Turbocharger thermal management structure

Abstract

Turbocharger thermal management structure relates to turbocharging device technical field of internal combustion engine, including connected radial turbine, centrifugal compressor and bearing system, and heat management structure is arranged between radial turbine and bearing system;The heat management structure includes heat shield one, heat shield two and heat shield three which are arranged in the shape of a metal sheet of a rotary body at the turbine back disc, the heat shield one and the heat shield two form the heat insulation cavity one between them, the heat shield two and the heat shield three form the heat insulation cavity two between them, the heat shield three and annular cooling groove form the heat insulation cavity three between them, the heat insulation cavity one is communicated with the gap at the turbine back disc, and the heat insulation cavity three is connected with the cold air hole;The heat insulation cavity three, the heat insulation cavity two and the heat insulation cavity one are sequentially communicated through the gas guide structure.The present application realizes the purpose of greatly improving the heat insulation efficiency and realizing the active and efficient cooling of the key area under the premise of not greatly increasing the weight and volume.

Description

Technical Field

[0001] This invention relates to the field of internal combustion engine turbocharging technology, and more specifically to the thermal management structure of a turbocharger. Background Technology

[0002] Turbocharging technology, as a key means of improving the power and efficiency of internal combustion engines, has been widely used in modern automobiles and various mechanical equipment. Its core principle is to use the high-temperature exhaust gas from the engine to drive a turbine, which in turn drives a coaxial compressor to pre-compress the intake air, thereby increasing the intake volume of the cylinders. However, this process also exposes the turbocharger's turbine to extremely harsh high-temperature environments for extended periods. The exhaust temperature of modern high-performance engines can reach as high as 950°C or even 1050°C, posing a serious challenge to the reliability of the turbocharger's bearing system.

[0003] Currently, the technical solutions commonly used in the industry to address high-temperature issues mainly include:

[0004] Single or double metal heat shield: A metal heat shield is installed between the turbine housing and the bearing housing. The heat is insulated by the air gap between the shield and the housing, in an attempt to separate the high-temperature heat source in the turbine flow channel from the bearing housing.

[0005] Optimize cooling water circuit: For turbochargers equipped with liquid-cooled intermediate shells, increase the coolant flow rate or optimize the water channel design to enhance cooling of critical areas such as the bearing housing.

[0006] Material upgrades: Use more heat-resistant alloy materials to manufacture turbine housings or try applying heat-insulating coatings such as ceramics.

[0007] However, the aforementioned existing technical solutions still have many obvious limitations and inherent defects, mainly in the following aspects:

[0008] First, the insulation efficiency of traditional heat shields has reached its limit. Single-layer or double-layer heat shields mainly rely on reflection and air insulation, and their insulation effect is limited. Under continuous extreme high-temperature conditions, a large amount of radiant heat and heat conduction will still penetrate the heat shield, causing the temperature of the heat shield itself to remain high. This not only fails to effectively protect surrounding components, but also becomes a huge heat source itself, exacerbating the thermal load on the bearing housing and leading to safety hazards such as oil coking and lubrication failure.

[0009] Secondly, existing water-cooling systems heavily rely on the engine's circulating water system. Increasing the coolant flow rate for turbocharger cooling would increase the load on the engine water pump, which is detrimental to overall engine energy efficiency. Furthermore, water-cooling systems are highly complex, and their application would reduce the casting yield of bearing housings and turbine housings, leading to a significant increase in costs. This is unfavorable for cost-sensitive products like turbochargers.

[0010] Third, using cast steel materials such as D5S or 1.4826 can significantly improve the upper limit of the application temperature of the bearing housing and volute, but the substantial increase in material cost has become the main bottleneck for the application of this material upgrade measure.

[0011] In conclusion, the existing technology obviously has inconveniences and defects in practical use, so it is necessary to improve it. Summary of the Invention

[0012] To address the shortcomings of existing technologies, this invention provides a turbocharger thermal management structure that significantly improves heat insulation efficiency and achieves active and efficient cooling of critical areas without substantially increasing weight and volume.

[0013] To address the above problems, the present invention provides the following technical solution:

[0014] A turbocharger thermal management structure includes a radial-flow turbine, a centrifugal compressor, and a bearing system connected together, wherein a thermal management structure is provided between the radial-flow turbine and the bearing system;

[0015] The thermal management structure includes a heat shield 1, a heat shield 2, and a heat shield 3, which are arranged in the shape of a rotating metal sheet at the turbine back disk. A heat shield 1 is formed between the heat shield 1 and the heat shield 2. A heat shield 2 is formed between the heat shield 2 and the heat shield 3. A heat shield 3 is formed between the heat shield 3 and the annular cooling groove. The heat shield 1 is connected to the gap at the turbine back disk. The heat shield 3 is connected to a cooling air hole.

[0016] The heat insulation cavity three, heat insulation cavity two, and heat insulation cavity one are sequentially connected by an air guiding structure.

[0017] As an optimized solution, the outer edge of the heat shield is pressed tightly against the axial stop of the turbine housing along the axial direction, the inner edge of the heat shield is pressed tightly against the stop inside the bearing body along the axial direction, the gap between the axial section of the heat shield and the radial stop of the heat shield is 0.5-1.0mm, and the gap between the radial section of the heat shield and the turbine back plate is 0.5-1.0mm.

[0018] As an optimized solution, the air guiding structure includes a vent hole 1 evenly opened along the circumferential direction on the axial section of the heat shield 1, which connects the heat shield 1 to the gap at the turbine back plate, and the vent hole 1 is located near the outer edge of the heat shield 1.

[0019] As an optimized solution, the outer edge of the second heat shield is pressed tightly against the inner wall of the axial section of the first heat shield along the axial direction. A ventilation gap is provided between the inner edge of the second heat shield and the stop inside the bearing body to connect the second heat shield with the first heat shield. The gap size of the ventilation gap is 0.5-1.5mm.

[0020] As an optimized solution, the outer edge of the heat insulation cover three is pressed and fitted with the outer edge of the heat insulation cover one along the axial direction, and the inner edge of the heat insulation cover three is pressed and fitted with the inner side platform of the annular cooling tank along the axial direction. The heat insulation cover three is provided with a vent hole two that connects the heat insulation cavity three and the heat insulation cavity two. The vent hole two and the cold air hole are 180° apart.

[0021] As an optimized solution, the inner wall of the annular cooling tank is evenly distributed with several flow-disrupting elements along the circumference, and the flow-disrupting elements include grooves or protrusions.

[0022] As an optimized solution, the air guiding structure includes a second air passage between the inner edge of the heat shield and the stop inside the bearing body, which connects the heat shield to the turbine back plate. The gap size of the second air passage is 0.5-1.5mm.

[0023] As an optimized solution, the second heat insulation cover is provided with a third vent that connects the second heat insulation cavity to the first heat insulation cavity, and the third vent is 180° out of phase with the second vent.

[0024] As an optimized solution, the diameter of the first vent is 1-3mm and the number is 6-18; the diameter of the second and third vents is 2-5mm and the number is 1.

[0025] Compared with the prior art, the beneficial effects of the present invention are:

[0026] Firstly, the triple thermal barrier formed by heat shield one, heat shield two and heat shield three significantly increases the thermal resistance from the turbine flow channel to the bearing body compared with traditional heat insulation technology, and reduces the heat transfer to the bearing body.

[0027] Secondly, the triple heat insulation cover together with the cold air hole constitutes the heat management structure. Cooling air is supplied to the heat management structure from the intercooler or external air source. After passing through the cold air nozzle and cold air hole, the cooling air enters the annular cooling tank and flows along the flow path on both sides of the annular cooling tank. It then flows into the heat insulation cavity two through the vent hole two on the heat insulation cover three, which is 180° phase with the cold air hole.

[0028] As the cooling air flows within the annular cooling groove, it can cool the heat transferred from the turbine housing to the bearing housing. Furthermore, the cooling effect is enhanced by the turbulence-enhancing elements, solving the problem of cooling this part of the transmission path in traditional turbocharger cooling technology.

[0029] Thirdly, the cooling gas entering the second insulation chamber will gradually drive the high-temperature gas in the chamber caused by thermal radiation and thermal conduction to flow out, enter the first insulation chamber from the first ventilation gap, and further drive the hot gas in the first insulation chamber to flow out, and flow out of the first insulation chamber from the first ventilation hole on the first insulation cover. In this process, the cooling gas is used to expel the high-temperature gas in the insulation chamber, thereby greatly reducing the gas temperature in the insulation chamber, which greatly improves the problem of high gas temperature in the insulation chamber in traditional insulation methods, and will further reduce the heat transfer from the turbine flow channel to the bearing body.

[0030] Fourthly, during the continuous cooling process, the gas flowing out from the vent is at a lower temperature, which will further expel the high-temperature gas between the axial section of the heat shield and the radial stop of the heat shield, thereby reducing the temperature of the gas on the walls of the axial section of the heat shield and the radial stop of the heat shield, thus reducing the heat transfer in these two areas, which is beneficial to further reduce the thermal load of the bearing body. Attached Figure Description

[0031] 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.

[0032] Figure 1 This is a schematic diagram of the structure of Embodiment 1;

[0033] Figure 2 for Figure 1 A magnified structural diagram of part A in the middle;

[0034] Figure 3 This is a schematic diagram of the structure of the turbulence-disrupting element of the present invention;

[0035] Figure 4 This is a schematic diagram showing the direction of cold air intake in Example 1;

[0036] Figure 5 This is a schematic cross-sectional view of the heat insulation cover 2 in Example 1;

[0037] Figure 6 This is a schematic diagram of the structure of the vent hole one of the present invention;

[0038] Figure 7 This is a schematic diagram of the structure of Example 2;

[0039] Figure 8 for Figure 7 A magnified structural diagram of part B in the middle section;

[0040] Figure 9 This is a schematic diagram showing the direction of cold air intake in Example 2;

[0041] Figure 10 This is a schematic cross-sectional view of the heat insulation cover 2 in Example 2;

[0042] Figure 11 This is a schematic diagram of the structure of the third vent hole of the present invention.

[0043] In the diagram: 1-Radial flow turbine; 11-Turbine housing; 111-Turbine housing axial stop; 112-Heat shield radial stop; 12-Radial flow turbine; 121-Turbine back plate; 2-Centrifugal compressor; 21-Compressor housing; 22-Centrifugal impeller; 3-Bearing system; 31-Sealing structure; 32-Anti-negative pressure oil leakage structure; 33-Floating bearing; 34-Thrust bearing; 35-Shaft; 4-Thermal management structure; 41-Heat shield one; 411-Outer edge of heat shield one; 412-Inner edge of heat shield one; 413-Axial section of heat shield one; 414-Radial section of heat shield one; 415-Ventilation hole one; 42-Heat shield two; 421-Outer edge of heat shield two; 422-Inner edge of heat shield two; 43-Heat shield three; 431- 432 - Outer edge of heat shield 3; 433 - Inner edge of heat shield 3; 434 - Vent hole 2; 45 - Cold air nozzle; 46 - Heat insulation cavity 1; 47 - Heat insulation cavity 2; 48 - Annular cooling groove; 49 - Heat insulation cavity 3; 481 - Inner platform of annular cooling groove; 482 - Inner wall of annular cooling groove; 483 - Turbidity element; 5 - Bearing body; 51 - Bearing body volute end wall; 52 - Inner stop of bearing body; 53 - Vent gap 1; 54 - Cold air hole; 55 - Lubricating oil hole; 56 - Bearing seat hole; 57 - Lubricating oil cooling cavity; 58 - Bearing body inlet flange face; 581 - Cold air hole inlet; 582 - Lubricating oil hole inlet; 59 - Oil and gas flange; 591 - Oil inlet nozzle; 6 - Bolt pressure plate structure; 84 - Vent gap 2; 93 - Vent hole 3. Detailed Implementation

[0044] 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.

[0045] Example 1,

[0046] like Figures 1 to 6 As shown, the turbocharger thermal management structure includes: a radial turbine 1, a centrifugal compressor 2, a bearing system 3, and a thermal management structure 4. The radial turbine 1 includes a turbine housing 11 and a radial turbine 12. The centrifugal compressor 2 includes a compressor housing 21 and a centrifugal impeller 22. The bearing system 3 includes a sealing structure 31, an anti-negative pressure oil leakage structure 32, a floating bearing 33, a thrust bearing 34, a shaft 35, and a bearing body 5 that supports these components. The thermal management structure 4 is located between the radial turbine 1 and the bearing body 5.

[0047] The thermal management structure 4 includes: heat insulation cover 1 41, heat insulation cover 2 42, heat insulation cover 3 43, cold air vent 54 and cold air nozzle 44. Heat insulation cover 1 41, heat insulation cover 2 42 and heat insulation cover 3 43 are all rotating metal sheets with a thickness of 0.8-1.5mm.

[0048] A heat insulation cavity 46 is formed between heat insulation cover 41 and heat insulation cover 42; a heat insulation cavity 47 is formed between heat insulation cover 42, heat insulation cover 43 and bearing housing volute end wall 51; a heat insulation cavity 49 is formed between heat insulation cover 43 and an annular cooling groove 48 provided on bearing housing 5.

[0049] The outer edge 411 of the heat shield mates with the axial stop 111 of the turbine housing, and the inner edge 412 of the heat shield mates with the stop 52 inside the bearing body. Under the pressure of the axial force, both mating positions are in a pressed state.

[0050] The gap between the axial section 413 of the heat shield and the radial stop 112 of the heat shield is designed to be between 0.5 and 1.0 mm, and the gap between the radial section 414 of the heat shield and the turbine back plate 121 is set to be between 0.5 and 1.0 mm.

[0051] Ventilation holes 415 are evenly arranged around the circumference of the axial section 413 of the heat insulation cover. The diameter of the ventilation holes 415 is 1-3mm and the number is 6-18. The ventilation holes 415 are close to the outer edge 411 of the heat insulation cover.

[0052] The outer edge 421 of the second heat shield can be pressed together with the inner wall of the axial section 413 of the first heat shield by axial force. A ventilation gap 53 is left between the inner edge 422 of the second heat shield and the stop 52 in the bearing body. The gap size of the ventilation gap 53 is 0.5-1.5mm.

[0053] The outer edge 431 of the heat insulation cover three is designed to mate with the outer edge 411 of the heat insulation cover one and be pressed together by axial force. The inner edge 432 of the heat insulation cover three mates with the inner platform 481 of the annular cooling groove. Under the pressing action of axial force, both mating positions are in a pressed state. The heat insulation cover three 43 is provided with a second vent 433. There is one second vent 433, and the diameter is 2-5mm. When installing the heat insulation cover three 43, ensure that the phase of the second vent 433 is 180° with the phase of the cooling air hole 54.

[0054] The bearing body 5 is provided with a lubricating oil hole 55, a bearing seat hole 56, a lubricating oil cooling chamber 57 and a cooling air hole 54. One end of the cooling air hole 54 is set on the inner wall surface 482 of the annular cooling groove, and the other end is set on the inlet flange surface 58 of the bearing body. The minimum diameter of the cooling air hole 54 is set to 2-5mm.

[0055] The inner wall surface 482 of the annular cooling tank is circumferentially distributed with interference flow elements 483. The interference flow elements 483 can be pits, grooves, raised cylinders, raised square pillars, and raised ribs.

[0056] There are two through holes on the inlet flange face 58 of the bearing body. In addition to the air inlet 581, there is also a lubricating oil inlet 582. The minimum distance between the air inlet 581 and the lubricating oil inlet 582 is not less than 2mm.

[0057] An oil-gas flange 59 is fitted on the outer side of the bearing housing inlet flange face 58. The oil-gas flange 59 also has two through holes, which are respectively connected to the lubricating oil inlet 582 and the cooling air inlet 581. An oil inlet 591 and a cooling air nozzle 44 are respectively installed on the oil-gas flange 59 and are respectively interference-fitted to the inner wall of the lubricating oil hole 55 and the cooling air hole 54. The inner diameter of the cooling air nozzle 44 is set to 2-5mm.

[0058] A bolt clamping plate structure 6 is provided between the turbine housing 11 and the bearing body 5. Through this structure, the turbine housing 11, heat shield 1 41, heat shield 2 42 and heat shield 3 43 are pressed together and assembled on the bearing body 5.

[0059] The working principle of this device is as follows:

[0060] The structure of this invention consists of a triple thermal barrier formed by a heat shield 41, a second heat shield 42, and a third heat shield 43. Compared with traditional heat insulation technology, this significantly increases the thermal resistance from the turbine flow channel to the bearing body 5 and reduces the heat transfer to the bearing body 5. On the other hand, the triple heat shield, together with the cooling air hole 54, constitutes the thermal management structure 4. Cooling air is supplied to the thermal management structure 4 from the intercooler or an external air source. After passing through the cooling air nozzle 44 and the cooling air hole 54, the cooling air enters the annular cooling groove 48 and flows along the flow paths on both sides of the annular cooling groove 48. It then flows into the second heat insulation cavity 47 through the second vent 433 on the third heat shield 43, which is 180° phase with the cooling air hole 54. As the cooling air flows within the annular cooling groove 48, it cools the heat transferred from the turbine housing 11 to the bearing housing 5. Furthermore, the cooling effect is enhanced by the turbulence element 483, solving the problem of cooling this part of the transmission path in traditional turbocharger cooling technology. Thirdly, the cooling air entering the second heat insulation chamber 47 gradually drives the outflow of high-temperature gas caused by thermal radiation and conduction within the chamber. This gas flows into the first heat insulation chamber 46 through the ventilation gap 53, further driving the outflow of hot gas within the first heat insulation chamber 46, and exiting the first heat insulation chamber 46 through the vent hole 415 on the heat insulation cover 41. This process utilizes the cooling... The cooling system expels the high-temperature gas from the insulation cavity, thereby significantly reducing the gas temperature inside the insulation cavity. This greatly improves the problem of high gas temperature inside the insulation cavity in traditional insulation methods, and will further reduce heat transfer from the turbine flow channel to the bearing body 5. Fourthly, during the continuous cooling process, the gas flowing out from the vent hole 415 is at a lower temperature, which will further expel the high-temperature gas between the axial section 413 of the insulation cover and the radial stop 112 of the insulation cover, thereby reducing the gas temperature on the walls of the axial section 413 of the insulation cover and the radial stop 112 of the insulation cover, thus reducing heat transfer in these two areas, which is beneficial to further reduce the thermal load on the bearing body 5.

[0061] This embodiment features a simple structure, convenient implementation, and low cost. It can achieve multiple reductions in heat transfer from the turbine to the bearing housing in a single structure, thereby significantly improving the risk of oil coking and lubrication failure caused by excessive heat load on the bearing housing.

[0062] Example 2:

[0063] like Figures 7 to 11 As shown, the difference from Embodiment 1 lies in the heat insulation cover 41 and the heat insulation cover 42;

[0064] A heat insulation cavity 46 is formed between heat insulation cover 41 and heat insulation cover 42; a heat insulation cavity 47 is formed between heat insulation cover 42, heat insulation cover 43 and bearing housing volute end wall 51.

[0065] The outer edge 411 of the heat shield is pressed against the axial stop 111 of the turbine housing. A ventilation gap 84 is left between the inner edge 412 of the heat shield and the stop 52 inside the bearing body. The size of the ventilation gap 84 is 0.5-1.5mm. The projected area of ​​the heat shield 41 covering the bearing body 5 should be as large as possible.

[0066] The outer edge 421 of the second heat shield can be interference-fitted with the inner wall of the axial section 413 of the first heat shield, or it can be designed to fit with the outer edge 411 of the first heat shield and be pressed together by axial force. The inner edge 422 of the second heat shield is tightly fitted with the stop 52 in the bearing body. A third vent 93 is provided on the second heat shield 42, and the third vent 93 is 180° out of phase with the second vent 433 provided on the third heat shield 43. There is one third vent 93, and its diameter is 2-5mm.

[0067] The working principle of this device is as follows:

[0068] Example 2 consists of a triple heat shield structure composed of heat shield 1 41, heat shield 2 42 and heat shield 3 43, which together with the cold air vent 54 constitute the heat management structure 4.

[0069] Cooling air is supplied to the thermal management structure 4 from the intercooler or an external air source. After passing through the air nozzle 44 and air orifice 54, the cooling air enters the annular cooling groove 48 and flows along the flow paths on both sides of the annular cooling groove 48. It then flows into the heat insulation cavity 47 through the vent 433 on the heat insulation cover 43, which is 180° phase with the air orifice 54. During its flow in the annular cooling groove 48, the cooling air can cool the heat transferred from the turbine housing 11 to the bearing housing 5, and the cooling effect is enhanced by the flow-deflecting element 483, solving the problem of cooling this part of the transmission path in traditional turbocharger cooling technology.

[0070] The cooling gas entering the second heat insulation cavity 47 gradually expels the high-temperature gas outflow caused by thermal radiation and heat conduction in the cavity. It flows into the first heat insulation cavity 46 through the third vent 93 and further drives the hot gas outflow in the first heat insulation cavity 46. It then enters the gap between the first heat insulation cavity 41 and the turbine back plate 121 through the second vent gap 84 on the inner edge of the first heat insulation cover 41. In this process, the cooling gas is used to expel the high-temperature gas in the heat insulation cavity, thereby significantly reducing the gas temperature in the heat insulation cavity. This greatly improves the problem of high gas temperature in the heat insulation cavity in traditional heat insulation methods and further reduces the heat transfer from the turbine flow channel to the bearing body 5.

[0071] During the continuous cooling process, the gas flowing out from the ventilation gap 84 is at a lower temperature, which will further expel the high-temperature gas between the heat shield 41 and the turbine back plate 121, thereby reducing the gas temperature of the radial section 414 of the heat shield and thus reducing the heat transfer from the heat shield 41 to the bearing body 5; at the same time, it also reduces the gas temperature near the turbine back plate 121, which helps to reduce the thermal stress at the turbine back plate 121.

[0072] 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 thermal management structure, characterized in that: It includes a radial turbine (1), a centrifugal compressor (2) and a bearing system (3) connected together, and a thermal management structure (4) is provided between the radial turbine (1) and the bearing system (3). The thermal management structure (4) includes a heat shield 1 (41), a heat shield 2 (42), and a heat shield 3 (43) arranged in the shape of a rotating metal sheet on the turbine back plate (121). A heat insulation cavity 1 (46) is formed between the heat shield 1 (41) and the heat shield 2 (42). A heat insulation cavity 2 (47) is formed between the heat shield 2 (42) and the heat shield 3 (43). A heat insulation cavity 3 (49) is formed between the heat shield 3 (43) and the annular cooling groove (48). The heat insulation cavity 1 (46) is connected to the gap at the turbine back plate (121). The heat insulation cavity 3 (49) is connected to a cold air hole (54). The heat insulation cavity three (49), heat insulation cavity two (47) and heat insulation cavity one (46) are sequentially connected by an air guiding structure; The air guiding structure includes a vent hole (415) that is uniformly opened along the circumferential direction on an axial section (413) of the heat shield to connect the heat insulation cavity (46) to the gap of the turbine back plate (121). The vent hole (415) is located near the outer edge (411) of the heat shield. The outer edge (421) of the second heat shield is pressed tightly against the inner wall of the axial section (413) of the first heat shield along the axial direction. The inner edge (422) of the second heat shield and the stop (52) inside the bearing body are provided with a ventilation gap (53) that connects the second heat shield (47) and the first heat shield (46). The gap size of the ventilation gap (53) is 0.5-1.5mm. The outer edge (431) of the heat insulation cover three is pressed and fitted with the outer edge (411) of the heat insulation cover one along the axial direction. The inner edge (432) of the heat insulation cover three is pressed and fitted with the inner side platform (481) of the annular cooling tank along the axial direction. The heat insulation cover three (43) is provided with a vent hole two (433) that connects the heat insulation cavity three (49) and the heat insulation cavity two (47). The vent hole two (433) and the cold air hole (54) are 180° apart. The air guiding structure includes a second air passage (84) located between the inner edge (412) of the heat shield and the stop (52) inside the bearing body, which connects the heat insulation cavity (46) to the gap of the turbine back plate (121). The gap size of the second air passage (84) is 0.5-1.5mm. The second heat insulation cover (42) is provided with a third vent (93) that connects the second heat insulation cavity (47) and the first heat insulation cavity (46). The third vent (93) and the second vent (433) are 180° apart.

2. The turbocharger thermal management structure according to claim 1, characterized in that: The outer edge (411) of the heat shield is pressed and fitted with the axial stop (111) of the turbine housing along the axial direction, the inner edge (412) of the heat shield is pressed and fitted with the stop (52) inside the bearing body along the axial direction, the gap between the axial section (413) of the heat shield and the radial stop (112) of the heat shield is 0.5-1.0mm, and the gap between the radial section (414) of the heat shield and the turbine back plate (121) is 0.5-1.0mm.

3. The turbocharger thermal management structure according to claim 1, characterized in that: The inner wall of the annular cooling tank (482) is uniformly distributed with several interference flow elements (483) in the circumferential direction.

4. The turbocharger thermal management structure according to claim 3, characterized in that: The disturbance element (483) includes a groove or a protrusion.

5. The turbocharger thermal management structure according to claim 1, characterized in that: The diameter of the first ventilation hole (415) is 1-3 mm and the number is 6-18; the diameter of the second ventilation hole (433) and the third ventilation hole (93) is 2-5 mm and the number is 1.

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