An active heat-insulated turbocharger integrated bearing system

Abstract

This application discloses an active heat-insulated turbocharger integrated bearing system, relating to the field of turbochargers. The system includes an intermediate housing, a limiting pin, a bearing, and a rotor shaft. An inner bore is formed within the intermediate housing, and the bearing is located within this bore, while the rotor shaft is located within the bearing. The limiting pin is located in a mounting hole, with one end fixed to the bearing sidewall. A radial clearance exists between the sidewall of the limiting pin and the inner wall of the mounting hole, used to transfer dynamic load to the intermediate housing when the bearing undergoes radial displacement, thus improving limiting reliability. The thrust shoulder of the rotor shaft has a heat-insulating annular cavity. After the engine oil enters the heat-insulating annular cavity, it forms a heat-insulating medium layer, preventing heat conduction to the bearing. This application allows engine oil to be directly supplied to the thrust oil film without first flowing through an inner oil film, improving the oil condition on the thrust surface, enhancing the limiting reliability and vortex end bearing capacity of the integrated bearing, and increasing bearing service life.

Description

Technical Field

[0001] This application relates to the technical field of turbochargers, and more specifically, to an active heat-insulated turbocharger integrated bearing system. Background Technology

[0002] Turbocharging utilizes exhaust gases to generate greater power output with the same cylinder capacity. The turbocharger's rotor shaft is supported within an intermediate housing by an integrated bearing that combines the thrust bearing and the floating bearing into a single, compact structure.

[0003] In existing integrated bearing solutions, a hollow locating pin is inserted through the intermediate housing, and the locating pin and the intermediate housing are fixedly connected (e.g., by interference fit). The bearing sidewall has a hole for the locating pin to insert into. During turbocharger operation, there is a clearance between the hole on the bearing and the locating pin. By injecting oil into the hollow locating pin, the oil is divided into two paths: one path directly enters the outer oil film, and the other path sequentially enters the inner oil film and thrust oil film before flowing out, achieving continuous lubrication of the bearing and rotor shaft.

[0004] However, this solution has the following interrelated technical bottlenecks:

[0005] I. Insufficient Reliability of the Positioning Mechanism. The positioning mating surface is located inside the bearing pin hole, and the impact load is directly transmitted to the pin hole wall of the copper alloy bearing through the pin. Copper alloy has low hardness and poor impact resistance. Under long-term high-frequency vibration, the pin hole wall is prone to wear and deformation, leading to an increase in the positioning clearance, a decrease in positioning accuracy, and in severe cases, bearing damage. At the same time, due to the limited bearing wall thickness, the usable mating length is limited, resulting in high contact stress, which further aggravates wear.

[0006] 2. Poor oil condition on the thrust surface. The oil in the thrust oil film must first flow through the inner oil film and be heated by friction before it can reach the thrust surface, resulting in a significant decrease in the viscosity of the oil and a reduction in the load-bearing capacity of the thrust oil film.

[0007] Third, the heat-bearing capacity of the turbine end is limited. The thrust surface is adjacent to the high-temperature turbine, and the viscosity of the engine oil decreases further after heating, reducing the oil film's load-bearing capacity. High temperatures also accelerate oil oxidation and coking, posing a risk of oil passage blockage. This problem, combined with the aforementioned poor oil condition, further deteriorates the working environment of the turbine end thrust surface.

[0008] To address the aforementioned issues, this application proposes an integrated bearing system that combines limit structure optimization, oil supply path reconfiguration, and active heat insulation. Summary of the Invention

[0009] In view of this, the purpose of this application is to provide an active heat-insulated turbocharger integrated bearing system to improve the limiting reliability of the integrated bearing, improve the oil condition of the thrust surface, and enhance the bearing capacity of the turbine end.

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

[0011] An active heat-insulated turbocharger integrated bearing system includes an intermediate housing, a bearing, a limiting pin, and a rotor shaft. The intermediate housing has an interconnected inner bore and a mounting channel. The bearing is located within the inner bore of the intermediate housing, and the rotor shaft is located within the bearing, with both coaxial. The limiting pin is located in the mounting channel, and a portion of its structure is threaded to the side wall of the bearing. A radial clearance exists between the side wall of the limiting pin and the inner wall of the mounting channel.

[0012] An outer oil film is formed between the outer wall of the bearing and the cavity wall of the inner hole of the intermediate shell, an inner oil film is formed between the inner wall of the bearing and the rotor shaft, and a thrust oil film is formed between the two end faces of the bearing and the adjacent components; a thrust shoulder is coaxially fixedly connected to the end of the rotor shaft near the turbine, and the thrust oil film at the end of the bearing near the turbine is located between the end face of the bearing and the thrust shoulder.

[0013] The intermediate housing and the bearing are provided with an assembly oil passage, through which machine oil is introduced into the inner hole of the intermediate housing and the bearing. The port of the assembly oil passage between the inner wall of the bearing and the rotor shaft is located in the axial direction of the rotor shaft between the inner oil film and the thrust oil film.

[0014] The thrust shoulder includes a main body and a heat insulation ring body that are coaxially and fixedly connected to each other. The heat insulation ring body is located between the main body and the bearing. A heat insulation ring cavity is formed between the heat insulation ring body and the main body. The heat insulation ring cavity is connected to the oil passage of the assembly.

[0015] Preferably, the thrust shoulder is provided with a plurality of centrifugal oil-throwing holes, one end of which is connected to the heat insulation ring cavity, and the other end is located on the outer wall of the thrust shoulder and faces the inner wall of the intermediate housing. The plurality of centrifugal oil-throwing holes are arranged in a circumferential array along the thrust shoulder.

[0016] Preferably, the intermediate housing has an interconnected oil drain space and an oil return ring cavity, the oil return ring cavity is coaxial with the bearing, the centrifugal oil throwing hole is located in the oil return ring cavity at the opening of the hole on the outer wall of the thrust shoulder, and the length direction of the centrifugal oil throwing hole is inclined relative to the axial direction of the rotor shaft.

[0017] Preferably, the assembly oil passage includes a first oil passage and a second oil passage. The first oil passage is opened in the intermediate housing and one end of the first oil passage is connected to the inner hole of the intermediate housing. The second oil passage is opened in the bearing and penetrates the wall thickness of the bearing. The end of the second oil passage located on the outer wall of the bearing is directly opposite the port of the first oil passage.

[0018] Preferably, one end of the bearing is a vortex end and the other end is a pressure end, with the turbine located at the vortex end and the booster impeller located at the pressure end; multiple first and second oil passages are provided, with some of the first and second oil passages used to supply oil to the pressure end and others used to supply oil to the vortex end; the end of the first oil passage away from the second oil passage is connected to the mounting hole; the length direction of both the first and second oil passages is inclined relative to the radial direction of the bearing; the end of the second oil passage away from the first oil passage is located at the vortex end or the pressure end.

[0019] Preferably, the inner wall of the bearing end face is provided with an oil guide ring groove, the oil guide ring groove is located between the inner oil film and the thrust oil film, and the oil guide ring groove is directly connected to the second oil passage.

[0020] Preferably, the limiting pin has a diversion channel, which includes an oil inlet and multiple oil outlets that are interconnected. The oil inlet is located at the end of the limiting pin away from the bearing, and the multiple oil inlets are located on the side wall of the limiting pin. All the ends of the first oil passages away from the second oil passages are connected to the oil outlets.

[0021] Preferably, there are two first oil passages, one of which corresponds to the vortex end and the other corresponds to the pressure end. Multiple second oil passages are provided for each of the pressure end or the vortex end. The outer wall of the bearing is provided with a bearing outer ring groove, which is located at the port of the first oil passage. One end of the multiple second oil passages away from the axis of the bearing is located in the bearing outer ring groove.

[0022] Preferably, the intermediate housing is further provided with an oil discharge channel, which is located on the side of the bearing away from the limiting pin. The oil discharge channel connects the inner hole of the intermediate housing and the oil drain space. The bearing is provided with an oil passage hole that penetrates its own wall thickness. The oil passage hole and the oil discharge channel are coaxially aligned.

[0023] Preferably, the bearing sidewall has a threaded hole, one end of the limiting pin is coaxially inserted into the threaded hole and threadedly connected to the bearing, and the end face of the limiting pin away from the bearing is provided with a torque structure.

[0024] The active heat-insulated turbocharger integrated bearing system provided in this application has at least the following advantages compared to related technologies:

[0025] First, the reliability of the limit pin is improved. By fixing the limit pin to the bearing and setting a radial clearance between the limit pin and the mounting hole, the dynamic load caused by vibration is transferred to the space between the limit pin and the intermediate housing, avoiding the thin-walled bearing from directly bearing the alternating load and reducing the risk of bearing wear. Moreover, since the intermediate housing is larger, the mounting hole can be set to a longer distance, making the contact area between the limit pin and the intermediate housing larger and reducing the impact force generated when the limit pin is engaged.

[0026] Second, the oil condition on the thrust surface is improved. In related technologies, the engine oil must first flow through the inner oil film and be heated by friction before reaching the thrust oil film. This application, by setting the port of the assembly oil passage between the inner oil film and the thrust oil film, allows the low-temperature engine oil to be directly supplied to the thrust oil film without having to flow through the inner oil film first, thereby maintaining a higher viscosity and improving the load-bearing capacity of the thrust oil film.

[0027] Third, the turbine end bearing capacity is enhanced. By setting a heat insulation ring cavity inside the thrust shoulder, the oil enters and forms a heat insulation medium layer, effectively blocking the conduction of turbine heat to the bearing and maintaining the viscosity and bearing capacity of the thrust oil film; at the same time, the centrifugal oil slinger hole enables the continuous renewal of the oil in the heat insulation ring cavity, ensuring the durability of the heat insulation effect. Attached Figure Description

[0028] To more clearly illustrate the technical solutions in the embodiments of this application or related technologies, the drawings used in the description of the embodiments or related technologies will be briefly introduced below. Obviously, the drawings described below are only embodiments of this application. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0029] Figure 1 This is a schematic diagram illustrating the overall structure of the integrated bearing system for the active heat-insulated turbocharger in this application embodiment;

[0030] Figure 2 for Figure 1 Enlarged view of part A in the middle;

[0031] Figure 3 This is a schematic diagram illustrating the structure of the limiting pin in the embodiments of this application;

[0032] Figure 4 This is a half-sectional schematic diagram illustrating the structure of the bearing in the embodiments of this application;

[0033] Figure 5 This is a schematic diagram illustrating the structure of the rotor shaft at the vortex end of the bearing in an embodiment of this application.

[0034] Figures 1-5 In the accompanying drawings, the reference numerals include:

[0035] 1. Intermediate shell; 11. Mounting channel; 12. Transition channel; 13. Inner hole of intermediate shell; 14. Oil drain space; 15. Oil return ring cavity; 16. Oil unloading channel; 17. First oil passage; 2. Bearing; 21. Second oil passage; 22. Bearing outer ring groove; 23. Oil passage hole; 24. Oil guide ring groove; 25. Inner oil film; 26. Outer oil film; 27. Thrust oil film; 3. Limiting pin; 31. Diverting channel; 32. Torque structure; 4. Rotor shaft; 41. Thrust shoulder; 411. Main body; 412. Heat insulation ring body; 42. Heat insulation ring cavity; 43. Centrifugal oil throwing hole; 44. Sealing ring; 5. Turbine; 6. Booster impeller. Detailed Implementation

[0036] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0037] Unless otherwise defined, the technical or scientific terms used in this application shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms "first," "second," and similar words used in this application do not indicate any order, quantity, or importance. Terms such as "connection" or "linked" are not limited to physical or mechanical connections, but can include electrical connections, whether direct or indirect. Terms such as "upper," "lower," "left," and "right" are used only to indicate relative positional relationships; when the absolute position of the described object changes, the relative positional relationship may also change accordingly. An embodiment of this application discloses an active thermal insulation turbocharger integrated bearing system.

[0038] The core of this application is to provide an active heat-insulated turbocharger integrated bearing system.

[0039] Please refer to Figure 1 and Figure 2 .

[0040] The active heat-insulated turbocharger integrated bearing system provided in this application includes an intermediate housing 1, a bearing 2 and a rotor shaft 4. An intermediate housing inner hole 13 is provided in the intermediate housing 1. The intermediate housing inner hole 13 is a cylindrical space. The bearing 2 is coaxially located in the intermediate housing inner hole 13. The rotor shaft 4 is located in the bearing 2 and the two are coaxial.

[0041] A limiting pin 3 is provided through the intermediate housing 1. The intermediate housing 1 has a mounting channel 11 along the radial direction of the inner hole 13 of the intermediate housing for the limiting pin 3 to pass through. One end of the mounting channel 11 is connected to the inner hole 13 of the intermediate housing, and the other end is located on the outer surface of the intermediate housing 1. One end of the limiting pin 3 extends into the inner hole 13 of the intermediate housing and is fixed relative to the bearing 2. A radial clearance is formed between the side wall of the limiting pin 3 and the inner wall of the mounting channel 11.

[0042] In the specific implementation process, the bearing 2 and the limiting pin 3 can be interference-fitted with each other, or the two can be detachably connected. In this embodiment, a threaded hole is opened on the middle side wall of the bearing 2. The axis of the threaded hole is the radial direction of the bearing 2. One end of the limiting pin 3 is coaxially inserted into the threaded hole and threadedly connected to the bearing 2. After the limiting pin 3 is tightened, the bearing 2 and the limiting pin 3 are relatively fixed, and the threaded hole of the bearing 2 is completely sealed without leaving any gaps.

[0043] During the rotation of the rotor shaft 4, the bearing 2 vibrates slightly between itself and the intermediate housing 1 due to the force. During the vibration, since the limiting pin 3 and the bearing 2 are fixed together, there is basically no change in their relative positions. However, the limiting pin 3 and the intermediate housing 1 are not completely fastened, so the side wall of the limiting pin 3 will continuously contact and rub against the inner wall of the mounting hole 11. Thus, the limiting dynamic load of the bearing 2 is located between the intermediate housing 1 and the limiting pin 3, reducing the impact of contact limiting on the bearing 2.

[0044] Meanwhile, since the intermediate housing 1 is relatively large, the length of the mounting hole 11 can be set to a longer distance, which makes the contact area between the side wall of the limiting pin 3 and the intermediate housing 1 larger, which can reduce the impact force generated when the two contact and limit each other, thereby reducing the degree of stress damage to both.

[0045] To facilitate the identification of the bearing 2's orientation, one end of the bearing 2 is the scroll end, and the other end is the pressure end. The turbine 5 is located at the scroll end, and the booster impeller 6 is located at the pressure end. Both the turbine 5 and the booster impeller 6 are coaxial with the bearing 2. Two external oil films 26 are formed between the outer wall of the bearing 2 and the cavity wall of the inner bore 13 of the intermediate shell, and two internal oil films 25 are formed between the inner wall of the bearing 2 and the rotor shaft 4. The two external oil films 26 and the two internal oil films 25 are located at both ends of the bearing 2's length direction, i.e., near the scroll end and near the pressure end, respectively. Between the two internal oil films 25 and the two external oil films 26, relatively wide oil chambers are formed on the inner and outer sides of the middle part of the bearing 2, respectively.

[0046] A thrust oil film 27 is formed between the two end faces of the bearing 2 and the adjacent components. When the turbine 5 rotates, the rotor shaft 4 is subjected to axial thrust. A thrust shoulder 41 is coaxially fixedly connected to the end of the rotor shaft 4 near the turbine 5. The thrust oil film 27 of the bearing 2 near the turbine 5 is located between the end face of the bearing 2 and the thrust shoulder 41. An end plate is provided at the pressure end of the bearing 2 in the intermediate housing 1. The thrust oil film 27 at the pressure end of the bearing 2 is located between the bearing 2 and the end plate. The thrust oil film 27 has the function of bearing the axial force of the bearing 2.

[0047] The intermediate housing 1 and the bearing 2 are provided with assembly oil passages. Through the assembly oil passages, oil can be introduced from the outside into the inner hole 13 of the intermediate housing and into the bearing 2, and oil is supplied to each inner oil film 25, outer oil film 26 and thrust oil film 27 to lubricate the wall between the bearing 2 and the inner hole 13 of the intermediate housing, as well as the wall between the inner wall of the bearing 2 and the rotor shaft 4.

[0048] The port of the assembly oil passage between the inner wall of the bearing 2 and the rotor shaft 4 is located between the inner oil film 25 and the thrust oil film 27. That is, the oil in the inner oil film 25 and the thrust oil film 27 is directly supplied by the assembly oil passage. It is a low-temperature oil that hardly undergoes friction before entering the oil film. It directly cools the two oil films, which can effectively remove frictional heat and reduce the risk of oil coking.

[0049] Based on this, the thrust shoulder 41 includes a main body 411 and a heat insulation ring 412 that are coaxially and fixedly connected to each other. The heat insulation ring 412 is located between the main body 411 and the bearing 2, and the main body 411 and the heat insulation ring 412 can be integrally formed. The main body 411 is directly connected to the rotor shaft 4, and a plurality of sealing rings 44 are embedded in the side wall of the main body 411. The sealing rings 44 abut against the cavity wall of the inner hole 13 of the intermediate shell, thereby preventing the oil in the inner hole 13 of the intermediate shell from leaking out to the turbine 5 side.

[0050] The heat insulation ring 412 is annular, and there is a gap between its inner edge sidewall and the sidewall of the rotor shaft 4; and a heat insulation ring cavity 42 is formed between the heat insulation ring 412 and the main body 411, and the oil inside the bearing 2 can enter the heat insulation ring cavity 42 through the gap between the heat insulation ring 412 and the rotor shaft 4.

[0051] After the heat insulation ring cavity 42 is filled with oil, a heat insulation layer is formed, which reduces the heat transfer efficiency between the main body 411 and the heat insulation ring 412, reduces the heating of the thrust oil film 27 at the vortex end, increases the viscosity of the thrust oil film 27 at the vortex end, and thus improves the load-bearing capacity of the thrust oil film 27.

[0052] In one specific embodiment, to facilitate the forming of the heat insulation annular cavity 42, the rotor shaft 4 is an assembly that can be fixed by processes such as insertion and welding of a round rod and a sleeve, which will not be elaborated here. In this embodiment, the turbine 5 and the thrust shoulder 41 are integrally formed.

[0053] The active heat-insulated turbocharger integrated bearing system provided in this application will be described in more detail below with reference to the accompanying drawings and specific embodiments.

[0054] Based on the above embodiments, refer to Figure 2 and Figure 5 .

[0055] Specifically, the thrust shoulder 41 has multiple centrifugal oil-throwing holes 43. One end of each centrifugal oil-throwing hole 43 is connected to the heat insulation ring cavity 42, and the other end is located on the outer wall of the thrust shoulder 41 with the opening facing the inner wall of the intermediate housing 1. Thus, the centrifugal oil-throwing hole 43 connects the heat insulation ring cavity 42 and the outer side of the thrust shoulder 41. During the rotation of the rotor shaft 4, under centrifugal force, the oil in the heat insulation ring cavity 42 can be discharged through the centrifugal oil-throwing holes 43 and reach the outer side of the thrust shoulder 41. This ensures that new oil can continuously enter the heat insulation ring cavity 42, guaranteeing the durability of the heat insulation effect.

[0056] Multiple centrifugal oil-throwing holes 43 are arranged in a circumferential array along the thrust shoulder 41, so that the arrangement of the centrifugal oil-throwing holes 43 does not affect the rotational balance of the thrust shoulder 41.

[0057] Based on the above embodiments, refer to Figure 2 and Figure 5 .

[0058] Specifically, the intermediate housing 1 has an interconnected oil drain space 14 and an oil return annular cavity 15. The oil drain space 14 is connected to the outside of the intermediate housing 1, and the connection point is located on the side of the inner hole 13 of the intermediate housing away from the mounting hole 11. The space of the oil return annular cavity 15 is annular and coaxial with the bearing 2. The outer edge of the thrust oil film 27 at the volute end of the bearing 2 is located inside the oil return annular cavity 15. That is, the oil flowing from the inside of the bearing 2 through the thrust oil film 27 at the volute end to the outside of the bearing 2 can directly enter the oil return annular cavity 15 for discharge without interfering with or mixing with the external oil film 26.

[0059] Based on the above embodiments, refer to Figure 2 and Figure 5 .

[0060] The end of the centrifugal oil-throwing hole 43 that is away from the heat insulation ring cavity 42 is directly opposite the oil return ring cavity 15, that is, the oil thrown out by the centrifugal oil-throwing hole 43 directly enters the oil return ring cavity 15.

[0061] The cavity wall of the return oil ring cavity 15 is also the inner wall of the intermediate housing 1. The length direction of the centrifugal oil throwing hole 43 is inclined relative to the axial direction of the rotor shaft 4. Specifically, the end of the centrifugal oil throwing hole 43 away from the heat insulation ring cavity 42 is inclined in the direction away from the turbine 5, so the oil discharged from the centrifugal oil throwing hole 43 has a tendency to flow away from the turbine 5; when this part of the oil is thrown to the cavity wall of the return oil ring cavity 15 near the bearing 2, and this place is close to the outer oil film 26 at the vortex end, it can play a certain cooling effect on the inner wall surface of the intermediate housing 1 at this place and the outer oil film 26 near this place.

[0062] Similarly, if the end of the centrifugal oil throwing hole 43 away from the heat insulation ring cavity 42 is tilted towards the direction closer to the turbine 5, the thrown oil falls onto the cavity wall of the return oil ring cavity 15 near the turbine 5, thereby cooling the inner wall surface of the intermediate housing 1 at this point.

[0063] Based on any of the above embodiments, refer to Figures 1-4 .

[0064] Specifically, the assembly oil passage includes a first oil passage 17 and a second oil passage 21. The first oil passage 17 is located in the intermediate housing 1, and one end of the first oil passage 17 is connected to the inner hole 13 of the intermediate housing, allowing engine oil to reach the outer oil film 26 through the first oil passage 17. The second oil passage 21 is located in the bearing 2 and extends through the wall thickness of the bearing 2. One end of the second oil passage 21 is located on the outer wall of the bearing 2, directly opposite the port of the first oil passage 17. Engine oil can flow directly into the second oil passage 21 after exiting the first oil passage 17, and then reach the inner side of the bearing 2 through the second oil passage 21.

[0065] As a result, the oil can directly enter the outer and inner sides of the bearing 2, and most of the oil entering the inner side of the bearing 2 does not pass through the outer side of the bearing 2. The oil passages on the inner and outer walls of the bearing 2 are smoother and the response is faster.

[0066] Based on the above embodiments, refer to Figure 1 and Figure 2 .

[0067] Specifically, multiple first oil passages 17 and second oil passages 21 are provided. Some of the first oil passages 17 and second oil passages 21 are used to supply oil to the pressure end, while others are used to supply oil to the vortex end. The end of each first oil passage 17 away from the second oil passage 21 is connected to the mounting hole 11. The engine oil enters the intermediate housing 1 through the mounting hole 11, and then enters the inner hole 13 of the intermediate housing through the first oil passages 17 and the second oil passages 21.

[0068] The length direction of both the first oil passage 17 and the second oil passage 21 is inclined relative to the radial direction of the bearing 2. Along the direction of oil flow, the first oil passage 17 and the second oil passage 21 tend to gradually move away from the axis of the limiting pin 3. Oil guide ring grooves 24 are formed on the inner wall of the bearing 2 near the pressure end and the scroll end. The edge of the oil guide ring groove 24 is directly on the end face of the bearing 2. The end of the second oil passage 21 away from the first oil passage 17 is located at the bottom of the oil guide ring groove 24. Therefore, the end of each second oil passage 21 away from the first oil passage 17 is located at the scroll end or the pressure end. This means that the oil reaching the scroll end and pressure end face of the bearing 2 has not been squeezed and rubbed by the inner oil film 25 or the outer oil film 26, resulting in a relatively low temperature and maintaining a high viscosity, thus improving the load-bearing capacity of the pressure end and the scroll end of the bearing 2.

[0069] Based on the above embodiments, refer to Figures 2-4 .

[0070] Specifically, the limiting pin 3 has a diversion channel 31, which includes an oil inlet and multiple oil outlets that are interconnected. The diversion channel 31 is T-shaped, with two oil outlets located on opposite side walls of the limiting pin 3, and the oil inlet located at the end of the limiting pin 3 away from the bearing 2.

[0071] The side wall of the limiting pin 3 is coaxially provided with an annular groove, and the two oil outlet holes are located at the bottom of the annular groove. In this embodiment, there are two first oil passages 17, and a transition channel 12 is also provided on the intermediate housing 1. The length direction of the transition channel 12 is parallel to the axis of the bearing 2. The mounting channel 11 is located in the middle of the transition channel 12. The ends of the two first oil passages 17 away from the second oil passage 21 are connected through the transition channel 12 and the mounting channel 11, respectively. When the limiting pin 3 is located in the mounting channel 11, the annular groove on the side wall of the limiting pin 3 is connected to the transition channel 12, and the two oil outlet holes are coaxially opposite the transition channel 12.

[0072] As the oil flows from the distribution channel 31 into the transition channel 12, the annular groove of the limiting pin 3 makes the space at the connection between the two wider, and the solid structure has less impact on the oil pressure.

[0073] One of the first oil passages 17 corresponds to the vortex end, and the other first oil passage 17 corresponds to the pressure end. Multiple second oil passages 21 are provided for each pressure end or vortex end. In this embodiment, there are four second oil passages 21 for each pressure end and vortex end. The four second oil passages 21 are arranged in a circumferential array around the bearing 2.

[0074] Two bearing outer ring grooves 22 are coaxially formed on the outer wall of the bearing 2. The bearing outer ring grooves 22 are located at the port of the first oil passage 17 and in the middle of the outer oil film 26. The ends of the four second oil passages 21 at the same end of the bearing 2 that are away from the axis of the bearing 2 are located in the bearing outer ring grooves 22.

[0075] Thus, the engine oil first flows from the first oil passage 17 into the bearing outer ring groove 22, and then enters the four second oil passages 21 relatively evenly through the bearing outer ring groove 22. From there, it flows evenly from multiple directions through the four second oil passages 21 to the oil guide ring grooves 24 at the pressure end or scroll end of the bearing 2, and to the end face of the bearing 2, improving the circumferential uniformity of the oil entering the inner oil film 25 relative to the bearing 2. When the engine oil flows through the bearing outer ring groove 22 and the oil guide ring grooves 24, it can create a relatively stable oil pressure within the grooves. This allows it to fill the space between the outer wall of the bearing 2 and the inner wall of the intermediate housing bore 13 through the bearing outer ring groove 22, forming a more stable outer oil film 26. It also fills the space between the inner wall of the bearing 2 and the side wall of the rotor shaft 4 through the oil guide ring grooves 24, forming a more stable inner oil film 25.

[0076] It can be seen that the outer oil film 26, the inner oil film 25 and the thrust oil film 27 are all directly supplied with oil through the assembly oil passage. The oil supplied to each oil film is a low-temperature oil that has not undergone friction, which makes the oil in the three oil films have high viscosity and high mechanical properties.

[0077] In some related technologies, the diversion channel 31 of the limiting pin 3 is directly connected to the inner side of the bearing 2, that is, the oil first enters the middle of the bearing 2 and then diverts to both ends to the inner oil film 25. At this time, the oil that reaches the inner oil film 25 has passed through the friction between the inner wall of the middle part of the bearing 2 and the rotor shaft 4, and the temperature rises, which causes the bearing capacity of the inner oil film 25 to decrease.

[0078] In this application, because the diversion channel 31 is set so that the oil is diverted before entering the inner hole 13 of the intermediate shell and directly reaches the vortex end and pressure end through the assembly oil passage, the inner oil film 25, the outer oil film 26 and the thrust oil film 27 are all direct oil supply, and the mechanical properties of the three are higher than those of the above-mentioned related technologies.

[0079] Meanwhile, since the limiting pin 3 and the bearing 2 are fixedly connected, the hole in the middle of the bearing 2 through which the limiting pin 3 passes and which connects the inner and outer sides of the bearing 2 is blocked, leaving no gap. As a result, the oil outside the bearing 2 cannot enter the inner side of the bearing 2 in the middle of the bearing 2. The oil inside the bearing 2 can only be discharged in one direction through the oil passage 23 and the oil discharge channel. This also avoids the negative impact of the oil in the middle of the bearing 2 being rubbed on the inner oil film 25.

[0080] Based on the above embodiments, refer to Figure 2 .

[0081] Specifically, the intermediate housing 1 is also provided with an oil discharge channel 16. The oil discharge channel 16 is located on the side of the bearing 2 away from the limiting pin 3. The oil discharge channel 16 connects the inner hole 13 of the intermediate housing and the oil drain space 14. The bearing 2 is provided with an oil passage hole 23 that penetrates its own wall thickness. The oil passage hole 23 is located on the side of the bearing 2 away from the limiting pin 3, and the oil passage hole 23 and the oil discharge channel 16 are coaxially aligned. The oil inside the middle part of the bearing 2 can flow directly into the oil discharge channel 16 through the oil passage hole 23 and finally enter the oil drain space 14.

[0082] Therefore, the oil flowing out from the inner side of the middle of the bearing 2 is basically directly discharged into the oil drain space 14, and does not affect the oil in the space outside the bearing 2.

[0083] At this point, the complete oil circuit has been established: the oil enters the diversion channel 31 of the limiting pin 3 from the mounting hole 11 of the intermediate housing 1, and then enters the inner hole 13 of the intermediate housing through the two first oil passages 17. On the outside of the bearing 2, one oil path flows to the outer oil film 26 near the pressure end and the pressure end face of the bearing 2, and the other oil path flows to the outer oil film 26 near the scroll end and the scroll end face of the bearing 2. Two portions of oil enter the inner oil guide ring groove 24 of the bearing 2 from both ends through the second oil passage. One portion of the oil flows to the inner oil film 25 near the pressure end and the pressure end face of the bearing 2, while the other portion flows to the inner oil film 25 near the scroll end, the scroll end face of the bearing 2, and the heat insulation ring cavity 42. Finally, the oil near the pressure end of the bearing 2 directly enters the oil drain space 14, and the oil near the scroll end of the bearing 2 flows into the oil drain space 14 through the return oil ring cavity 15. The oil that passes through the inner and outer oil films 26 and moves near the middle of the bearing 2 enters the oil drain space 14 through the oil discharge channel 16. The oil in the oil drain space 14 is finally discharged from the intermediate housing 1.

[0084] The above-mentioned oil circuit has the advantages of parallel oil supply, independent lubrication points, rapid and controllable oil supply, and can also reduce the temperature of the inner and outer oil films 26 of the bearing 2, thereby reducing the risk of high-temperature sintering and carbon buildup in the oil circuit.

[0085] Based on any of the above embodiments, refer to Figure 2 and Figure 4 .

[0086] Specifically, based on the threaded connection between the limiting pin 3 and the bearing 2, a torque structure 32 is provided on the end face of the limiting pin 3 away from the bearing 2. The torque structure 32 provides a force point for loosening the limiting pin 3 relative to the bearing 2. In this embodiment, the torque structure 32 is a torque groove, and there are four torque grooves on the end face of the limiting pin 3 away from the bearing 2. The four torque grooves are arranged in a circumferential array along the limiting pin 3, and the length direction of each torque groove is radial to the limiting pin 3. By inserting a special torque tool into the torque groove and rotating it, the limiting pin 3 can be rotated, which facilitates the disassembly and maintenance of the limiting pin 3.

[0087] The intermediate shell 1 is made of high-strength cast iron, and the limiting pin 3 is made of alloy steel with a nitrided hardened layer on the surface, which improves the impact resistance of the structure at the stress point.

[0088] The various embodiments in this specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

[0089] The above provides a detailed description of an active heat-insulated turbocharger integrated bearing system provided in this application. Specific examples have been used to illustrate the principles and implementation methods of this application. The descriptions of the embodiments above are merely for the purpose of helping to understand the method and core ideas of this application. It should be noted that those skilled in the art can make various improvements and modifications to this application without departing from its principles, and these improvements and modifications also fall within the protection scope of this application.

Claims

1. An active heat-insulated turbocharger integrated bearing system, characterized in that, The system includes an intermediate housing (1), a bearing (2), a limiting pin (3), and a rotor shaft (4). The intermediate housing (1) has an interconnected intermediate housing inner hole (13) and a mounting channel (11). The bearing (2) is located inside the intermediate housing inner hole (13), and the rotor shaft (4) is located inside the bearing (2) and the two are coaxial. The limiting pin (3) is located in the mounting channel (11), and part of its structure is threaded to the side wall of the bearing (2). There is a radial clearance between the side wall of the limiting pin (3) and the inner wall of the mounting channel (11). An outer oil film (26) is formed between the outer wall of the bearing (2) and the cavity wall of the inner hole (13) of the intermediate shell, an inner oil film (25) is formed between the inner wall of the bearing (2) and the rotor shaft (4), and a thrust oil film (27) is formed between the two end faces of the bearing (2) and the adjacent components; a thrust shoulder (41) is coaxially fixedly connected to one end of the rotor shaft (4) near the turbine (5), and the thrust oil film (27) of the bearing (2) near the turbine (5) is located between the end face of the bearing (2) and the thrust shoulder; The intermediate housing (1) and the bearing (2) are provided with an assembly oil passage, through which oil is supplied to the inner hole (13) of the intermediate housing and the bearing (2). The port of the assembly oil passage between the inner wall of the bearing (2) and the rotor shaft (4) is located in the axial direction of the rotor shaft (4) between the inner oil film (25) and the thrust oil film (27). The thrust shoulder (41) includes a main body (411) and a heat insulation ring (412) that are coaxially and fixedly connected to each other. The heat insulation ring (412) is located between the main body (411) and the bearing (2). A heat insulation ring cavity (42) is formed between the heat insulation ring (412) and the main body (411). The heat insulation ring cavity (42) is connected to the oil passage of the assembly.

2. The active heat-insulated turbocharger integrated bearing system according to claim 1, characterized in that, The thrust shoulder (41) is provided with a plurality of centrifugal oil-throwing holes (43). One end of the centrifugal oil-throwing hole (43) is connected to the heat insulation ring cavity (42), and the other end is located on the outer wall of the thrust shoulder (41) and faces the inner wall of the intermediate housing (1). The plurality of centrifugal oil-throwing holes (43) are arranged in a circumferential array along the thrust shoulder (41).

3. The active heat-insulated turbocharger integrated bearing system according to claim 2, characterized in that, The intermediate housing (1) has an interconnected oil drain space (14) and an oil return ring cavity (15). The oil return ring cavity (15) and the bearing (2) are coaxial. The centrifugal oil throwing hole (43) is located in the oil return ring cavity (15) at the opening of the outer wall of the thrust shoulder (41). The length direction of the centrifugal oil throwing hole (43) is inclined relative to the axial direction of the rotor shaft (4).

4. The active thermal insulation turbocharger integrated bearing system according to any one of claims 1-3, characterized in that, The assembly oil passage includes a first oil passage (17) and a second oil passage (21). The first oil passage (17) is opened in the intermediate housing (1). One end of the first oil passage (17) is connected to the inner hole (13) of the intermediate housing. The second oil passage (21) is opened in the bearing (2) and extends through the wall thickness of the bearing. One end of the second oil passage (21) located on the outer wall of the bearing (2) is directly opposite the port of the first oil passage (17).

5. The active heat-insulated turbocharger integrated bearing system according to claim 4, characterized in that, One end of the bearing (2) is the vortex end and the other end is the pressure end. The turbine (5) is located at the vortex end and the booster impeller (6) is located at the pressure end. Multiple first oil passages (17) and second oil passages (21) are provided. Part of the first oil passages (17) and second oil passages (21) are used to supply oil to the pressure end, and another part of the first oil passages (17) and second oil passages (21) are used to supply oil to the vortex end. The end of the first oil passage (17) away from the second oil passage (21) is connected to the mounting hole (11). The length direction of the first oil passage (17) and the second oil passage (21) is inclined relative to the radial direction of the bearing (2). The end of the second oil passage (21) away from the first oil passage (17) is located at the vortex end or the pressure end.

6. The active thermal insulation turbocharger integrated bearing system according to claim 5, characterized in that, The inner wall of the bearing (2) at the end face is provided with an oil guide ring groove (24), which is located between the inner oil film (25) and the thrust oil film (27). The oil guide ring groove (24) is directly connected to the second oil passage (21).

7. The active thermal insulation turbocharger integrated bearing system according to claim 6, characterized in that, The limiting pin (3) has a diversion channel (31), which includes an oil inlet and multiple oil outlets that are interconnected. The oil inlet is located at the end of the limiting pin (3) away from the bearing (2), and the multiple oil inlets are located on the side wall of the limiting pin (3). All the ends of the first oil passages (17) away from the second oil passages (21) are connected to the oil outlets.

8. The active thermal insulation turbocharger integrated bearing system according to claim 7, characterized in that, There are two first oil passages (17), one of which corresponds to the vortex end and the other corresponds to the pressure end. Multiple second oil passages (21) corresponding to the pressure end or the vortex end are provided. The outer wall of the bearing (2) is provided with a bearing outer ring groove (22). The bearing outer ring groove (22) is located at the port of the first oil passage (17). One end of the multiple second oil passages (21) away from the axis of the bearing (2) is located in the bearing outer ring groove (22).

9. The active thermal insulation turbocharger integrated bearing system according to claim 8, characterized in that, The intermediate housing (1) is also provided with an oil discharge channel (16), which is located on the side of the bearing (2) away from the limiting pin (3). The oil discharge channel (16) connects the inner hole (13) of the intermediate housing and the oil drain space (14). The bearing (2) is provided with an oil passage hole (23) that penetrates its own wall thickness. The oil passage hole (23) and the oil discharge channel (16) are coaxially aligned.

10. The active thermal insulation turbocharger integrated bearing system according to any one of claims 1-3, characterized in that, The bearing (2) has a threaded hole on its side wall. One end of the limiting pin (3) is coaxially inserted into the threaded hole and threadedly connected to the bearing (2). The end face of the limiting pin (3) away from the bearing (2) is provided with a torque structure (32).

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