Nozzle ring assembly for turbocharger

Abstract

The utility model relates to the technical field of turbochargers, and discloses a nozzle ring assembly for a turbocharger, which comprises a chassis, the inner wall of the chassis is rotatably connected with a rotating disc, the upper surface of the rotating disc is fixedly connected with a cover plate, the inner wall of the cover plate is fixedly connected with a fixed ring, and the fixed ring is fixedly connected with a nozzle. According to the turbine blade nozzle ring, the circulation cross section can be reduced and the rotating speed of a turbine can be increased when an engine rotates at a low speed by arranging the turbine blade nozzle ring, so that a higher supercharging effect is provided, a torque curve is improved, and the engine can generate more power at a low speed; within the whole engine rotating speed range, the variable nozzle ring can adjust airflow according to needs, reduce unnecessary energy loss and improve fuel efficiency, through precise mechanical connection and fixing design such as use of threaded fixing holes and fixing bolts, the whole device can keep structural stability and sealing performance in the high-temperature and high-pressure environment, and the service life of the device is prolonged. Abrasion is reduced, and the service life is prolonged.

Description

Technical Field

[0001] The utility model relates to the technical field of turbochargers, in particular to a nozzle ring assembly for a turbocharger. Background Art

[0002] Turbocharger technology, as a key means of improving internal combustion engine performance, has long been a research hotspot in the automotive industry and high-performance engine design. However, traditional turbochargers are limited in their boost efficiency and response speed under varying engine operating conditions by a fixed geometry, which restricts engine performance across the full operating range. The nozzle ring, a core component responsible for regulating the flow of gas into the turbine, presented several challenges in early nozzle ring designs. For example, the blade structure was not conducive to the flow of high-speed, high-temperature gas, resulting in significant impact and friction losses. Summary of the Invention

[0003] In order to solve the above technical problems, the utility model provides a nozzle ring assembly for a turbocharger.

[0004] The utility model is implemented by the following technical solution: a nozzle ring assembly for a turbocharger, comprising a chassis, an inner wall of the chassis being rotatably connected to a rotating disk, an upper surface of the rotating disk being fixedly connected to a cover plate, an inner wall of the cover plate being fixedly connected to a fixing ring, and an upper surface of the cover plate being provided with a plurality of first mounting holes.

[0005] Through the above technical solution, the rotating connection between the chassis and the rotating disk enables the nozzle ring to adjust the opening size under different engine operating conditions, optimize the airflow path, and thus improve combustion efficiency and power response speed. The cover plate and fixing ring increase the overall rigidity and sealing of the structure, ensuring the smooth guidance of high-pressure gas, while also improving the durability of the device.

[0006] As a further improvement of the above solution, a connecting column is sleeved on the inner wall of the first mounting hole, and a turbine blade is fixedly connected to the upper surface of the connecting column.

[0007] Through the above technical solution, the combination of the connecting column and the turbine blades further refines the power conversion process. The turbine blades are firmly connected to the nozzle ring assembly through the connecting column, ensuring good power transmission and directional control even at high-speed rotation, enhancing the overall dynamic balance and reducing the risk of wear.

[0008] As a further improvement of the above solution, a rotating connecting rod is fixedly connected to the bottom of the connecting column.

[0009] Through the above technical solution, the rotating connecting rod is connected to the bottom end of the connecting column, ensuring that the rotational power of the turbine blades can be smoothly and effectively transmitted to the underlying structure, which is adjusted by the rotation of the rotating connecting rod.

[0010] As a further improvement of the above solution, a plurality of second mounting holes are provided on the upper surface of the rotating disk, and the second mounting holes are adapted to the connecting columns.

[0011] Through the above technical solution, the adaptive design of the second mounting hole and the connecting column ensures assembly accuracy and reduces debugging time and cost during the production process.

[0012] As a further improvement of the above solution, a plurality of mounting grooves are provided on the lower surface of the chassis, and the mounting grooves are adapted to the rotating connecting rods.

[0013] Through the above technical solution, the matching design of the mounting groove and the rotating connecting rod not only facilitates the disassembly and maintenance of the nozzle ring assembly, but also reduces the complexity of operation and shortens the maintenance cycle in actual application, significantly reducing maintenance costs and downtime.

[0014] As a further improvement of the above solution, a plurality of first threaded fixing holes are provided on the lower surface of the rotating disk, and a plurality of second threaded fixing holes are provided on the lower surface of the cover plate.

[0015] Through the above technical solution, the double-threaded fixing system of the first threaded fixing hole and the second threaded fixing hole greatly enhances the connection stability between the cover plate and the rotating disk.

[0016] As a further improvement of the above solution, the internal thread of the first threaded fixing hole is connected to a fixing bolt, and the fixing bolt is adapted to the second threaded fixing hole.

[0017] Through the above technical solution, the addition of the fixing bolts ensures seamless connection between the two threaded fixing holes, which not only simplifies the assembly process but also ensures safety in long-term use.

[0018] Compared with the prior art, the beneficial effects of the present invention are:

[0019] The utility model is capable of reducing the flow cross-section at low engine speeds and accelerating the turbine speed by arranging a turbine blade nozzle ring, thereby providing a higher boost effect, improving the torque curve, and enabling the engine to generate more power at low speeds. Within the entire engine speed range, the variable nozzle ring can adjust the airflow as needed, reduce unnecessary energy loss, and improve fuel efficiency. Through precise mechanical connection and fixing design, such as the use of threaded fixing holes and fixing bolts, the overall device can maintain structural stability and sealing in high temperature and high pressure environments, reduce wear, and extend service life. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 This is a schematic diagram of the overall structure of the utility model;

[0021] Figure 2This is a schematic diagram of the structure of the utility model when viewed from above;

[0022] Figure 3 This is a schematic diagram of the explosion structure of the utility model;

[0023] Figure 4 This is a schematic diagram of the explosion structure of the utility model;

[0024] Figure 5 This is a schematic diagram of the turbine blade structure of the utility model.

[0025] Description of main symbols:

[0026] 1. Chassis; 2. Rotating plate; 3. Cover plate; 4. Fixing ring; 5. First mounting hole; 6. Connecting column; 7. Turbine blade; 8. Rotating connecting rod; 9. Second mounting hole; 10. Mounting slot; 11. First threaded fixing hole; 12. Second threaded fixing hole; 13. Fixing bolt. DETAILED DESCRIPTION

[0027] Below, the present invention is further described in conjunction with the accompanying drawings and specific implementation methods. It should be noted that, under the premise of no conflict, the various embodiments or technical features described below can be arbitrarily combined to form new embodiments. Example

[0028] Please combine Figure 1-5 The cam 3 is provided with a plurality of holes 5 on the top of the cover plate 3, and the cam 3 is provided with a plurality of holes 5 on the top of the cover plate 3.

[0029] The inner wall of the first mounting hole 5 is sleeved with a connecting column 6, and the upper surface of the connecting column 6 is fixedly connected to the turbine blade 7. The connecting column 6 is inserted into the first mounting hole 5. Its main task is to carry and fix the turbine blade 7 to ensure the effective transmission of force between the blade and the base. The turbine blade 7 is fixed at the top of the connecting column 6 and directly interacts with the gas flow. It is the core executor of energy conversion.

[0030] The bottom of the connecting column 6 is fixedly connected with a rotating connecting rod 8, and the rotating connecting rod 8 is connected to the bottom end of the connecting column 6, so as to ensure that the rotating power of the turbine blade 7 can be stably and effectively transmitted to the underlying structure, and the rotating connecting rod 8 is adjusted through rotation.

[0031] A plurality of second mounting holes 9 are formed in the upper surface of the rotating disc 2, and the second mounting holes 9 are matched with the connecting column 6. The second mounting holes 9 are arranged on the rotating disc 2 and are in alignment with the connecting column 6, so as to ensure accurate matching of the two in the spatial position and to make the power transmission more efficient.

[0032] A plurality of mounting grooves 10 are formed in the lower surface of the bottom disc 1, and the mounting grooves 10 are matched with the rotating connecting rod 8. The mounting grooves 10 are arranged below the bottom disc 1 and correspond to the rotating connecting rod 8, so as to provide the latter with a guide rotation and to reduce noise and vibration during operation.

[0033] A plurality of first threaded fixing holes 11 are formed in the lower surface of the rotating disc 2, and a plurality of second threaded fixing holes 12 are formed in the lower surface of the cover plate 3. The first threaded fixing holes 11 and the second threaded fixing holes 12 are respectively formed in the rotating disc 2 and the cover plate 3, and are connected to each other through bolts, so as to realize tight locking of the two.

[0034] The first threaded fixing holes 11 are threadedly connected with fixing bolts 13, and the fixing bolts 13 are matched with the second threaded fixing holes 12. The fixing bolts 13 ensure absolute fixation between the cover plate 3 and the rotating disc 2, so as to avoid the risk of loosening under high-speed rotation.

[0035] The implementation principle of a nozzle ring assembly for a turbocharger in the embodiment of the present application is as follows: the chassis 1 provides the basic framework and support of the overall device, and the cavity in the central area allows the rotating disk 2 to be rotatably connected to its inner wall, ensuring that the rotating disk can rotate freely around the axis without generating additional friction resistance. The cover plate 3 is fastened to the upper surface of the rotating disk 2, which not only seals and protects the internal structure, but also increases the overall rigidity through the fixing ring 4, providing a support platform for subsequent components. The fixing ring 4 enhances the stability of the connection between the cover plate 3 and other components to prevent deformation caused by high-speed operation. The first mounting holes 5 are distributed at multiple preset positions on the cover plate 3, laying the foundation for the precise positioning and installation of the connecting column 6 of the subsequent components. The connecting column 6 is inserted into the first mounting hole 5. Its main task is to carry and fix the turbine blade 7 to ensure the effective transmission of force between the blade and the base. The turbine blade 7 is fixed to the connecting column. The top of the connecting column 6 directly interacts with the gas flow and is the core executor of energy conversion. The rotating connecting rod 8 is connected to the bottom end of the connecting column 6 to ensure that the rotational power of the turbine blades 7 can be smoothly and effectively transmitted to the underlying structure. The rotating connecting rod 8 is adjusted by rotating it. The second mounting hole 9 is provided on the rotating disk 2 to form a corresponding position with the connecting column 6 to ensure that the two are accurately matched in spatial position, making power transmission more efficient. The mounting groove 10 is located below the chassis 1 and corresponds to the rotating connecting rod 8 to provide guided rotation for the latter while reducing noise and vibration during operation. The first threaded fixing hole 11 and the second threaded fixing hole 12 are respectively opened under the rotating disk 2 and the cover plate 3, and are connected to each other by bolts to achieve tight locking of the two. The fixing bolt 13 ensures absolute fixation between the cover plate 3 and the rotating disk 2, avoiding the risk of loosening under high-speed rotation.

[0036] The above-mentioned embodiments are only preferred embodiments of the present invention and cannot be used to limit the scope of protection of the present invention. Any non-substantial changes and replacements made by technicians in this field on the basis of the present invention fall within the scope of protection required by the present invention.

Claims

1. A nozzle ring assembly for a turbocharger, characterized in that: The invention comprises a chassis (1), wherein the inner wall of the chassis (1) is rotatably connected to a rotating disk (2), the upper surface of the rotating disk (2) is fixedly connected to a cover plate (3), the inner wall of the cover plate (3) is fixedly connected to a fixing ring (4), and the upper surface of the cover plate (3) is provided with a plurality of first mounting holes (5).

2. The nozzle ring assembly for a turbocharger according to claim 1, characterized in that: A connecting column (6) is sleeved on the inner wall of the first mounting hole (5), and a turbine blade (7) is fixedly connected to the upper surface of the connecting column (6).

3. The nozzle ring assembly for a turbocharger according to claim 2, characterized in that: The bottom of the connecting column (6) is fixedly connected to a rotating connecting rod (8).

4. The nozzle ring assembly for a turbocharger according to claim 1, characterized in that: A plurality of second mounting holes (9) are provided on the upper surface of the rotating disk (2), and the second mounting holes (9) are adapted to the connecting columns (6).

5. The nozzle ring assembly for a turbocharger according to claim 1, characterized in that: The lower surface of the chassis (1) is provided with a plurality of mounting grooves (10), and the mounting grooves (10) are adapted to the rotating connecting rods (8).

6. The nozzle ring assembly for a turbocharger according to claim 1, characterized in that: The lower surface of the rotating disk (2) is provided with a plurality of first threaded fixing holes (11), and the lower surface of the cover plate (3) is provided with a plurality of second threaded fixing holes (12).

7. The nozzle ring assembly for a turbocharger according to claim 6, characterized in that: The first threaded fixing hole (11) is internally threadedly connected to a fixing bolt (13), and the fixing bolt (13) is adapted to the second threaded fixing hole (12).

Images