MIM turbocharging blade

Abstract

The utility model discloses an MIM (metal injection molding) turbocharging blade, which relates to the technical field of turbocharging blades and comprises a connecting seat, a group of blades are fixedly connected to the annular side surface of the connecting seat, two reinforcing ribs are fixedly connected between the group of blades, a group of grooves for turbulent flow are formed in the surface of each reinforcing rib, and a fixing rod is fixedly connected to the lower surface of the connecting seat. A connecting shaft is arranged on the lower surface of the fixing rod, the annular side face of the fixing rod is sleeved with a threaded ring in a threaded mode, the grooves in the surfaces of the blades can disturb airflow, the airflow forms a specific flow state on the surfaces of the blades, and the change of the flow state can increase the turbulence degree of the airflow and promote mixing of boundary layers. When the airflow flows through the blades, the airflow can flow in a mode of being attached to the surfaces of the blades, separation of the airflow on the surfaces of the blades and generation of vortexes are reduced, air resistance is reduced, the aerodynamic efficiency of the blades is improved, and then the turbocharging effect is enhanced.

Description

Technical Field

[0001] This utility model relates to the field of turbocharger blade technology, and in particular to a MIM turbocharger blade. Background Technology

[0002] MIM (Metal Injection Molding) turbocharger blades, as key components of turbocharger systems, play a crucial role in improving engine performance. Turbocharger systems utilize the energy of exhaust gases to drive a turbine, which in turn drives a compressor to compress air, increasing the engine's intake air volume, improving combustion efficiency, and boosting power and torque output. The MIM process allows for the manufacture of complex and precise shapes for turbocharger blades, meeting the stringent requirements of high-performance engines. In practical applications, MIM turbocharger blades typically work in conjunction with the following structures:

[0003] 1. Turbine housing, which protects the turbine blades, guides the flow of exhaust gas, and connects the turbine to the engine exhaust system, must have good high temperature resistance and sealing performance;

[0004] 2. The compressor impeller is connected to the turbine blades via a connecting shaft. Driven by the turbine, it rotates at high speed to compress air. Its design directly affects the boosting effect.

[0005] 3. Bearing system: Supports the rotating shafts of the turbine and compressor, ensuring smooth and low-friction rotation, and withstanding radial and axial loads from high-speed rotation;

[0006] 4. Exhaust gas bypass valve, used to control the amount of exhaust gas entering the turbine, adjust the turbine speed and boost pressure, and ensure stable engine operation under different operating conditions.

[0007] Currently, various technologies and design approaches are being employed in the industry to improve the performance of turbocharger blades. Some manufacturers optimize the aerodynamic shape of the blades, such as by using special curved surface designs and adjusting the number of blades, to improve gas flow efficiency. Other companies are dedicated to developing new materials, such as high-strength, high-temperature resistant alloys, to enhance the reliability of blades under high-temperature and high-pressure environments. In addition, in terms of manufacturing processes, MIM technology is being continuously improved to enhance the forming precision and surface quality of the blades.

[0008] However, the above-described implementation still has the following problems. Regarding blade structural strength, despite the use of new materials, the blades still risk deformation or even breakage under extreme conditions, such as the enormous aerodynamic forces and high-temperature impacts generated during high-load engine operation. This affects the normal operation of the turbocharger system and the reliability of the engine. In terms of aerodynamic performance, traditional blade designs struggle to maintain optimal airflow across the entire operating range, leading to severe airflow separation and significant energy loss under certain conditions, thus reducing turbocharger efficiency. Furthermore, due to the complex and varied operating conditions of the engine, fixed-structure turbocharger blades cannot flexibly adapt to different operating conditions. To address the precise requirements for gas flow and pressure, this application proposes a solution that enhances the structural strength of the blades and improves aerodynamic performance through the design of blade reinforcing ribs and grooves. Simultaneously, the adjustable connecting shaft length allows for flexible blade adjustments based on different engine operating conditions, improving the overall performance and adaptability of the turbocharger system. This MIM turbocharger blade design features a robust structure, effectively reducing the risk of blade damage under extreme conditions. Furthermore, it optimizes gas flow across the entire operating range, improving turbocharger efficiency, and can be precisely adjusted according to the actual needs of the engine, providing more stable and efficient boost support. Utility Model Content

[0009] To address the shortcomings of existing technologies, this invention provides a MIM turbocharger blade that solves the problem that when an engine operates under high load, the blade still faces the risk of deformation or even breakage due to the enormous aerodynamic forces and high-temperature impacts. Traditional blade designs struggle to maintain optimal airflow across all operating conditions, leading to severe airflow separation and significant energy loss under certain conditions.

[0010] To achieve the above objectives, this utility model provides the following technical solution:

[0011] A MIM turbocharger blade includes a connecting seat. A set of blades is fixedly connected to the annular side of the connecting seat. Two reinforcing ribs are fixedly connected between the set of blades. Each reinforcing rib has a set of grooves for turbulence on its surface. A fixing rod is fixedly connected to the lower surface of the connecting seat. A connecting shaft is provided on the lower surface of the fixing rod. A threaded ring is threaded onto the annular side of the fixing rod. Two connecting posts are fixedly connected to the annular side of both the connecting shaft and the threaded ring. Two connecting plates are movably engaged on the surfaces of the two pairs of connecting posts. A nut is threaded onto the annular side of each connecting post. A set of connecting blocks is fixedly connected between the two reinforcing ribs.

[0012] Preferably, the upper surface of the connecting shaft is provided with an annular groove, the annular groove is movably sleeved with the fixed rod, the annular side of the fixed rod is fixedly connected with a limit block, and the inner wall of the annular groove is provided with a slot, which is movably connected with the limit block.

[0013] Preferably, the threaded ring is threadedly connected to the upper end of the connecting shaft, and each connecting post has a washer movably fitted on its annular side.

[0014] Compared with the prior art, the present invention has the following beneficial effects:

[0015] 1. The grooves on the blade surface can disturb the airflow, causing it to form a specific flow pattern on the blade surface. This change in flow pattern can increase the turbulence of the airflow, promote the mixing of the boundary layer, and thus delay the occurrence of airflow separation. When the airflow passes over the blade, it can flow more closely to the blade surface, reducing airflow separation and vortex generation on the blade surface, reducing air resistance, improving the aerodynamic efficiency of the blade, and thus enhancing the turbocharging effect. Turbocharger blades are subjected to the impact of high temperature, high pressure, and high-speed airflow during operation. Two reinforcing ribs are fixedly connected between a set of blades, and a connecting block is also fixedly connected between the two reinforcing ribs to ensure stability. The reinforcing ribs can increase the structural strength and rigidity of the blades, enabling them to better resist these external forces and reduce the risk of deformation and breakage.

[0016] 2. Install the connecting plate and fix it with two pairs of nuts to ensure the connection and fixation of the connecting shaft, threaded ring and fixing rod. Under different working conditions, such as different engine speeds, loads and environmental conditions, the relative position of the blades and airflow can be changed by adjusting the length of the connecting shaft. This allows the blades to better adapt to the actual working conditions, optimize the flow path of gas in the turbine or compressor, reduce airflow turbulence and energy loss, and improve gas compression or expansion efficiency. Attached Figure Description

[0017] The above description is only an overview of the technical solution of this utility model. In order to better understand the technical means of this utility model and to implement it in accordance with the contents of the specification, the preferred embodiments of this utility model are described in detail below with reference to the accompanying drawings.

[0018] Figure 1 This is an overall structural diagram of the present invention;

[0019] Figure 2 This is a structural diagram of the blade of this utility model;

[0020] Figure 3 This is a structural diagram of the fixing rod of this utility model;

[0021] Figure 4 This is a structural diagram of the connecting plate of this utility model.

[0022] Legend: 1. Connecting seat; 2. Blade; 3. Connecting shaft; 4. Threaded ring; 5. Reinforcing rib; 6. Connecting block; 7. Groove; 8. Fixing rod; 9. Limiting block; 10. Slot; 11. Connecting plate; 12. Nut; 13. Washer; 14. Connecting column; 15. Annular groove. Detailed Implementation

[0023] This application provides a MIM turbocharger blade that effectively solves the problem of blade deformation or even breakage under the enormous aerodynamic forces and high-temperature impacts generated during high-load engine operation. Traditional blade designs struggle to maintain optimal airflow across all operating conditions, leading to severe airflow separation and significant energy loss in some situations. By incorporating blade reinforcing ribs and grooves, the structural strength of the blade is enhanced, improving aerodynamic performance. Furthermore, the adjustable connecting shaft length allows for flexible adjustment of the blade according to different engine operating conditions, improving the overall performance and adaptability of the turbocharger system. This MIM turbocharger blade design is structurally robust, effectively reducing the risk of blade damage under extreme conditions. It optimizes gas flow across all operating conditions, improving turbocharger efficiency, and can be precisely adjusted according to the actual needs of the engine, providing more stable and efficient boost support. Example

[0024] like Figure 1 , Figure 2 , Figure 3 and Figure 4 As shown, the technical solution in this application embodiment effectively solves the problem that when an engine operates under high load, the blades still risk deformation or even breakage due to the enormous aerodynamic forces and high-temperature impacts. Traditional blade designs struggle to maintain optimal airflow across all operating conditions, leading to severe airflow separation and significant energy loss under certain conditions. The overall approach is as follows:

[0025] To address the problems existing in the prior art, this utility model provides a MIM turbocharger blade, including a connecting seat 1. A set of blades 2 are fixedly connected to the annular side of the connecting seat 1. Two reinforcing ribs 5 are fixedly connected between the set of blades 2. Each reinforcing rib 5 has a set of grooves 7 for turbulence. A fixing rod 8 is fixedly connected to the lower surface of the connecting seat 1. A connecting shaft 3 is provided on the lower surface of the fixing rod 8. A threaded ring 4 is threaded onto the annular side of the fixing rod 8. Two connecting posts 14 are fixedly connected to the annular sides of the connecting shaft 3 and the threaded ring 4. Two connecting plates 11 are movably engaged on the surfaces of the two pairs of connecting posts 14. A nut 12 is threaded onto the annular side of each connecting post 14. A set of connecting blocks 6 are fixedly connected between the two reinforcing ribs 5. The grooves 7 on the surface of the blades 2 can turbulence the airflow. The disturbance effect causes the airflow to form a specific flow pattern on the surface of blade 2. This change in flow pattern can increase the turbulence of the airflow, promote the mixing of the boundary layer, and thus delay the occurrence of airflow separation. When the airflow flows through blade 2, it can flow more closely to the surface of blade 2, reduce the separation of airflow and the generation of eddies on the surface of blade 2, reduce air resistance, improve the aerodynamic efficiency of blade 2, and thus enhance the turbocharging effect. Turbocharger blade 2 is subjected to the impact of high temperature, high pressure and high speed airflow during operation. Two reinforcing ribs 5 are fixedly connected between a group of blades 2, and a connecting block 6 is also fixedly connected between the two reinforcing ribs 5 to ensure stability. The reinforcing ribs 5 can increase the structural strength and rigidity of blade 2, enabling it to better resist these external forces and reduce the risk of deformation and breakage.

[0026] An annular groove 15 is formed on the upper surface of the connecting shaft 3. The annular groove 15 is movably sleeved with the fixed rod 8. A limit block 9 is fixedly connected to the annular side of the fixed rod 8. A slot 10 is formed on the inner wall of the annular groove 15. The slot 10 is movably connected to the limit block 9. The threaded ring 4 is threadedly sleeved with the upper end of the connecting shaft 3. A washer 13 is movably sleeved on the annular side of each connecting post 14. By rotating the two pairs of nuts 12 with a tool, the fixation between the threaded ring 4 and the connecting shaft 3 is opened. At this time, the threaded ring 4 is rotated upward to disengage it from the connecting shaft 3, thus opening the limit. At this time, the connecting shaft 3 can slide to adjust its length. After adjustment, the length can be adjusted. The threaded ring 4 is rotated downwards to connect with the upper end of the connecting shaft 3. To prevent the threaded ring 4 from being affected by vibration, a connecting plate 11 is installed and connected and fixed by two pairs of nuts 12, thereby ensuring the connection and fixation of the connecting shaft 3, the threaded ring 4 and the fixing rod 8. Under different working conditions, such as different engine speeds, loads and environmental conditions, the relative position of the blade 2 and the airflow can be changed by adjusting the length of the connecting shaft 3, so that the blade 2 can better adapt to the actual working conditions, optimize the flow path of gas in the turbine or compressor, reduce airflow turbulence and energy loss, and improve gas compression or expansion efficiency.

[0027] Among them, the connecting seat 1 is used to connect a group of blades 2, providing a mounting base for the blades 2, so that the blades 2 can be orderly distributed around its annular side, ensuring the relative position of the blades 2 is stable during operation;

[0028] Blade 2 is the core component for turbocharging. It guides the airflow and uses the energy of the airflow to drive the turbine to rotate, which in turn drives the compressor to compress air, thereby increasing the engine's intake air volume and combustion efficiency.

[0029] The connecting shaft 3, in conjunction with the fixed rod 8, can adjust its length, change the relative position of the blade 2 and the airflow, optimize the gas flow path, improve the gas compression or expansion efficiency, and adapt to different working conditions.

[0030] The threaded ring 4 is threadedly connected to the fixing rod 8 and cooperates with the connecting shaft 3. The length of the connecting shaft 3 can be adjusted by rotation. After adjustment, it can also be connected and fixed together with the connecting plate 11 and nut 12.

[0031] The reinforcing rib 5 is connected between a group of blades 2, increasing the structural strength and rigidity of the blades 2, resisting the impact of high temperature, high pressure and high-speed airflow, and reducing the risk of deformation and breakage of the blades 2;

[0032] The connecting block 6 is fixed between the two reinforcing ribs 5, which further enhances the stability of the reinforcing ribs 5, allowing the reinforcing ribs 5 to better play their role in enhancing the structural strength of the blade 2 and ensuring the normal operation of the blade 2;

[0033] The groove 7 is formed on the surface of the reinforcing rib 5, which disturbs the airflow, changes the airflow pattern, increases the turbulence, delays airflow separation, reduces airflow separation and eddies, and improves the aerodynamic efficiency of the blade 2.

[0034] The fixing rod 8, together with the connecting seat 1 and the connecting shaft 3, provides support for the connecting shaft 3. It cooperates with the threaded ring 4, the connecting shaft 3 and other components to realize the length adjustment of the connecting shaft 3 and the overall connection and fixation.

[0035] The limiting block 9 is fixed to the annular side of the fixed rod 8 and is movably connected to the slot 10 on the inner wall of the annular groove 15, which limits the range of motion of the connecting shaft 3 and ensures the safety and stability of the connecting shaft 3 when adjusting its length.

[0036] The slot 10 is formed on the inner wall of the annular groove 15 and is movably connected to the limiting block 9. Together with the limiting block 9, it limits the sliding of the connecting shaft 3 and prevents the connecting shaft 3 from moving excessively.

[0037] The connecting plate 11 is movably snapped onto the connecting post 14 of the connecting shaft 3 and the threaded ring 4, and the connecting shaft 3, the threaded ring 4 and the fixing rod 8 are connected and fixed with the nut 12 to prevent the threaded ring 4 from being affected by vibration.

[0038] Nut 12 is threaded onto connecting post 14. Tightening nut 12 can fix connecting plate 11, thereby ensuring a stable connection between connecting shaft 3, threaded ring 4 and fixing rod 8 and preventing components from loosening.

[0039] The gasket 13 is movably sleeved on the annular side of the connecting post 14, increasing the contact area between the nut 12 and the connecting post 14, dispersing pressure, protecting the surface of the connecting parts, and preventing damage to the parts when the nut 12 is tightened;

[0040] The connecting post 14 is fixed on the annular side of the connecting shaft 3 and the threaded ring 4, providing an installation position for the connecting plate 11, so that the connecting plate 11 can be connected to the connecting shaft 3 and the threaded ring 4, thereby achieving a stable connection between the components.

[0041] An annular groove 15 is formed on the upper surface of the connecting shaft 3, which is movably connected to the fixing rod 8 and cooperates with the limiting block 9 and the slot 10 on the fixing rod 8 to realize the sliding and limiting of the connecting shaft 3, and facilitate the adjustment of the length of the connecting shaft 3.

[0042] Working principle:

[0043] The grooves 7 on the surface of blade 2 can disturb the airflow, causing it to form a specific flow pattern on the blade 2 surface. This change in flow pattern can increase the turbulence of the airflow, promote boundary layer mixing, and thus delay the occurrence of airflow separation. When the airflow passes over blade 2, it can flow more closely to the surface of blade 2, reducing airflow separation and vortex generation on the blade 2 surface, reducing air resistance, improving the aerodynamic efficiency of blade 2, and thus enhancing the turbocharging effect. The turbocharger blade 2 is subjected to the impact of high temperature, high pressure, and high-speed airflow during operation. Two reinforcing ribs 5 are fixedly connected between a set of blades 2, and a connecting block 6 is fixedly connected between the two reinforcing ribs 5 to ensure stability. The reinforcing ribs 5 can increase the structural strength and rigidity of blade 2, enabling it to better resist these external forces and reduce the risk of deformation and breakage. By rotating the two pairs of screws with a tool... The nut 12 opens the fixation between the threaded ring 4 and the connecting shaft 3. At this time, the threaded ring 4 is rotated upward to disengage from the connecting shaft 3, opening the limit switch. The connecting shaft 3 can then slide to adjust its length. After adjustment, the threaded ring 4 is rotated downward to connect with the upper end of the connecting shaft 3. To prevent the threaded ring 4 from being affected by vibration, the connecting plate 11 is installed and fixed by two pairs of nuts 12, thus ensuring the connection and fixation of the connecting shaft 3, the threaded ring 4, and the fixing rod 8. Under different working conditions, such as different engine speeds, loads, and changes in environmental conditions, the relative position of the blade 2 and the airflow can be changed by adjusting the length of the connecting shaft 3, allowing the blade 2 to better adapt to the actual working conditions, optimize the flow path of the gas in the turbine or compressor, reduce airflow turbulence and energy loss, and improve the gas compression or expansion efficiency.

[0044] Finally, it should be noted that the above embodiments are merely examples for clearly illustrating the present invention and are not intended to limit the implementation. Those skilled in the art can make other variations or modifications based on the above description. It is neither necessary nor possible to exhaustively list all possible implementations here. However, obvious variations or modifications derived therefrom are still within the protection scope of this invention.

Claims

1. A MIM turbocharger blade, comprising a connecting seat (1), characterized in that, A set of blades (2) are fixedly connected to the annular side of the connecting seat (1). Two reinforcing ribs (5) are fixedly connected between the set of blades (2). A set of grooves (7) for turbulence are opened on the surface of each reinforcing rib (5). A fixing rod (8) is fixedly connected to the lower surface of the connecting seat (1). A connecting shaft (3) is provided on the lower surface of the fixing rod (8). Among them, the fixed rod (8) has a threaded ring (4) threaded on its annular side, and the connecting shaft (3) and the threaded ring (4) are both fixedly connected to two connecting columns (14). The surfaces of the two pairs of connecting columns (14) are movably engaged with two connecting plates (11), and each connecting column (14) has a nut (12) threaded on its annular side.

2. The MIM turbocharger blade as described in claim 1, characterized in that: A set of connecting blocks (6) are fixedly connected between the two reinforcing ribs (5).

3. The MIM turbocharger blade as described in claim 1, characterized in that: The upper surface of the connecting shaft (3) is provided with an annular groove (15); The annular groove (15) is movably connected to the fixed rod (8).

4. The MIM turbocharger blade as described in claim 3, characterized in that: The fixed rod (8) is fixedly connected to the circumferential side of the limiting block (9); The annular groove (15) has a slot (10) on its inner wall, and the slot (10) is movably connected to the limiting block (9).

5. The MIM turbocharger blade as described in claim 1, characterized in that: The threaded ring (4) is threadedly connected to the upper end of the connecting shaft (3).

6. The MIM turbocharger blade as described in claim 1, characterized in that: Each of the connecting posts (14) has a gasket (13) movably fitted onto its annular side.

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