Turbocharger unit

Abstract

This invention relates to the field of internal combustion engine turbocharger technology, including a bearing housing, an oil supply line, and an integrated bearing. The integrated bearing comprises a pressure-end integrated bearing and a scroll-end integrated bearing arranged parallel along the axial direction. The bearing housing includes an inner wall surface of a bearing seat, within which a support sleeve is rotatably mounted. The pressure-end integrated bearing and the scroll-end integrated bearing are located on opposite sides of the support sleeve. The pressure-end integrated bearing and the scroll-end integrated bearing are radially connected by an oil supply pin 1 and an oil supply pin 2, which communicate with their internal cavities and are fixed to the bearing housing. This invention addresses the contradictions inherent in traditional split bearing systems, which, while avoiding high-temperature effects, suffer from high oil consumption, insufficient internal oil film lubrication, and high cost. While integrated bearing systems achieve low cost and structural simplification, they exhibit significant shortcomings in critical areas such as sufficient internal oil film lubrication, high-temperature reliability of the thrust surface, and compressor-side oil control capabilities.

Description

Technical Field

[0001] This invention relates to the field of internal combustion engine supercharging technology, and more specifically to turbocharger devices. Background Technology

[0002] As a crucial component for improving engine power density and fuel economy, the performance and reliability of turbochargers directly impact the overall engine's power output and durability. With modern engine technology advancing towards higher power-to-weight ratios, higher efficiency, and higher reliability, the operating environment of turbochargers is becoming increasingly demanding. Specifically, to achieve higher efficiency, turbine inlet temperature is significantly increased, while power losses in accessories (including the oil pump) are drastically reduced. To accommodate higher power density, rotor system speed and load increase, leading to intensified vibration and higher alternating load frequencies. These factors combined pose unprecedented challenges to the lubrication reliability, cooling effectiveness, and long-term durability of the bearing system, a core component of the turbocharger.

[0003] The bearing system is a key friction pair and supporting component of a turbocharger, and its performance directly determines the turbocharger's efficiency, vibration and noise levels, oil consumption, and service life. Currently, mainstream turbocharger bearing systems mainly adopt the following two technical solutions, but both have certain limitations.

[0004] The first type is a split bearing system, such as Figure 1 As shown, in this system, the thrust bearing 01, which bears the axial load, is typically arranged independently on the compressor 02 side, spatially and structurally separated from the floating bearing 03 (radial bearing), which bears the radial load. The advantages of this design are: keeping the thrust bearing 01 away from the high-temperature zone at the turbine 04 end, effectively avoiding the thermal impact of high-temperature combustion gas on the lubricating oil film on the thrust surface, and improving the thermal stability of the thrust bearing 01; structurally, each component performs its own function, with clear definitions.

[0005] However, its drawbacks are also quite prominent:

[0006] 1. The large number of parts results in a complex system structure and relatively high manufacturing costs.

[0007] 2. The oil consumption is relatively high. Since the thrust bearing 01 and the floating bearing 03 usually require independent oil supply circuits or cavities, the overall volume of lubricating oil supply and leakage paths are increased, resulting in an increase in the amount of oil consumed and carried away by the turbocharger.

[0008] 3. Insufficient internal oil film supply: This system typically supplies oil directly to the external oil film (the oil film between the floating bearing 03 and the bearing housing bore 05), while the internal oil film (the oil film between the floating bearing 03 and the rotor journal 06) relies on oil seeping from the radial oil holes of the floating bearing. In this method, the establishment of the internal oil film depends on the pressure transmission of the external oil film. The oil supply pressure and flow are often insufficient and indirect. Especially under high-speed and high-load conditions, the internal oil film is prone to deterioration due to insufficient oil supply, becoming the weakest link in the entire bearing system most susceptible to wear and failure.

[0009] The second type is a thrust-floating integrated bearing system, such as Figure 2 As shown, this system integrates the functional surfaces of a thrust bearing onto a single floating bearing body. The thrust surfaces are located at both ends of the integrated bearing 07, forming a highly integrated component. Its significant advantages are: highly simplified structure, reduced number of parts, lower manufacturing costs, and improved production consistency.

[0010] However, this solution also has inherent flaws:

[0011] 1. Integrated oil supply leads to limited internal oil film pressure. In order to simultaneously lubricate the radial bearing section 08 and the thrust bearing section 09, the oil circuit design usually separates the oil supply channels for the external and internal oil films. This design often generates pressure loss within the oil circuit, resulting in reduced oil pressure and limited flow to the internal oil film (especially the radial bearing pair) that ultimately requires sufficient lubrication, thus compromising the lubrication effect.

[0012] 2. For a compact structure, one thrust face of the integrated bearing is often located on the side closer to the turbine end, with the rotor shaft shoulder serving as the thrust face. The extreme high-temperature environment at the turbine end easily causes the oil adhering to this area to undergo high-temperature oxidation and cracking, forming carbon deposits and coking. Carbon deposits not only increase friction and damage the oil film, but in severe cases, they can also cause the rotor to seize, leading to abnormal wear or even seizure of the bearing and journal, resulting in significant reliability risks.

[0013] 3. This structure also requires sufficient oil supply to the pressure end thrust surface. Therefore, a relatively large amount of oil is supplied from the pressure end thrust surface to the compressor side. When the compressor inlet is under high negative pressure (vacuum) conditions, the large amount of oil increases the risk of being sucked into the intake manifold from the compressor end seal, i.e., the problem of "compressor negative pressure oil leakage", which affects engine combustion and may cause abnormal oil consumption.

[0014] In summary, while existing split-type bearing systems avoid the effects of high temperatures, they suffer from drawbacks such as high oil consumption, insufficient internal oil film lubrication, and high cost. Integrated bearing systems, on the other hand, achieve low cost and structural simplification, but have significant shortcomings in critical areas such as sufficient internal oil film lubrication, high-temperature reliability of the thrust surface, and compressor-side oil control. In particular, achieving stable, sufficient, and pressurized lubrication in the weakest link—the internal oil film—while systematically reducing oil consumption, preventing high-temperature carbon buildup, and enhancing compressor oil leakage resistance, without significantly increasing costs, has become a critical technical challenge that urgently needs to be addressed for turbochargers to achieve higher performance and reliability.

[0015] In conclusion, the existing technology obviously has inconveniences and defects in practical use, so it is necessary to improve it. Summary of the Invention

[0016] To address the shortcomings of existing technologies, this invention provides a turbocharger device that solves the problems of high oil consumption, insufficient internal oil film lubrication, and high cost associated with traditional split bearing systems, which avoid the effects of high temperatures. While integrated bearing systems achieve low cost and structural simplification, they have significant shortcomings in key areas such as sufficient internal oil film lubrication, high-temperature reliability of the thrust surface, and compressor-side oil control capabilities.

[0017] To address the above problems, the present invention provides the following technical solution:

[0018] A turbocharger assembly, including a bearing housing, oil supply lines, and an integrated bearing;

[0019] The integrated bearing includes a pressure-end integrated bearing and a volute-end integrated bearing arranged side by side along the axial direction.

[0020] The bearing body includes an inner wall surface of a bearing seat, and a support sleeve is rotatably provided within the inner wall surface of the bearing seat. The pressure end integrated bearing and the vortex end integrated bearing are located on both sides of the support sleeve.

[0021] The pressure end integrated bearing and the volute end integrated bearing are radially connected by oil supply pin one and oil supply pin two, which communicate with their inner cavities. Oil supply pin one and oil supply pin two are fixed to the bearing body.

[0022] The oil supply pipeline includes an axial oil passage for lubricating oil that is opened on the bearing body, and the oil inlets of oil supply pin one and oil supply pin two are connected to the axial oil passage for lubricating oil.

[0023] The opposite ends of the pressure end integrated bearing and the volute end integrated bearing are respectively the oil wedge surface of the pressure end integrated bearing and the oil wedge surface of the volute end integrated bearing. The oil wedge surface of the pressure end integrated bearing and the oil wedge surface of the volute end integrated bearing are respectively connected to the inner cavity of the pressure end integrated bearing and the volute end integrated bearing.

[0024] As an optimized solution, the support sleeve is provided with a compressor-side bearing surface and a turbine-side bearing surface that correspond to the oil wedge surface of the integrated bearing at the pressure end and the oil wedge surface of the integrated bearing at the turbine end; the outer diameter of the compressor-side bearing surface is the same as the outer diameter of the oil wedge surface of the integrated bearing at the pressure end, and is 0.1-0.15mm smaller than the inner diameter of the inner wall of the bearing housing; the outer diameter of the turbine-side bearing surface is 80-90% of the outer diameter of the compressor-side bearing surface.

[0025] As an optimized solution, the axial distance between the turbine-side bearing surface and the compressor-side bearing surface is 0.02-0.04 mm smaller than the axial distance between the turbine end integrated bearing oil wedge surface and the pressure end integrated bearing oil wedge surface.

[0026] As an optimized solution, both the pressure end integrated bearing and the vortex end integrated bearing include an outer wall surface and an inner wall surface of the bearing, and the outer wall surface of the bearing is clearance-fitted with the inner wall surface of the bearing housing.

[0027] The inner wall of the bearing is provided with a circumferential groove corresponding to oil supply pin one or oil supply pin two. A number of axial grooves are provided around one side of the circumferential groove and are connected thereto. The other end of the axial groove extends to the pressure end integrated bearing oil wedge surface or the volute end integrated bearing oil wedge surface.

[0028] As an optimized solution, the length of the axial groove accounts for 70-90% of the axial length of the pressure end integrated bearing or the vortex end integrated bearing.

[0029] As an optimized solution, the oil supply pipeline also includes a lubricating oil inlet passage opened on the bearing body, and the lubricating oil inlet passage is connected to the lubricating oil axial passage.

[0030] As an optimized solution, the oil supply pipeline also includes a first branch oil passage and a second branch oil passage that are opened in parallel on the bearing body, and an oil supply hole 1 and an oil supply hole 2 that are opened correspondingly on the pressure end integrated bearing and the vortex end integrated bearing. The first branch oil passage is connected to the first oil supply hole, and the second branch oil passage is connected to the second oil supply hole.

[0031] As an optimized solution, both the first and second oil supply pins are provided with oil supply pin through holes. One end of the first and second oil supply pins are respectively interference-fitted with the corresponding first and second branch oil passages, and the other end of the first and second oil supply pins are respectively clearance-fitted with the corresponding first and second oil supply holes.

[0032] As an optimized solution, a number of bearing housing axial grooves are provided on the inner wall of the bearing housing along the circumferential direction. The end of the bearing housing axial groove extends to the oil discharge end face of the vortex end, and the length of the bearing housing axial groove is 80-90% of the length from the oil discharge end face of the vortex end to the oil discharge end face of the pressure end.

[0033] As an optimized solution, the support sleeve is rotatably mounted on the rotor shaft, which includes a stepped shaft one, a stepped shaft two, and a stepped shaft three with progressively decreasing diameters along the axial direction. The stepped shaft one is provided with an oil slinger groove and a vortex end sealing ring groove, and the end face of the stepped shaft one is welded to the radial turbine. The stepped shaft two is clearance-fitted with the vortex end integrated bearing. The support sleeve is interference-fitted with the stepped shaft three.

[0034] Compared with the prior art, the beneficial effects of the present invention are:

[0035] This invention achieves precise positioning of the pressure end integrated bearing and the volute end integrated bearing through oil supply pin one and oil supply pin two, respectively, so that lubricating oil can be preferentially supplied to the oil wedge surface of the pressure end integrated bearing and the oil wedge surface of the volute end integrated bearing. Thus, the lubricating oil is first supplied to the oil wedge surface of the bearing that mainly supports the rotor shaft radially, effectively reducing the risk of wear between the rotor shaft and the inner wall surface of the bearing.

[0036] The lubricating oil entering the inner wall of the bearing is evenly distributed in the circumferential direction through the circumferential groove, and then guided to the oil wedge surface of the volute end integrated bearing and the oil wedge surface of the pressure end integrated bearing through the axial groove connected to it. While ensuring that the thrust surface is fully lubricated, the amount of oil flowing to the compressor side is significantly reduced, which effectively reduces the possibility of oil leakage of the centrifugal compressor under the negative pressure condition of intake.

[0037] After the lubricating oil reaches the oil wedge surface of the integrated bearing at the volute end and the integrated bearing at the pressure end, it is thrown outward by the centrifugal force of the rotating support sleeve. Since the diameter of the bearing surface on the compressor side is larger than that on the turbine side, the total oil pressure generated at the pressure end is higher at the same speed. Therefore, a pressure difference is formed in the outer clearance of the bearing from the pressure end to the volute end, which drives the oil to flow towards the volute end. In addition, the axial groove of the bearing housing only leads to the volute end side, which further restricts the flow of oil towards the compressor side and enhances the sealing ability of the system under negative pressure conditions.

[0038] The entire lubrication path passes sequentially through the bearing inner clearance, the vortex-side bearing surface / compressor-side bearing surface, and the bearing outer clearance, forming a series oil supply method. Compared with the traditional parallel oil supply structure, this design significantly reduces the total amount of oil required by the bearing system and reduces the operating power consumption of the oil supply system.

[0039] Meanwhile, the bearing surfaces on the vortex end and compressor side are positioned in the center, keeping them away from the high temperature of the radial turbine. This avoids carbon buildup and coking caused by high temperatures, improving the reliability of the bearing system during long-term operation. Overall, the device has a simple structure, is easy to implement, has controllable costs, and is well-suited for engineering applications. Attached Figure Description

[0040] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the accompanying drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. In all the drawings, similar elements or parts are generally identified by similar reference numerals. In the drawings, the elements or parts are not necessarily drawn to scale.

[0041] Figure 1 and Figure 2 This is a schematic diagram of the existing technology;

[0042] Figure 3 This is a schematic diagram of the structure of the present invention;

[0043] Figure 4 for Figure 3 An enlarged schematic diagram of part A in the middle;

[0044] Figure 5 This is a schematic diagram of the structure of the inner wall surface of the bearing housing of the present invention;

[0045] Figure 6 This is a schematic diagram of the structure of the pressure end integrated bearing of the present invention;

[0046] Figure 7 This is a schematic diagram of the rotor shaft structure of the present invention;

[0047] Figure 8 This is a schematic diagram of the support sleeve of the present invention.

[0048] In the diagram: 1-Centrifugal compressor; 101-Centrifugal impeller; 102-Compressor housing; 2-Radial turbine; 201-Radial turbine; 202-Volume casing; 203-Heat shield; 3-Bearing system; 4-Bearing body; 401-Volume end stop; 402-Bearing housing inner wall; 403-Bearing housing axial groove; 404-Volume end oil discharge face; 405-Pressure end oil discharge face; 406-Bolt; 407-Oil baffle plate Positioning surface; 5-Oil supply pipeline; 501-Lubricating oil inlet passage; 502-Lubricating oil axial passage; 503-Branch oil passage one; 504-Branch oil passage two; 6-Anti-negative pressure component; 601-Impeller sleeve; 602-Shaft seal turbine side end face; 603-Oil baffle; 604-Shaft seal; 605-Pressure end sealing ring; 606-Vortex end sealing ring; 607-Impeller sleeve inner ring wall; 608-Bearing body vortex end inner ring wall; 609 - Pressure end sealing ring groove; 610 - Impeller sleeve wall surface; 7 - Integrated bearing; 701 - Pressure end integrated bearing; 702 - Oil supply hole one; 703 - Scroll end integrated bearing; 704 - Oil supply hole two; 705 - Oil supply pin one; 706 - Oil supply pin two; 709 - Oil supply pin through hole; 710 - Scroll end integrated bearing oil wedge surface; 711 - Pressure end integrated bearing oil wedge surface; 712 - Bearing outer wall surface; 713 - Bearing Inner wall surface; 714-circumferential groove; 715-axial groove; 716-bearing external clearance; 717-bearing internal clearance; 8-rotor shaft; 801-stepped shaft one; 802-stepped shaft two; 803-stepped shaft three; 804-oil slinger groove; 805-vortex end sealing ring groove; 806-locking nut; 9-support sleeve; 901-turbine side bearing surface; 902-compressor side bearing surface; 903-support sleeve pressure side end face. Detailed Implementation

[0049] The embodiments of the technical solution of the present invention will now be described in detail with reference to the accompanying drawings. These embodiments are merely illustrative of the technical solution of the present invention and are therefore intended to limit the scope of protection of the present invention.

[0050] like Figures 3 to 8 As shown, the turbocharger assembly includes a centrifugal compressor 1, a radial turbine 2, and a bearing system 3. The centrifugal compressor 1 includes a centrifugal impeller 101 and a compressor housing 102; the radial turbine 2 includes a radial turbine 201, a volute 202, and a heat shield 203; the bearing system 3 includes a bearing housing 4, an oil supply line 5, an anti-negative pressure assembly 6, an integrated bearing 7, a rotor shaft 8, and a support sleeve 9.

[0051] The impeller sleeve 601 connecting the compressor housing 102 and the bearing body 4 is fastened by a "bolt 406-pressure plate" structure or a clamp structure; the volute housing 202 and the volute end stop 401 of the bearing body 4 are also fastened by the same connection method.

[0052] The integrated bearing 7 includes a pressure-end integrated bearing 701 and a scroll-end integrated bearing 703 arranged side by side along the axial direction.

[0053] The bearing body 4 includes an inner wall surface 402 of the bearing housing, and a support sleeve 9 is rotatably provided inside the inner wall surface 402 of the bearing housing. The pressure end integrated bearing 701 and the volute end integrated bearing 703 are located on both sides of the support sleeve 9.

[0054] The pressure end integrated bearing 701 and the scroll end integrated bearing 703 are radially connected by oil supply pin 1 705 and oil supply pin 2 706, which communicate with their inner cavities. Oil supply pin 1 705 and oil supply pin 2 706 are fixed to the bearing body 4.

[0055] The oil supply line 5 includes a lubricating oil axial passage 502 opened on the bearing body 4, and the oil inlets of oil supply pin 1 705 and oil supply pin 2 706 are connected to the lubricating oil axial passage 502.

[0056] The opposite ends of the pressure end integrated bearing 701 and the scroll end integrated bearing 703 are respectively the pressure end integrated bearing oil wedge surface 711 and the scroll end integrated bearing oil wedge surface 710. The pressure end integrated bearing oil wedge surface 711 and the scroll end integrated bearing oil wedge surface 710 are respectively connected to the inner cavities of the pressure end integrated bearing 701 and the scroll end integrated bearing 703.

[0057] The support sleeve 9 is provided with a corresponding compressor-side bearing surface 902 and a turbine-side bearing surface 901 that cooperate with the pressure end integrated bearing oil wedge surface 711 and the turbine end integrated bearing oil wedge surface 710.

[0058] The turbine-side bearing surface 901 of the support sleeve 9 forms a squeezed oil film with the oil wedge surface 710 of the turbine end integrated bearing to balance the axial force toward the turbine side.

[0059] The compressor-side bearing surface 902 and the pressure end integrated bearing oil wedge surface 711 form a squeezed oil film to balance the axial force towards the compressor side; the outer diameter of the compressor-side bearing surface 902 is the same as the outer diameter of the pressure end integrated bearing oil wedge surface 711, and is 0.1-0.15mm smaller than the inner diameter of the bearing housing inner wall surface;

[0060] The outer diameter of the turbine-side bearing surface 901 is 80-90% of the outer diameter of the compressor-side bearing surface 902;

[0061] The axial distance between the turbine-side bearing surface 901 and the compressor-side bearing surface 902 is 0.02-0.04 mm smaller than the axial distance between the turbine end integrated bearing oil wedge surface 710 and the pressure end integrated bearing oil wedge surface 711 after being positioned by oil supply pin 1 705 and oil supply pin 2 706.

[0062] The support sleeve pressure side end face 903 is in contact with the shaft seal turbine side end face 602, and together with the centrifugal impeller 101, it is locked onto the rotor shaft 8 by the lock nut 806.

[0063] Both the pressure end integrated bearing 701 and the vortex end integrated bearing 703 include an outer wall surface 712 and an inner wall surface 713. The outer wall surface 712 and the inner wall surface 402 of the bearing housing are in clearance fit; the clearance is 0.1-0.15mm, forming a damping oil film.

[0064] The inner wall surface 713 of the bearing is provided with a circumferential groove 714 corresponding to the oil supply pin 1 705 or the oil supply pin 2 706. A number of axial grooves 715, 4-8 in number, are provided around one side of the circumferential groove 714 and are connected thereto. The other end of the axial groove 715 extends to the pressure end integrated bearing oil wedge surface 711 or the volute end integrated bearing oil wedge surface 710.

[0065] The length of the axial groove 715 accounts for 70-90% of the axial length of the pressure end integrated bearing 701 or the volute end integrated bearing 703.

[0066] The cross-sectional shape of the circumferential groove 714 and the axial groove 715 can be semi-circular, triangular, rectangular or trapezoidal, and the groove width and groove depth are controlled within the range of 0.7-1.0mm.

[0067] The oil supply line 5 also includes a lubricating oil inlet passage 501 opened on the bearing body 4, which is connected to the lubricating oil axial passage 502.

[0068] The oil supply line 5 also includes a first branch oil passage 503 and a second branch oil passage 504 that are opened in parallel on the bearing body 4, and an oil supply hole 702 and an oil supply hole 704 that are opened correspondingly on the pressure end integrated bearing 701 and the scroll end integrated bearing 703. The first branch oil passage 503 is connected to the first oil supply hole 702, and the second branch oil passage 504 is connected to the second oil supply hole 704.

[0069] Both oil supply pin 1 705 and oil supply pin 2 706 have an internal oil supply pin through hole 709 with a diameter of not less than 1.0 mm. One end of oil supply pin 1 705 and oil supply pin 2 706 are respectively interference-fitted with the corresponding branch oil passage 1 503 and branch oil passage 2 504, and the other end of oil supply pin 1 705 and oil supply pin 2 706 are respectively clearance-fitted with the corresponding oil supply hole 1 702 and oil supply hole 2 704.

[0070] The inner wall surface 402 of the bearing housing has several axial grooves 403 along the circumferential direction, with a quantity of 4-8. The end of the axial groove 403 extends to the oil discharge end face 404 of the volute end. The length of the axial groove 403 is 80-90% of the length from the oil discharge end face 404 of the volute end to the oil discharge end face 405 of the pressure end.

[0071] The support sleeve 9 is rotatably mounted on the rotor shaft 8. The rotor shaft 8 includes a stepped shaft 1 801, a stepped shaft 2 802, and a stepped shaft 3 803 whose diameter decreases progressively along the axial direction. The stepped shaft 1 801 is provided with an oil slinger groove 804 and a vortex end sealing ring groove 805. The end face of the stepped shaft 1 801 is welded to the radial flow turbine 201. The stepped shaft 2 802 is clearance-fitted with the vortex end integrated bearing 703. The support sleeve 9 is interference-fitted with the stepped shaft 3 803.

[0072] The anti-negative pressure assembly 6 includes an impeller sleeve 601, an oil baffle 603, a shaft seal 604, a pressure end sealing ring 605, and a volute end sealing ring 606. The pressure end sealing ring 605 and the volute end sealing ring 606 are respectively pressed against the inner ring wall 607 of the impeller sleeve and the inner ring wall 608 of the volute end of the bearing housing 4 by their own elasticity, and are correspondingly installed in the pressure end sealing ring groove 609 and the volute end sealing ring groove 805. The outer side of the oil baffle 603 is tightly attached to the impeller sleeve wall 610 and is pressed onto the oil baffle positioning surface 407 of the bearing housing 4 by bolts 406.

[0073] The working principle of this device is as follows:

[0074] The present invention achieves precise positioning of the pressure end integrated bearing 701 and the volute end integrated bearing 703 by using oil supply pin 1 705 and oil supply pin 2 706 respectively, so that lubricating oil can be preferentially supplied to the oil wedge surface 711 of the pressure end integrated bearing and the oil wedge surface 710 of the volute end integrated bearing. Thus, the lubricating oil is supplied first to the bearing oil wedge surface of the main radial support rotor shaft 8, effectively reducing the wear risk between the rotor shaft 8 and the inner wall surface 713 of the bearing.

[0075] The lubricating oil entering the inner wall surface 713 of the bearing is evenly distributed in the circumferential direction by means of the circumferential groove 714, and then guided to the volute end integrated bearing oil wedge surface 710 and the pressure end integrated bearing oil wedge surface 711 through the axial groove 715 connected to it. While ensuring that the thrust surface is fully lubricated, the amount of oil flowing to the compressor side is significantly reduced, which effectively reduces the possibility of oil leakage of the centrifugal compressor 1 under the intake negative pressure condition.

[0076] After the lubricating oil reaches the integrated bearing oil wedge surface 710 and the integrated bearing oil wedge surface 711 at the volute end, it is thrown outward by the centrifugal force of the rotating support sleeve 9. Since the diameter of the compressor side bearing surface 902 is larger than that of the turbine side bearing surface 901, the total oil pressure generated at the pressure end is higher at the same speed. Therefore, a pressure difference is formed in the bearing outer clearance 716 from the pressure end to the volute end, which drives the oil to flow towards the volute end. In addition, the axial groove 403 of the bearing housing only leads to the volute end side, which further restricts the flow of oil towards the compressor side and enhances the sealing ability of the system under negative pressure conditions.

[0077] The entire lubrication path passes sequentially through the bearing inner clearance 717, the vortex end side bearing surface / compressor side bearing surface 902 and the bearing outer clearance 716, forming a series oil supply method. Compared with the traditional parallel oil supply structure, this design significantly reduces the total amount of oil required by the bearing system 3 and reduces the operating power consumption of the oil supply system.

[0078] Meanwhile, the bearing surface on the vortex end and the bearing surface on the compressor side 902 are arranged in a central position, keeping them away from the high temperature of the radial turbine 2, thereby avoiding carbon buildup and coking caused by high temperature, and improving the reliability of the bearing system 3 in long-term operation. Overall, the device has a simple structure, is easy to implement, has controllable cost, and has good engineering applicability.

[0079] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention, and they should all be covered within the scope of the claims and specification of the present invention.

Claims

1. A turbocharger device characterized by: Includes bearing housing (4), oil supply line (5), and integrated bearing (7); The integrated bearing (7) includes a pressure end integrated bearing (701) and a vortex end integrated bearing (703) arranged side by side along the axial direction. The bearing body (4) includes an inner wall surface (402) of the bearing seat, and a support sleeve (9) is rotatably provided inside the inner wall surface (402) of the bearing seat. The pressure end integrated bearing (701) and the vortex end integrated bearing (703) are located on both sides of the support sleeve (9). The pressure end integrated bearing (701) and the volute end integrated bearing (703) are radially connected by an oil supply pin one (705) and an oil supply pin two (706) communicating with their inner cavities. The oil supply pin one (705) and the oil supply pin two (706) are fixed on the bearing body (4). The oil supply pipeline (5) includes a lubricating oil axial oil passage (502) opened on the bearing body (4), and the oil inlets of the first oil supply pin (705) and the second oil supply pin (706) are connected to the lubricating oil axial oil passage (502). The end opposite to the pressure end integrated bearing (701) and the volute end integrated bearing (703) is the pressure end integrated bearing oil wedge surface (711) and the volute end integrated bearing oil wedge surface (710), respectively. The pressure end integrated bearing oil wedge surface (711) and the volute end integrated bearing oil wedge surface (710) are respectively connected to the inner cavity of the pressure end integrated bearing (701) and the volute end integrated bearing (703).

2. The turbocharger apparatus of claim 1, wherein: The support sleeve (9) is provided with a compressor-side bearing surface (902) and a turbine-side bearing surface (901) that correspond to the pressure end integrated bearing oil wedge surface (711) and the turbine end integrated bearing oil wedge surface (710). The outer diameter of the compressor-side bearing surface (902) is the same as that of the pressure end integrated bearing oil wedge surface (711), and is 0.1-0.15 mm smaller than the inner diameter of the bearing housing inner wall surface (402). The outer diameter of the turbine-side bearing surface (901) is 80-90% of the outer diameter of the compressor-side bearing surface (902).

3. The turbocharger device according to claim 2, characterized in that: The axial distance between the turbine side bearing surface (901) and the compressor side bearing surface (902) is 0.02-0.04 mm smaller than the axial distance between the turbine end integrated bearing oil wedge surface (710) and the pressure end integrated bearing oil wedge surface (711).

4. The turbocharger device according to claim 2, characterized in that: Both the pressure end integrated bearing (701) and the vortex end integrated bearing (703) include an outer wall surface (712) and an inner wall surface (713) of the bearing, and the outer wall surface (712) of the bearing is clearance-fitted with the inner wall surface (402) of the bearing housing; The inner wall surface (713) of the bearing is provided with a circumferential groove (714) corresponding to the oil supply pin one (705) or the oil supply pin two (706). A plurality of axial grooves (715) are provided on one side of the circumferential groove (714) and connected thereto. The other end of the axial groove (715) extends to the pressure end integrated bearing oil wedge surface (711) or the vortex end integrated bearing oil wedge surface (710).

5. The turbocharger device according to claim 4, characterized in that: The length of the axial groove (715) accounts for 70-90% of the axial length of the pressure end integrated bearing (701) or the vortex end integrated bearing (703).

6. The turbocharger device according to claim 1, characterized in that: The oil supply pipeline (5) also includes a lubricating oil inlet passage (501) opened on the bearing body (4), and the lubricating oil inlet passage (501) is connected to the lubricating oil axial passage (502).

7. The turbocharger device according to claim 1, characterized in that: The oil supply pipeline (5) also includes a branch oil passage 1 (503) and a branch oil passage 2 (504) that are opened in parallel on the bearing body (4), and an oil supply hole 1 (702) and an oil supply hole 2 (704) that are opened corresponding to the pressure end integrated bearing (701) and the volute end integrated bearing (703). The branch oil passage 1 (503) is connected to the oil supply hole 1 (702), and the branch oil passage 2 (504) is connected to the oil supply hole 2 (704).

8. The turbocharger device according to claim 7, characterized in that: Both the first oil supply pin (705) and the second oil supply pin (706) are provided with oil supply pin through holes (709). One end of the first oil supply pin (705) and the second oil supply pin (706) are respectively press-fitted with the corresponding first branch oil passage (503) and the second branch oil passage (504). The other end of the first oil supply pin (705) and the second oil supply pin (706) are respectively clearance-fitted with the corresponding first oil supply hole (702) and the second oil supply hole (704).

9. The turbocharger device according to claim 1, characterized in that: The inner wall surface (402) of the bearing housing is provided with a plurality of bearing housing axial grooves (403) along the circumferential direction. The end of the bearing housing axial groove (403) extends to the vortex end oil discharge end face (404). The length of the bearing housing axial groove (403) is 80-90% of the length from the vortex end oil discharge end face (404) to the pressure end oil discharge end face (405).

10. The turbocharger device according to claim 1, characterized in that: The support sleeve (9) is rotatably mounted on the rotor shaft (8). The rotor shaft (8) includes a stepped shaft one (801), a stepped shaft two (802), and a stepped shaft three (803) whose diameter decreases gradually along the axial direction. The stepped shaft one (801) is provided with an oil slinger groove (804) and a vortex end sealing ring groove (805). The end face of the stepped shaft one (801) is welded to the radial turbine (201). The stepped shaft two (802) is clearance-fitted with the vortex end integrated bearing (703). The support sleeve (9) is interference-fitted with the stepped shaft three (803).

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