular design reduces the difficulty of processing and assembly.

[0051] Please continue reading. Figure 3 , Figure 4The thickness of the middle ring 32 is set to be greater than the thickness of the outer ring 31, and the thickness of the outer ring 31 is set to be greater than the thickness of the inner ring 33; an outer receiving groove 34 is formed on the outer side of the middle ring 32 to receive the fixing part 1; an inner receiving groove 35 is formed on the inner side of the middle ring 32 to receive the elastic ring 41.

[0052] In some embodiments, the thickness of the middle ring 32 is greater than the thickness of the outer ring 31 and the inner ring 33, so that the middle ring 32 has sufficient structural strength to support the movement of the blade assembly 2 and the rocker arm 21. The formation of the outer receiving groove 34 allows the fixing part 1 to be securely accommodated therein, thereby ensuring the connection reliability of the fixing part 1. The formation of the inner receiving groove 35 provides installation space for the elastic ring 41, so that the elastic ring 41 can effectively apply elastic force to the moving part 3. As a preferred embodiment, the outer receiving groove 34 and the inner receiving groove 35 can be formed on the middle ring 32 by machining or casting. Furthermore, the thickness of the middle ring 32 can be adjusted according to the stress conditions in actual applications. For example, in high temperature or high stress environments, the thickness of the middle ring 32 can be appropriately increased to improve its durability.

[0053] In use, this utility model features ring structures of varying thicknesses, forming an outer receiving groove 34 and an inner receiving groove 35. This design effectively solves the problem of uneven stress on the moving part 3 under high-temperature conditions. Specifically, the blade assembly 2 bears significant exhaust gas pressure, therefore the middle ring 32, which cooperates with the blade assembly 2, needs to possess greater structural strength. The thickened design of the middle ring 32 enhances the overall structural stability and reduces the risk of deformation due to excessive stress. The rational layout of the outer receiving groove 34 and the inner receiving groove 35 not only optimizes space utilization but also improves the installation accuracy of the fixing part 1 and the elastic ring 41, thereby reducing the risk of thermal deformation jamming and insufficient vibration suppression capabilities. This significantly improves the reliability and service life of the nozzle ring under high-temperature operating conditions.

[0054] Please continue reading. Figure 2 , Figure 3 , Figure 4 The spacer sleeves 42 are configured to be five in number and evenly distributed in the inner ring 33; the elastic ring 41 includes a first annular contact portion 411 and a second annular contact portion 412 respectively disposed at both ends; the first annular contact portion 411 is configured to abut against the inner ring 33.

[0055] In some embodiments, five spacer sleeves 42 are evenly distributed on the inner ring 33. This arrangement ensures that the moving part 3 is subjected to uniform force in the circumferential direction. The selection of five spacer sleeves 42 is an optimal solution based on experimental data, which can ensure structural strength while avoiding excessive weight increase. The two ends of the elastic ring 41 are respectively provided with a first annular contact portion 411 and a second annular contact portion 412, wherein the first annular contact portion 411 directly contacts the inner ring 33. As a preferred embodiment, the first annular contact portion 411 can adopt an arc-shaped contact surface design to increase the contact area; the second annular contact portion 412 can adopt a planar design to facilitate cooperation with other components. The elastic ring 41 can be made of a high-temperature resistant alloy material, such as a nickel-based high-temperature alloy.

[0056] In use, this invention effectively solves the problem of uneven stress on the movable part 3 through the evenly distributed spacer sleeves 42 and the elastic ring 41 with a specific contact structure. The even arrangement of the five spacer sleeves 42 ensures that the movable part 3 maintains a stable stress state under high-temperature working conditions, avoiding local stress concentration. The double contact design of the elastic ring 41 ensures reliable contact with the inner ring 33 and facilitates subsequent assembly, thereby significantly improving the structural stability of the nozzle ring under high-temperature conditions, reducing thermal deformation and vibration, and thus extending the service life of the nozzle ring.

[0057] Please continue reading. Figure 2 , Figure 4 The blade assembly 2 includes a connecting shaft 22 and a blade 23; the connecting shaft 22 is disposed between the rocker arm 21 and the blade 23; the middle ring 32 has a movable hole 321; the connecting shaft 22 is configured to pass through the movable hole 321.

[0058] Specifically, this invention, through the establishment of an independent connecting shaft 22 structure, precisely transmits the rotational motion of the rocker arm 21 to the blade 23, while maintaining the relative positional stability of the blade 23 and the central ring 32. The movable hole 321 allows the connecting shaft 22 to maintain smooth movement even when it undergoes minor thermal deformation under high-temperature conditions, preventing jamming. The rigid connection of the connecting shaft 22 effectively suppresses vibrations caused by airflow pulsation, resulting in a more uniform stress distribution on the blade assembly 2.

[0059] Please continue reading. Figure 3 , Figure 4 It further includes a vortex end heat shield 5 disposed in the content reservoir 35; one end of the vortex end heat shield 5 is configured to abut against the inner ring 33.

[0060] In some embodiments, the turbine end heat shield 5 is made of a high-temperature resistant alloy material, such as a nickel-based high-temperature alloy or a cobalt-based high-temperature alloy. The cross-sectional shape of the turbine end heat shield 5 can be designed as a cone to enhance structural strength; by providing the turbine end heat shield 5 on the inner side of the moving part 3, direct heat radiation from high-temperature exhaust gas to the inner side of the moving part 3 is effectively blocked. Specifically, the turbine end heat shield 5 isolates the high-temperature area from the inner ring 33 of the moving part 3, reducing the risk of thermal deformation of other turbocharger components outside the inner ring 33, and avoiding deformation problems of other turbocharger components caused by heat transmitted from the turbine end, thereby improving the overall operating stability and service life of the turbocharger.

[0061] Please see Figure 5-8 The turbine end structure shown includes the aforementioned nozzle ring, an intermediate body 6, and a vortex housing 7; the vortex housing 7 is disposed in the intermediate body 6; and the nozzle ring is disposed between the intermediate body 6 and the vortex housing 7.

[0062] Thus, the turbine end structure, through the cooperative arrangement of the intermediate body 6 and the vortex housing 7, achieves stable support and accurate positioning of the nozzle ring. Specifically, the support portion 61 of the intermediate body 6 and the inner ring 33 of the nozzle ring form a double support structure, effectively improving the uniformity of stress on the moving part 3. The cooperative arrangement of the transition channel 75 of the vortex housing 7 and the blade 23 ensures a smooth transition of exhaust gas flow. This structural design significantly reduces the risk of nozzle ring deformation under high-temperature operating conditions, improving the overall reliability and service life of the structure.

[0063] Please continue reading. Figure 7 , Figure 8 The intermediate body 6 includes a support portion 61 extending into the content storage groove 35; the support portion 61 includes a first step 611 and a second step 612; the second annular contact portion 412 is configured to abut against the first step 611, and the other end of the vortex end heat insulation cover 5 is configured to abut against the second step 612.

[0064] In some embodiments, the support portion 61 is designed with a two-step structure. The first step 611 forms a contact support with the second annular contact portion 412 of the elastic ring 41, and the second step 612 forms a contact support with the vortex end heat shield 5. As a preferred embodiment, the support portion 61 can be integrally formed with the intermediate body 6 using a one-piece casting process, and the step height difference is controlled by precision machining. Furthermore, the insertion depth of the support portion 61 is configured to match the depth of the internal receiving groove 35 to ensure axial positioning accuracy between the components.

[0065] In use, this invention achieves dual axial positioning of the elastic ring 41 and the vortex end heat shield 5 through the stepped structure design of the support part 61. Specifically, the cooperation between the first step 611 and the second annular contact part 412 effectively transmits axial force, preventing axial movement of the elastic ring 41; the limiting effect of the second step 612 on the vortex end heat shield 5 prevents thermal deformation displacement under high-temperature conditions. This dual positioning structure ensures that the movable part 3 maintains a stable axial position under high-temperature operating conditions, further solving the problem of thermal deformation and jamming of the nozzle ring due to uneven force, thereby significantly improving the working stability of the nozzle ring under high-temperature conditions.

[0066] Please continue reading. Figure 7 , Figure 8 The vortex casing 7 includes an outer vortex casing wall 71, an inner vortex casing wall 72, an exhaust gas flow channel 73 disposed between the outer vortex casing wall 71 and the inner vortex casing wall 72, a turbine housing cavity 74 surrounded by the inner vortex casing wall 72, and a transition flow channel 75 disposed between the exhaust gas flow channel 73 and the turbine housing cavity 74; the blades 23 are uniformly disposed in the transition flow channel 75; and the support section 422 is uniformly disposed in the transition flow channel 75.

[0067] In some embodiments, the outer wall 71 and the inner wall 72 of the volute form a double-layer structure, and the exhaust gas passage 73 is used to guide the exhaust gas flow. The turbine housing 74 is used to house the turbine rotor assembly. The transition passage 75 serves as a channel connecting the exhaust gas passage 73 and the turbine housing 74, and its cross-sectional shape can be designed to be tapered or expanded. The arrangement angle of the blades 23 in the transition passage 75 is adjustable, for example, using an installation angle of 15° to 45°.

[0068] In use, this invention optimizes the exhaust gas flow path by integrating the blades 23 and the support section 422 in the transition channel 75 region. The uniform distribution of the blades 23 controls the opening and closing degree of the transition channel 75, thereby controlling its flow velocity according to the exhaust gas discharge conditions. The support section 422 enhances the structural stability of the moving part 3 in the transition channel 75 and suppresses vibrations caused by airflow pulsation. This arrangement allows for more efficient transfer of exhaust gas energy to the turbine. Under high-temperature operating conditions, this structure maintains stable airflow guidance performance and reduces the impact of thermal deformation on the airflow channel.

[0069] The above description only illustrates the preferred embodiment of this utility model and should not be construed as limiting the scope of the claims. This utility model is not limited to the above embodiments, and variations in its specific structure are permitted. All changes made within the scope of the independent claims of this utility model are also within the scope of protection of this utility model.

Claims

1. A nozzle ring, characterized in that... ,include: One fixed part (1); Multiple blade assemblies (2), wherein each blade assembly (2) includes a rocker arm (21); the multiple blade assemblies (2) are circumferentially disposed on the fixing part (1) via one end of the rocker arm (21); A movable part (3); a plurality of the blade assemblies (2) are disposed on the movable part (3) via the other end of the rocker arm (21); and A bidirectional support assembly (4), wherein the bidirectional support assembly (4) includes an elastic ring (41) disposed on one side of the movable part (3) and a plurality of spacer sleeves (42) disposed circumferentially on the other side of the movable part (3).

2. The nozzle ring according to claim 1, characterized in that: The active part (3) includes an outer ring (31), a middle ring (32) and an inner ring (33) arranged sequentially from the outside to the inside; a plurality of blade assemblies (2) are arranged in the middle ring (32), a plurality of spacers (42) are arranged in the outer ring (31), and the elastic ring (41) is arranged in the inner ring (33).

3. The nozzle ring according to claim 2, characterized in that: The outer ring (31) has a plurality of fixing holes (311) distributed circumferentially; the spacer sleeve (42) includes a fixing section (421) and a support section (422) connected to each other; the fixing section (421) is configured to cooperate with the fixing holes (311).

4. The nozzle ring according to claim 3, characterized in that: The thickness of the middle ring (32) is set to be greater than the thickness of the outer ring (31), and the thickness of the outer ring (31) is set to be greater than the thickness of the inner ring (33); an outer receiving groove (34) is formed on the outer side of the middle ring (32) to receive the fixing part (1); an inner receiving groove (35) is formed on the inner side of the middle ring (32) to receive the elastic ring (41).

5. The nozzle ring according to claim 4, characterized in that: The spacer sleeve (42) is configured to be five in number and evenly distributed in the inner ring (33); the elastic ring (41) includes a first annular contact portion (411) and a second annular contact portion (412) respectively disposed at both ends; the first annular contact portion (411) is configured to abut against the inner ring (33).

6. The nozzle ring according to claim 2, characterized in that: The blade assembly (2) includes a connecting shaft (22) and a blade (23); the connecting shaft (22) is disposed between the rocker arm (21) and the blade (23); the middle ring (32) has a movable hole (321); the connecting shaft (22) is configured to pass through the movable hole (321).

7. The nozzle ring according to claim 4, characterized in that: It further includes a vortex end heat shield (5) disposed in the content reservoir (35); one end of the vortex end heat shield (5) is configured to abut against the inner ring (33).

8. A turbine end structure, comprising the nozzle ring as described in any one of claims 1-7, characterized in that... It also includes: An intermediate (6); and A vortex shell (7), wherein the vortex shell (7) is disposed in the intermediate body (6); The nozzle ring is disposed between the intermediate body (6) and the vortex shell (7).

9. The turbine end structure according to claim 8, characterized in that: The intermediate body (6) includes a support portion (61) extending into the content reservoir (35); the support portion (61) includes a first step (611) and a second step (612); the second annular contact portion (412) is configured to abut against the first step (611), and the other end of the vortex end heat shield (5) is configured to abut against the second step (612).

10. The turbine end structure according to claim 8, characterized in that: The vortex housing (7) includes an outer wall (71), an inner wall (72), an exhaust gas passage (73) disposed between the outer wall (71) and the inner wall (72), a turbine housing cavity (74) surrounded by the inner wall (72), and a transition passage (75) disposed between the exhaust gas passage (73) and the turbine housing cavity (74). The blades (23) are uniformly arranged in the transition channel (75); the support section (422) is uniformly arranged in the transition channel (75).

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