A turbocharger turbine end oil and gas sealing structure

Abstract

The present invention discloses a turbocharger turbine end oil and gas sealing structure, including a turbocharger main shaft turbine, a heat shield, a first sealing member, a second sealing member and a supercharger bearing housing, wherein the supercharger main shaft turbine includes a turbine and a main shaft, one side of the heat shield is installed on the periphery of the main shaft and close to the turbine for protecting the sealing member; one side of the heat shield is installed with a first sealing member for preventing high-temperature gas brought by the operation of an internal combustion engine from invading the interior of the bearing housing; the second sealing member is installed between the first sealing member and the supercharger bearing housing. The turbocharger turbine end oil and gas sealing structure can meet the turbocharger lubricating oil sealing requirements in limited space, high temperature, zero speed and high oil pressure without adding other parts of the diesel engine, destroying the overall structure of the supercharger, and affecting the performance and reliability of the supercharger, and is suitable for axial flow and radial flow superchargers of various sizes, without requiring external assistance and is easy to implement.

Description

Technical Field

[0001] The present invention relates to the technical field of turbochargers, and in particular to an oil and gas sealing structure at a turbine end of a turbocharger. Background Art

[0002] As the operating conditions of internal combustion engines become increasingly harsh, the lubricating oil supply pressure of internal combustion engines and their turbochargers continues to increase. At present, for turbochargers with sequential and two-stage supercharging, when one or several turbochargers in the supercharging system are not working or working at a low speed, the lubricating oil pressure in the system remains as high as when it is in working state, which puts forward quite high requirements for the oil inlet and return and lubricating oil sealing of the turbocharger. At the same time, as the integration of diesel engines and turbochargers becomes higher and higher, the spatial size of turbochargers is getting smaller and smaller. Limited by the compact layout space and more functional requirements, the oil and gas seal structure design of the turbine end of miniaturized turbochargers faces unprecedented challenges.

[0003] The traditional sealing method of the turbocharger lubricating oil sealing system is labyrinth seal or piston ring seal. In recent years, as the requirements for weight, volume, acceleration followability, etc. of internal combustion engines and their turbochargers have become increasingly stringent, especially for turbochargers with sequential and two-stage supercharging, when one or several turbochargers in the supercharging system are not working or working at low speed, the lubricating oil pressure remains as high as when it is working. This puts forward quite high requirements for the lubricating oil inlet, return oil and lubricating oil sealing in the turbocharger when it is not working. The traditional sealing method cannot meet the sealing requirements of limited space, high temperature, zero speed and high oil pressure. Summary of the invention

[0004] The present invention provides an oil-gas sealing structure at the turbine end of a turbocharger, so as to overcome the problem that for a turbocharger of sequential supercharging and two-stage supercharging mode, when one or several superchargers in the supercharging system are not working or working at a low speed, the existing traditional sealing method cannot meet the sealing requirements of limited space, high temperature, zero speed and high oil pressure.

[0005] In order to achieve the above object, the technical solution of the present invention is:

[0006] A turbocharger turbine end oil and gas sealing structure comprises a turbocharger main shaft turbine, a heat shield, a sealing component and a turbocharger bearing housing, wherein the turbocharger main shaft turbine comprises a turbine and a main shaft, one side of the heat shield is installed at the periphery of the main shaft and close to the turbine for protecting the sealing component, the sealing component comprises a first sealing component and a second sealing component, the first sealing component is installed on the other side of the heat shield, the second sealing component is installed between the first sealing component and the turbocharger bearing housing, the turbocharger bearing housing and the main shaft respectively form radial gaps for lubricating oil circulation with the turbine radial locating bearing, the second sealing component is provided with a plurality of return oil chambers and a plurality of oil drain ports, the return oil chamber is used to store lubricating oil from the radial gap, and the oil drain port is used to discharge the lubricating oil in the return oil chamber to the turbocharger return oil chamber.

[0007] Furthermore, the first sealing component includes a turbine end oil seal sleeve, a sealing piston ring and a turbine end air seal gasket, the turbine end oil seal sleeve is installed on the main shaft, the turbine end oil seal sleeve is provided with a ring groove for cooperating with the installation of the sealing piston ring, the outer side of the turbine end oil seal sleeve is provided with the turbine end air seal gasket, and the turbine end air seal gasket is provided with a protruding structure for clamping the sealing piston ring.

[0008] Furthermore, the second sealing component includes a turbine end copper oil seal body, the turbine end copper oil seal body is provided with a first sealing tooth and a second sealing tooth, the inner diameter of the circle where the second sealing tooth is located is larger than the inner diameter of the circle where the first sealing tooth is located, the first sealing tooth, one side of the main shaft and the turbine end copper oil seal body constitute a second turbine end oil return chamber, the second turbine end oil return chamber is used to store lubricating oil from the second radial gap, the turbine end copper oil seal body, the turbine end air seal gasket and the supercharger bearing housing constitute a first turbine end oil return chamber, the first turbine end oil return chamber is used to store lubricating oil from the first radial gap.

[0009] Furthermore, one side of the vortex end oil seal sleeve is provided with a stepped structure which is installed in cooperation with the second sealing tooth. The stepped structure, one side of the main shaft, the first sealing tooth and the second sealing tooth constitute a third vortex end oil return chamber. The third vortex end oil return chamber is used to store the lubricating oil originating from the second vortex end oil return chamber through the lower end of the first sealing tooth. The stepped structure, the second sealing tooth and the vortex end air seal pad constitute a fourth vortex end oil return chamber. The fourth vortex end oil return chamber is used to store the lubricating oil originating from the third vortex end oil return chamber through the lower end of the second sealing tooth.

[0010] Furthermore, the vortex end copper oil seal body is provided with a first oil drain port, a second oil drain port and a third oil drain port on the other side of the main shaft, the first oil drain port is communicated with the first vortex end oil return chamber, the second vortex end oil return chamber and the supercharger oil return chamber, the second oil drain port is communicated with the third vortex end oil return chamber and the supercharger oil return chamber, and the third oil drain port is communicated with the fourth vortex end oil return chamber and the supercharger oil return chamber.

[0011] Furthermore, the supercharger bearing housing and the turbine radial locating bearing are circumferentially positioned using locating pins, and one end of the turbine radial locating bearing is axially positioned and installed with the turbine end copper oil seal body.

[0012] Furthermore, the diameter of the turbine radial locating bearing is larger than the diameter of the circle where the contact surface between the turbine radial locating bearing and the turbine end copper oil seal body is located.

[0013] Furthermore, a heat-insulating air cavity is formed between the heat-insulating cover and the second sealing member.

[0014] Furthermore, a first oil-resistant and high-temperature-resistant sealant layer is provided between the turbine end air seal gasket and the contact surface of the supercharger bearing housing, and a second oil-resistant and high-temperature-resistant sealant layer is provided between the turbine end air seal gasket and the contact surface of the turbine end copper oil seal body.

[0015] Beneficial effects of the present invention:

[0016] The present invention provides an oil-gas sealing structure at the turbine end of a turbocharger, wherein a heat shield is added on one side of the turbine end to protect the sealing component; a first sealing component is installed on one side of the heat shield to prevent high-temperature gas caused by the operation of an internal combustion engine from invading the interior of a bearing housing; a second sealing component is installed between the first sealing component and the supercharger bearing housing to increase the oil return effect and prevent oil leakage. Without adding other parts of the diesel engine, destroying the overall structure of the supercharger, and affecting the performance and reliability of the supercharger, the lubricating oil sealing requirements of the turbocharger in limited space, high temperature, zero speed, and high oil pressure can be met, and it is suitable for axial flow and radial flow superchargers of various sizes, and no external assistance is required and it is easy to implement. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative labor.

[0018] Figure 1 This is a schematic diagram of the oil and gas sealing structure of the turbine end of the turbocharger of the present invention;

[0019] Figure 2 for Figure 1 A magnified view of middle;

[0020] Figure 3 for Figure 1 Enlarged view of B.

[0021] In the figure: 1. turbine end oil seal sleeve; 111. ring groove; 112. stepped structure; 2. sealing piston ring; 3. turbine end gas seal pad; 311. protruding structure; 4. turbine end copper oil seal body; 5. high temperature resistant bolts; 6. turbine; 7. heat insulation cover; 8. first turbine end oil return chamber; 9. supercharger bearing housing; 10. turbine end radial bearing oil circuit; 11. bearing housing oil inlet circuit; 12. turbine radial positioning bearing; 121. first radial gap; 122. second radial gap; 13. positioning pin; 14. main shaft; 15. second turbine end oil return chamber; 16. first sealing tooth; 17. third turbine end oil return chamber; 18. second sealing tooth; 19. fourth turbine end oil return chamber; 20. heat insulation air chamber; 21. first oil drain port; 22. second oil drain port; 23. third oil drain port; 24; supercharger oil return chamber. DETAILED DESCRIPTION

[0022] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0023] This embodiment provides a turbocharger turbine end oil and gas sealing structure, such as Figure 1 As shown, it includes a supercharger main shaft turbine, a heat shield 7, a first sealing component, a second sealing component and a supercharger bearing housing 9. The supercharger main shaft turbine includes a turbine 6 and a main shaft 14. One side of the heat shield 7 is installed on the periphery of the main shaft 14 and close to the turbine 6 to protect the sealing component; the first sealing component is installed on the other side of the heat shield 7 to prevent the high-temperature gas brought by the operation of the internal combustion engine from invading the inside of the supercharger bearing housing 9 and thus protecting the bearing rotor; the second sealing component is installed between the first sealing component and the supercharger bearing housing 9 to increase the oil return effect and prevent oil leakage.

[0024] First, the turbine end copper oil seal body 4 and the turbine end gas seal gasket 3 are fixedly installed by pressing and fitting with high-temperature resistant bolts 5, and then installed and fixed on the end face of the turbine 6 side inside the supercharger bearing housing 9; the heat insulation cover 7 that protects the oil and gas sealing structure at the turbine 6 end is positioned and installed on the supercharger bearing housing 9, which is used to prevent the high-temperature combustion gas generated during the operation of the internal combustion engine from invading the inside of the supercharger bearing housing 9 from the turbine 6 end, and protect the function and performance of the bearing rotor component; the turbine end oil seal sleeve 1 is installed on the main shaft 14 and rotates synchronously with the main shaft 14, and the sealing piston ring 2 is installed in the annular groove 111 on the outside of the turbine end oil seal sleeve 1, which plays a sealing role when the bearing rotor component rotates; the turbine radial positioning bearing 12 is installed on the supercharger bearing housing 9 close to the turbine 6 side. The inner hole and the first radial gap 121 are formed together with the supercharger bearing housing 9. When the supercharger lubricating oil passes through the bearing housing oil inlet 11 inside the supercharger bearing housing 9 under pressure, a part of the supercharger lubricating oil enters the second radial gap 122 between the main shaft 14 and the turbine radial positioning bearing 12 through the vortex end radial bearing oil passage 10 for main shaft lubrication and cooling, and another part of the supercharger lubricating oil enters the first radial gap 121 between the outer diameter of the turbine radial positioning bearing 12 and the inner diameter of the supercharger bearing housing 9 through the vortex end radial bearing oil passage 10. The lubricating oil in the first radial gap 121 is used to cool the turbine radial positioning bearing 12, and then overflows to both sides of the turbine radial positioning bearing 12. The lubricating oil overflowing to the pressure end side of the turbocharger directly enters the supercharger oil return chamber 24 and finally returns to the diesel engine oil pan. Because the space is large and far away from the sealing structure, there is no oil sealing problem. The lubricating oil overflowing to one side of the turbine 6 first enters the first vortex end oil return chamber 8 and releases and reduces part of the oil pressure. Under the action of gravity, the lubricating oil after the oil pressure drops flows downward in the first vortex end oil return chamber 8 and directly flows into the supercharger oil return chamber 24, and finally returns to the diesel engine oil pan.

[0025] The lubricating oil in the second radial gap 122 participates in the lubrication of the stator and rotor of the matching part of the turbine radial positioning bearing 12 and the main shaft 14. After participating in the lubrication, the lubricating oil overflows to both sides along the second radial gap between the turbine radial positioning bearing 12 and the main shaft. The lubricating oil overflowing to the pressure end of the turbocharger directly enters the turbocharger oil return chamber 24 and finally returns to the diesel engine oil pan. Because the space is large and far away from the sealing structure, there is no oil sealing problem. Figure 2As shown, the lubricating oil overflowing to one side of the turbine 6 first enters the second vortex end oil return chamber 15, and releases and reduces part of the oil pressure. Under the action of gravity, the lubricating oil after the oil pressure drops flows downward in the second vortex end oil return chamber 15, and flows into the supercharger oil return chamber 24 through the first oil drain port 21 at the bottom and finally returns to the diesel engine oil pan. Because the vortex end copper oil seal body 4 is a stator component and the main shaft 14 is a rotor component, there must be a third radial gap between the first sealing tooth 16 of the vortex end copper oil seal body 4 and the main shaft 14. Since the vortex end copper oil seal body 4 is a copper material component and the main shaft is a steel material component, the design allows radial wear during operation. Although the third radial clearance is controlled to be very small, a small amount of lubricating oil will still flow into the third vortex end oil return chamber 17 along the main shaft 14 under the action of pressure and inertia, and release and reduce part of the oil pressure. After the oil pressure drops, the lubricating oil flows downward in the third vortex end oil return chamber 17 under the action of gravity and passes through the second oil drain port 22 at the lower end, and then flows into the supercharger oil return chamber 24 and finally returns to the diesel engine oil pan.

[0026] Because the vortex end copper oil seal body 4 is a stator component and the vortex end oil seal sleeve 1 is a rotor component, there must be a fourth radial gap between the second sealing tooth 18 of the vortex end copper oil seal body 4 and the vortex end oil seal sleeve 1. Since the vortex end copper oil seal body 4 is a copper material component and the vortex end oil seal sleeve 1 is a steel material component, the design allows radial wear during operation. Although the fourth radial gap is controlled to be very small, there will still be a very small amount of lubricating oil gas that sneaks into the fourth vortex end oil return chamber 19 and gradually condenses into oil droplets. The very small amount of lubricating oil after convergence flows into the third vortex end oil return chamber 17 under the action of gravity, and then flows downward along the third vortex end oil return chamber 17 and passes through the third oil drain port 23 at the bottom, and then flows into the supercharger oil return chamber 24 and finally returns to the diesel engine oil pan. If there is still lubricating oil trying to enter the turbine 6 side through the fourth vortex end oil return chamber 19, the vortex end sealing piston ring 2 is responsible for the last blockage. At the same time, the main function of the sealing piston ring 2 is to prevent the high-temperature combustion gas on the turbine 6 side from passing through the sixth radial gap between the vortex end gas seal 3 and the vortex end oil seal ring, and finally invading the inside of the supercharger bearing housing 9. If a small amount of high-temperature combustion gas enters the fourth vortex end oil return chamber 19 through the sealing piston ring 2, since the radial and axial gaps of the fourth vortex end oil return chamber 19 are very small, the actual leakage amount can be so small as to be negligible.

[0027] In a specific embodiment, the first sealing component includes a turbine end oil seal sleeve 1, a sealing piston ring 2 and a turbine end gas seal pad 3. The turbine end oil seal sleeve 1 is installed on the main shaft 14 by interference fit or is integrally processed with the main shaft 14. If the inner diameter of the turbine end oil seal sleeve 1 forms an interference fit with the outer diameter of the main shaft 14 and is tightly installed, the interference is controlled to be 0.03mm-0.07mm, and there is an axial positioning surface to achieve accurate axial positioning of the turbine end oil seal sleeve 1. In order to ensure the size and shape and position tolerances of the outer diameter of the turbine end oil seal sleeve 1, it can also be directly integrally processed on the main shaft 14. The turbine end oil seal sleeve 1 is provided with a ring groove 111 for matching and installing the sealing piston ring 2, and the width of the ring groove 111 is controlled to be 0.03mm-0.09mm larger than the width of the sealing piston ring 2. The turbine end gas seal pad 3 is provided on the outside of the turbine end oil seal sleeve 1, and the turbine end gas seal pad 3 is provided with a protruding structure 311 for clamping the sealing piston ring 2. The turbine end gas seal gasket 3 and the turbine end copper oil seal body 4 are fixedly installed by being pressed and fitted with high-temperature resistant bolts 5, and then fixed on the end face of one side of the turbine 6 inside the supercharger bearing housing 9. The heat insulation cover 7 for protecting the oil and gas sealing structure at the end of the turbine 6 is positioned and installed on the supercharger bearing housing 9 to prevent the high-temperature combustion gas at the end of the turbine 6 from invading the inside of the supercharger bearing housing 9 and protecting the bearing rotor parts; the turbine end oil seal sleeve 1 is installed on the main shaft 14 and rotates synchronously with the main shaft 14, and plays a sealing role when the bearing rotor parts rotate.

[0028] In a specific embodiment, Figure 3 As shown, the second sealing component includes a turbine end copper oil seal body 4, and the turbine end copper oil seal body 4 is provided with a first sealing tooth 16 and a second sealing tooth 18. The first sealing tooth 16, one side of the main shaft 14 and the turbine end copper oil seal body 4 constitute a second turbine end oil return chamber 15, and the turbine end copper oil seal body 4, the turbine end air seal gasket 3 and the supercharger bearing housing 9 constitute a first turbine end oil return chamber 8. A step structure 112 is provided on one side of the vortex end oil seal sleeve 1 for being mounted in cooperation with the second sealing tooth 18. The step structure 112, one side of the main shaft 14, the first sealing tooth 16 and the second sealing tooth 18 constitute a third vortex end oil return chamber 17. The step structure 112, the second sealing tooth 18 and the vortex end gas seal pad 3 constitute a fourth vortex end oil return chamber 19. The vortex end copper oil seal body 4 is provided on the other side of the main shaft 14 with a first oil drain port 21, a second oil drain port 22 and a third oil drain port 23. The first oil drain port 21, the second oil drain port 22 and the third oil drain port 23 are connected to the supercharger oil return chamber 24. By adding multiple vortex end oil return chambers and oil drain ports for returning the supercharger lubricating oil, the leakage of lubricating oil is further prevented.

[0029] In a specific embodiment, the supercharger bearing housing 9 and the turbine radial positioning bearing 12 are circumferentially positioned and evenly installed using positioning pins 13 to ensure that the turbine radial positioning bearing 12 does not rotate with the rotor during operation. One end of the turbine radial positioning bearing 12 is axially positioned and installed with the turbine end copper oil seal body 4 to ensure that the turbine radial positioning bearing 12 is not axially misaligned, further ensuring the accuracy of fixed installation. Specifically, the turbine end copper oil seal body 4 is made of copper material, which can avoid the problem of rubbing and damaging the stator and rotor parts due to the small radial clearance between the oil seal and the rotor. The turbine end copper oil seal body 4 arranges two sealing teeth along the axial direction of the main shaft 14, and the inner diameter of the sealing tooth and the radial clearance of the rotor are controlled at 0.1mm-0.2mm on one side, and the width of the sealing tooth is controlled at 0.5mm-2mm, and the inner diameter of the second sealing tooth 18 is larger than the inner diameter of the first sealing tooth 16, so as to form a liquid level height difference to improve the sealing effect.

[0030] In a specific embodiment, the diameter of the turbine radial locating bearing 12 is larger than the diameter of the circle where the contact surface between the turbine radial locating bearing 12 and the turbine end copper oil seal body 4 is located, so that the lubricating oil flowing into the first radial gap can smoothly flow into the first turbine end oil return chamber 8, and then flow into the supercharger oil return chamber to prevent lubricating oil leakage.

[0031] In a specific embodiment, the supercharger bearing housing 9 is evenly provided with bearing housing oil inlet passages 11, specifically, three bearing housing oil inlet passages 11 are evenly distributed at an angle of 120°. The bearing housing oil inlet passages 11 flow into the second radial gap formed by the turbine radial locating bearing 12 and the main shaft 14 through the turbine end radial bearing oil passage 10, thereby achieving the lubrication, cooling and cleaning of the main shaft 14.

[0032] In a specific embodiment, a heat insulating air cavity 20 is provided between the heat insulating cover 7 and the second sealing member. The heat insulating air cavity 20 forms a heat insulating function by air to prevent the high temperature combustion gas of the turbine from quickly transferring heat to the supercharger bearing housing 9.

[0033] In a specific embodiment, a first oil-resistant and high-temperature-resistant sealant layer is provided between the contact surface of the turbine end gasket 3 and the supercharger bearing housing 9, and a second oil-resistant and high-temperature-resistant sealant layer is provided between the contact surface of the turbine end gasket 3 and the turbine end copper oil seal body 4. The sealant applied to the oil-resistant and high-temperature-resistant sealant layer is an anti-aging, oil-resistant, and high-temperature-resistant silicone rubber sealant. The sealant is evenly applied to the entire pressing surface to withstand a short-term maximum temperature of 600°C and a long-term use temperature of 350°C.

[0034] Compared with the prior art, the advantages of the present invention are that, by designing and optimizing the arrangement of sealing structures such as the supercharger main shaft turbine, the heat shield, the first sealing component and the second sealing component, and optimizing the setting of the lubricating oil circuit and the common position, the axial and radial sealing functions of the supercharger turbine end are realized in a limited space, and the structure is compact and reasonable; for multi-stage supercharging or sequential supercharging systems, the characteristics of low (zero) speed and high oil pressure of the supercharger at partial load are achieved by axially and radially separating the return oil chamber to achieve the effect of layer-by-layer blocking and pressure reduction of multiple separation chambers, with higher return sliding efficiency, more targeted oil sealing and large safety margin; the radial sealing gap of the stator and rotor parts is small, the use of copper material is not afraid of scratching, and the structural reliability is high; the components described in the structure are all small-sized components made of conventional materials, which are easy to replace and cost-effective The invention has low cost and strong maintainability; it solves the problem of poor positioning of the radial bearing at the turbine end of a small-sized and compact supercharger; it has a more obvious and direct cooling effect on the sealing piston ring at the turbine end, which helps to extend the service life of the piston ring and reduce carbon deposits caused by high temperature at the piston ring; the supercharger realizes lubricating oil sealing and high-temperature gas sealing at the same time, with two functions in one structure, and there is no need to design the structure separately, so it is more compact and has strong structural versatility; without adding other parts of the diesel engine, destroying the overall structure of the supercharger, and affecting the performance and reliability of the supercharger, it can meet the lubricating oil sealing requirements of the turbocharger in limited space, high temperature, zero speed and high oil pressure, and is suitable for axial flow and radial flow superchargers of various sizes, without the need for external assistance, and is easy to implement.

[0035] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements 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.

Claims

1. A turbocharger turbine end oil and gas sealing structure, characterized in that: The invention comprises a supercharger main shaft turbine, a heat shield (7), a sealing component and a supercharger bearing housing (9), wherein the supercharger main shaft turbine comprises a turbine (6) and a main shaft (14), wherein the heat shield (7) is installed at the periphery of the main shaft (14) and close to the turbine (6) for protecting the sealing component, wherein the sealing component comprises a first sealing component and a second sealing component, wherein the first sealing component is installed at one side of the heat shield (7), wherein the second sealing component is installed between the first sealing component and the supercharger bearing housing (9), wherein the supercharger bearing housing (9) and the main shaft (14) respectively form radial gaps for lubricating oil circulation with a turbine radial positioning bearing (12), wherein the second sealing component is provided with a plurality of oil return chambers and a plurality of oil drain ports, wherein the oil return chambers are used to store lubricating oil from the radial gaps, and wherein the oil drain ports are used to discharge the lubricating oil in the oil return chambers to the supercharger oil return chamber (24); The first sealing component comprises a turbine end oil seal sleeve (1), a sealing piston ring (2) and a turbine end gas seal gasket (3); the turbine end oil seal sleeve (1) is mounted on the main shaft (14); the turbine end oil seal sleeve (1) is provided with a ring groove (111) for matching and mounting the sealing piston ring (2); the turbine end gas seal gasket (3) is provided on the outer side of the turbine end oil seal sleeve (1); the turbine end gas seal gasket (3) is provided with a protruding structure (311) for clamping the sealing piston ring (2); The second sealing component comprises a turbine end copper oil seal body (4), the turbine end copper oil seal body (4) is provided with a first sealing tooth (16) and a second sealing tooth (18), the inner diameter of the circle where the second sealing tooth (18) is located is greater than the inner diameter of the circle where the first sealing tooth (16) is located, the first sealing tooth (16), one side of the main shaft (14) and the turbine end copper oil seal body (4) constitute a second turbine end oil return chamber (15), the second turbine end oil return chamber (15) is used to store oil from the main shaft (14) and the turbine radial positioning The turbine radial locating bearing (12) is installed in the inner hole of the turbocharger bearing housing (9) close to the turbine (6) side, and together with the turbocharger bearing housing (9) form the first turbocharger end oil return chamber (8). The first turbocharger end oil return chamber (8) is used to store the lubricating oil from the first radial gap (121).

2. The turbocharger turbine end oil and gas sealing structure according to claim 1, characterized in that: A stepped structure (112) is provided on one side of the vortex end oil seal sleeve (1) and is mounted in cooperation with the second sealing tooth (18). The stepped structure (112), one side of the main shaft (14), the first sealing tooth (16) and the second sealing tooth (18) form a third vortex end oil return chamber (17). The third vortex end oil return chamber (17) is used to store lubricating oil originating from the second vortex end oil return chamber (15) through the lower end of the first sealing tooth (16). The stepped structure (112), the second sealing tooth (18) and the vortex end gas seal pad (3) form a fourth vortex end oil return chamber (19). The fourth vortex end oil return chamber (19) is used to store lubricating oil originating from the third vortex end oil return chamber (17) through the lower end of the second sealing tooth (18).

3. The turbocharger turbine end oil and gas sealing structure according to claim 1, characterized in that: The vortex end copper oil seal body (4) is provided with a first oil drain port (21), a second oil drain port (22) and a third oil drain port (23) on the other side of the main shaft (14); the first oil drain port (21) is communicated with the first vortex end oil return chamber (8), the second vortex end oil return chamber (15) and the supercharger oil return chamber (24); the second oil drain port (22) is communicated with the third vortex end oil return chamber (17) and the supercharger oil return chamber (24); and the third oil drain port (23) is communicated with the fourth vortex end oil return chamber (19) and the supercharger oil return chamber (24).

4. The turbocharger turbine end oil and gas sealing structure according to claim 1, characterized in that: The supercharger bearing housing (9) and the turbine radial positioning bearing (12) are circumferentially positioned using positioning pins (13), and one end of the turbine radial positioning bearing (12) is axially positioned and installed with the turbine end copper oil seal body (4).

5. The turbocharger turbine end oil and gas sealing structure according to claim 4, characterized in that: The diameter of the turbine radial positioning bearing (12) is greater than the diameter of the circle where the contact surface between the turbine radial positioning bearing (12) and the turbine end copper oil seal body (4) is located.

6. The turbocharger turbine end oil and gas sealing structure according to claim 1, characterized in that: A heat-insulating air cavity (20) is formed between the heat-insulating cover (7) and the second sealing component.

7. The turbocharger turbine end oil and gas sealing structure according to claim 1, characterized in that: A first oil-resistant and high-temperature-resistant sealing rubber layer is provided between the contact surface between the turbine end gas seal gasket (3) and the supercharger bearing housing (9), and a second oil-resistant and high-temperature-resistant sealing rubber layer is provided between the contact surface between the turbine end gas seal gasket (3) and the turbine end copper oil seal body (4).

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