Turbocharger back-to-back compact impeller temperature control device and control method thereof

Abstract

The invention belongs to the technical field of engine turbochargers, and discloses a turbocharger back-to-back compact type impeller temperature control device and a control method thereof.The turbocharger back-to-back compact type impeller temperature control device comprises a middle body, and a gas compressor and a turbine are installed on the two sides of the middle body in a back-to-back mode; a heat insulation block is arranged on the back side of the turbine, a heat insulation cavity is formed in the heat insulation block, an air inlet and an air outlet of the heat insulation cavity communicate with the air inlet side of the air compressor through an external pipeline, the air compressor works to enable negative pressure to be formed on the air inlet side of the air compressor and act into the external pipeline, and part of airflow enters the heat insulation cavity through the external pipeline. Cold air in the heat insulation cavity dissipates heat of the back side of the turbine through heat exchange so as to reduce the transfer of heat of the turbine to the gas compressor, heat dissipation air carrying heat flows back to the gas inlet side of the gas compressor, and gas with a certain temperature flows into the gas compressor; according to the invention, the heat transfer rate of the heat of the turbine to the gas compressor can be reduced.

Description

Technical Field

[0001] The present invention belongs to the technical field of engine turbochargers, and in particular, relates to a back-to-back compact impeller temperature control device for a turbocharger and a control method thereof. Background Art

[0002] The function of a turbocharger is to provide more compressed air to the engine so that the engine can burn more fuel and thus generate more power, improve the engine's fuel economy, and reduce the harmful components of the engine's exhaust gas.

[0003] As the operating altitude of aircraft engines increases, the air density decreases and the power of naturally aspirated engines will drop significantly. Turbochargers ensure normal engine starting and takeoff through efficient energy recovery and aerodynamic optimization, becoming the core technology for aircraft engines to maintain performance under extreme conditions such as high altitude, high temperature, and plateau. However, due to the harsh conditions at high altitudes, turbochargers also face a series of technical problems.

[0004] When the air inlet temperature at the compressor end of the supercharger is too low in a high-altitude environment, the temperature of the compressed air may be lower than expected, causing the air temperature entering the combustion chamber to be too low, affecting the fuel atomization effect, causing incomplete combustion and reducing power output.

[0005] There are also problems with the lubrication of the supercharger in high-altitude environments. On the one hand, it is necessary to maintain a stable oil supply in drastically changing flight conditions (such as climbing and diving). Therefore, the oil circuit design needs to take into account both efficiency and weight, resulting in more complex pipelines. However, complex pipelines may introduce oil pressure drop and leakage risks. On the other hand, aircraft engines are extremely sensitive to weight, and the lubrication system needs to be highly integrated. Based on the above problems, the superchargers currently used do not use the traditional immersion lubrication and floating bearing combination method, but use ball bearings and oil mist, and the ball bearings are arranged on one side of the compressor, which results in the loss of the thermal insulation function of the traditional intermediate.

[0006] In order to make up for the above defects, the current design (such as Figure 1-2 As shown in the figure, a multi-layer insulation gasket 8 is installed on the intermediate body for insulation. The installation is inconvenient, the deviation is too large and the reliability is poor. At the same time, compared with the traditional oil-cooled intermediate body, the insulation effect does not meet the ideal requirements. The back of the impeller will still be subjected to high heat transfer from the turbine end, resulting in local thermal stress. Long-term action will cause cracks on the back of the impeller. Summary of the invention

[0007] The main technical problem to be solved by the present invention is to provide a temperature control device and its control method for the back-to-back compact impeller of a turbocharger, which can reduce the temperature of the back of the impeller on the basis of the original supercharger, and at the same time introduce the gas at the front end of the compressor impeller into the intermediate body through the air flow pipeline, while improving the intermediate heat insulation effect, appropriately increasing the intake air temperature of the compressor, and solving the problem of too low intake air temperature at the compressor end at high altitudes.

[0008] To solve the above technical problems, the present invention provides the following technical solutions: A temperature control device for the back-to-back compact impeller of a turbocharger, including an intermediate body, a compressor and a turbine are installed back-to-back on both sides of the intermediate body, a heat insulation block is arranged on the back side of the turbine, a heat insulation chamber is opened inside the heat insulation block, the air inlet and outlet of the heat insulation chamber are communicated with the intake side of the compressor through an external pipeline, the compressor works to form a negative pressure on its intake side and act on the external pipeline, so that a part of the air flow enters the heat insulation chamber through the external pipeline, and the cold air in the heat insulation chamber dissipates heat to the back side of the turbine through heat exchange, so as to reduce the transfer of heat from the turbine to the compressor, and the heat-dissipating air carrying heat then flows back to the intake side of the compressor, so that the gas with a certain temperature flows into the compressor.

[0009] The following is a further optimization of the above technical solutions by the present invention: The heat insulation block is in a C-shaped structure.

[0010] Further optimization: The two ends of the heat insulation block are close to each other and are respectively provided with a heat insulation block air inlet and a heat insulation block air outlet, and the heat insulation block air inlet and the heat insulation block air outlet are respectively communicated with the heat insulation chamber.

[0011] Further optimization: The external pipeline includes an intake pipeline, one end of the intake pipeline is communicated with the heat insulation block air inlet, and the other end of the intake pipeline is communicated with a position inside the compressor close to the front end of the compressor intake.

[0012] Further optimization: The external pipeline further includes an exhaust pipeline, one end of the exhaust pipeline is communicated with the heat insulation block air outlet, and the other end of the exhaust pipeline is communicated with a position inside the compressor close to the inlet of the compressor impeller.

[0013] Further optimization: A gas throttle valve is serially installed on the intake pipeline, and the gas throttle valve is used to regulate the gas flow through the heat insulation chamber.

[0014] Further optimization: The heat insulation block adopts an integral structure, a connection disk is arranged at a position on the compressor housing of the compressor close to the heat insulation block; a support disk is arranged at a position on the turbine housing of the turbine close to the heat insulation block. After the compressor and the turbine are installed on the intermediate body, the connection disk and the support disk press both sides of the heat insulation block to fix and install the heat insulation block.

[0015] Further optimization: A plurality of heat-conducting honeycombs are respectively arranged on the left and right side surfaces of the heat-insulating block. The heat on the turbine needs to be transferred along the tortuous path on the outer wall of the heat-conducting honeycomb, significantly extending the heat conduction path and reducing the heat conduction efficiency.

[0016] Further optimization: There are a plurality of heat-conducting rib plates on the outer surface of the heat-insulating block. Each heat-conducting rib plate is arranged in a ring shape along the outer surface of the heat-insulating block, and a plurality of heat-conducting rib plates are arranged at equal intervals in sequence along the trend of the heat-insulating block; the heat-conducting rib plates are used to disperse thermal stress and increase the path length of heat conduction, enhancing thermal resistance and reducing heat conduction efficiency.

[0017] The present invention also provides a control method for a temperature control device of a back-to-back compact impeller of a turbocharger. Based on the above temperature control device of a back-to-back compact impeller of a turbocharger, it includes the following steps: S1. The exhaust gas emitted by the engine enters the turbine and drives the turbine and the compressor to work. The work of the compressor makes a negative value form on the intake side, and low-temperature air flows into the heat-insulating chamber through an external pipeline. At this time, the cold air dissipates the heat on the turbine through the principle of heat exchange, and the hot air after heat transfer flows into the compressor. S2. The gas flows unidirectionally in the heat-insulating chamber, reducing the rate of heat transfer from the turbine to the compressor. The air that has been heated in the heat-insulating chamber returns to the compressor and is used to appropriately adjust the intake air temperature of the compressor. S3. The special external structural shape of the heat-insulating block enables the heat of the turbine to be transferred along a tortuous path, significantly extending the heat conduction path and reducing the rate of heat transfer from the turbine to the compressor. S4. Regulate the gas throttle valve on the intake pipeline according to actual requirements to adjust the gas flow rate passing through the heat-insulating chamber, and realize the adjustment of the intake air temperature of the compressor.

[0018] The present invention adopts the above technical solutions and has at least the following beneficial effects: 1. The present invention innovatively uses the small negative pressure area formed at the front end of the impeller during the operation of the supercharger to realize the automatic circulation of gas, avoiding complex structural designs.

[0019] 2. On one side of the turbine in the present invention, the heat of the turbine is blocked by using an integral heat-insulating block to reduce the rate of heat transfer from the turbine to the compressor. Compared with the original method of bonding multiple heat-insulating gaskets, the assembly is simpler; at the same time, the method of pasting multiple heat-insulating gaskets results in a relatively large tolerance after axial assembly, and finally it is difficult to ensure the axial clearance. The integral heat-insulating block in the present invention can eliminate the cumulative assembly tolerance of the heat-insulating gasket, thereby ensuring the axial clearance of the supercharger and ensuring the performance of the supercharger.

[0020] 3. The heat insulation block of the present invention is positioned and installed by pressing the connecting plate and the supporting plate, which can better simplify the installation process and improve the installation efficiency.

[0021] 4. The various structural forms of the heat insulation block in the present invention can better isolate the heat transfer from the turbine end to the pressure end, and avoid thermal cracks on the back side of the compressor impeller.

[0022] 5. In the present invention, the air inlet and outlet of the insulation block are arranged at the farthest positions of the circumferential distribution on the insulation block, so that the path of gas flowing through the insulation block is the longest, and the heat exchange between the low-temperature air duct and the high-temperature air at the turbine end is more sufficient.

[0023] 6. The present invention adopts a gas circulation method to reduce the heat transfer from the turbine end to the compression end, while increasing the intake temperature of the compressor, solving the problem of too low compressor intake temperature in high-altitude application environments.

[0024] 7. The present invention arranges a gas throttle valve on the gas pipeline, which can adjust the gas flow through the insulation chamber according to actual needs. At this time, the intake temperature of the compressor is properly increased, so that the intake temperature of the compressor is properly adjusted, which solves the problem of the compressor intake temperature being too low in a high-altitude environment.

[0025] 8. The present invention innovatively utilizes the small negative pressure formed at the front end of the compressor impeller during the operation of the supercharger to drive the airflow to flow in one direction, so that the cold air enters the insulation block at the turbine end from the front end of the compressor, and enters the compressor after taking away part of the heat through heat exchange, which appropriately increases the compressor intake temperature and solves the problem of too low compressor intake temperature in a high-altitude environment. At the same time, the cold air enters the insulation block at the turbine end, and the structure of the insulation block better isolates the heat transfer from the turbine end to the compressor end, avoiding thermal cracks on the back side of the compressor impeller. The insulation block adopts an integral structure, which improves the original supercharger's method of pasting multiple layers of insulation gaskets. The assembly method using the insulation block is simpler and the installation accuracy can be better guaranteed.

[0026] The present invention is further described below in conjunction with the accompanying drawings and embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 It is a structural schematic diagram of a supercharger in the background technology; Figure 2 It is a partial enlarged view of the location of the thermal insulation gasket in the background technology; Figure 3 This is a schematic diagram of the overall structure of Example 1 of the present invention; Figure 4 This is a schematic diagram of the installation structure of the thermal insulation block in Example 1 of the present invention; Figure 5It is a partial enlarged view at the position of the heat insulation block in Embodiment 1 of the present invention; Figure 6 It is a schematic structural view of the heat insulation block in Embodiment 1 of the present invention; Figure 7 It is a schematic structural view of the heat insulation block in Embodiment 2 of the present invention.

[0028] In the figure: 1, ball bearing body; 2, compressor housing; 3, compressor air inlet passage; 4, compressor impeller inlet; 5, compressor impeller; 6, intermediate body; 7, back side of the wheel; 8, heat insulation gasket; 9, turbine housing; 10, front end of the compressor air inlet; 11, intake pipeline; 12, gas throttle valve; 13, heat insulation block; 14, heat insulation block air inlet; 15, heat insulation block air outlet; 16, heat-conducting honeycomb; 17, heat-conducting rib plate; 18, outlet pipeline; 19, heat insulation chamber; 20, compressor; 21, turbine; 22, coupling disc; 23, support disc. Specific embodiments

[0029] Embodiment 1: As Figure 3-6 shown: The back-to-back compact impeller temperature control device of the turbocharger includes an intermediate body 6. A compressor 20 and a turbine 21 are installed back-to-back on both sides of the intermediate body 6. A heat insulation block 13 is arranged on the back side of the turbine 21. A heat insulation chamber 19 is opened inside the heat insulation block 13. The air inlet and outlet of the heat insulation chamber 19 are communicated with the air inlet side of the compressor 20 through an external pipeline. When the compressor 20 works, a negative pressure is formed on its air inlet side and acts on the external pipeline, so that a part of the air flow enters the heat insulation chamber 19 through the external pipeline. The cold air in the heat insulation chamber 19 dissipates heat to the back side of the turbine 21 through heat exchange, so as to reduce the transfer of the heat of the turbine 21 to the compressor 20. The heat-dissipating air carrying heat then flows back to the air inlet side of the compressor 20, so that the gas with a certain temperature flows into the compressor 20.

[0030] In this embodiment, the overall structure of the compressor 20 includes a compressor housing 2. The compressor housing 2 is fixedly installed on the intermediate body 6. A compressor impeller 5 is rotatably installed at a position inside the compressor housing 2 close to the intermediate body 6. A compressor air inlet passage 3 is arranged on the front side of the compressor impeller 5 inside the compressor housing 2. A compressor impeller inlet 4 is arranged at a position where the compressor air inlet passage 3 is close to the compressor impeller 5.

[0031] A compressor air inlet front end 10 is arranged at the air inlet of the compressor air inlet passage 3 on the compressor housing 2; A compressor outlet is also arranged on the compressor housing 2.

[0032] With such a design, external air can enter the compressor intake passage 3 through the front end 10 of the compressor intake. At this time, the compressor impeller 5 rotates at a high speed within the compressor housing 2, creating a certain negative pressure value at the inlet 4 of the compressor impeller and sucking air into the compressor housing 2. After being compressed, the air is discharged through the compressor outlet to form high-pressure air.

[0033] In this embodiment, the overall structure of the turbine 21 includes a turbine housing 9. A turbine is rotatably installed within the turbine housing 9, and the turbine is in coaxial drive connection with the compressor impeller 5. The turbine housing 9 is provided with a turbine end intake port and a turbine end exhaust port.

[0034] With such a design, the exhaust gas emitted by the engine enters the turbine housing 9 through the turbine end intake port, and then the exhaust gas is discharged through the turbine end exhaust port. When the exhaust gas flows through the turbine housing 9, it is used to drive the turbine to rotate, and the rotation of the turbine synchronously drives the rotation of the compressor impeller 5.

[0035] In this embodiment, a ball bearing body 1 for supporting the rotation of the compressor impeller 5 and the turbine is provided within the compressor housing 2, and the ball bearing body 1 is fixedly installed within the compressor housing 2.

[0036] The heat insulation block 13 has a C-shaped structure, and the two ends of the heat insulation block 13 are close to each other and are respectively provided with a heat insulation block intake port 14 and a heat insulation block outlet port 15. The heat insulation block intake port 14 and the heat insulation block outlet port 15 are respectively communicated with the heat insulation chamber 19.

[0037] In this embodiment, the heat insulation block intake port 14 and the heat insulation block outlet port 15 are respectively arranged at the farthest positions in the circumferential distribution of the heat insulation chamber 19, so that the path of the gas flowing through the heat insulation chamber 19 is the longest, and the heat exchange between the low-temperature air in the heat insulation chamber 19 and the high-temperature air of the turbine 21 is more sufficient.

[0038] The peripheral pipeline includes an intake pipeline 11. One end of the intake pipeline 11 is communicated with the heat insulation block intake port 14, and the other end of the intake pipeline 11 is communicated with a position on the compressor intake passage 3 close to the front end 10 of the compressor intake.

[0039] The peripheral pipeline further includes an outlet pipeline 18. One end of the outlet pipeline 18 is communicated with the heat insulation block outlet port 15, and the other end of the outlet pipeline 18 is communicated with a position on the compressor intake passage 3 close to the inlet 4 of the compressor impeller.

[0040] With such a design, a certain negative pressure value is formed at the position of the compressor impeller inlet 4 during the operation of the supercharger, and the gas in the intake pipe 11, the heat insulation chamber 19, and the outlet pipe 18 flows unidirectionally. The low-temperature gas flows from the front end 10 of the compressor intake through the intake pipe 11 to the heat insulation block 13. At this time, the gas enters the heat insulation chamber 19 from the heat insulation block intake port 14. The cold air in the heat insulation chamber 19 dissipates the heat on the turbine 21 through the principle of heat exchange. After the heat transfer is completed, the hot air flows out from the heat insulation block outlet 15, and then through the diversion of the outlet pipe 18, finally, the gas with a certain temperature flows into the compressor impeller inlet 4 and then enters the compressor 20.

[0041] In this embodiment, the gas flows unidirectionally through the intake pipe 11, the heat insulation chamber 19, and the outlet pipe 18. The cold air in the heat insulation chamber 19 reduces the heat transfer from the turbine 21 to the compressor 20, thereby reducing the temperature at the position of the back side 7 of the compressor impeller 5 and avoiding the generation of thermal cracks at the position of the back side 7. The gas returns to the position of the compressor impeller inlet 4 after passing through the heat insulation chamber 19 in the heat insulation block 13. At this time, the gas temperature is appropriately increased, solving the problem of too low intake air temperature at the compressor 20 in the high-altitude environment.

[0042] A gas throttle valve 12 is serially installed on the intake pipe 11, which can adjust the gas flow rate passing through the heat insulation chamber 19 according to actual needs, ensuring that the intake air temperature of the compressor 20 can be appropriately adjusted to meet the requirements of the engine under different working conditions.

[0043] In this embodiment, the heat insulation block 13 adopts an integral structure, improving the original method of pasting multiple heat insulation gaskets 8 in the supercharger. The method of pasting multiple heat insulation gaskets 8 results in a relatively large tolerance after axial assembly, and finally, it is difficult to ensure the axial clearance. The assembly method using the heat insulation block 13 is simpler, and the installation accuracy can be better guaranteed.

[0044] The heat insulation block 13 is arranged between the compressor housing 2 and the turbine housing 9, and a connection disk 22 is arranged at the position of the compressor housing 2 close to the heat insulation block 13; a support disk 23 is arranged at the position of the turbine housing 9 close to the heat insulation block 13. After the compressor housing 2 and the turbine housing 9 are installed on the intermediate body 6, the connection disk 22 and the support disk 23 clamp both sides of the heat insulation block 13 to realize the fixed installation of the heat insulation block 13 without additional bolts and other fasteners, improving the installation efficiency.

[0045] In this embodiment, heat-conducting honeycombs 16 are respectively arranged on the left and right side surfaces of the heat insulation block 13. The heat on the turbine 21 needs to be transferred along the tortuous path on the outer wall of the heat-conducting honeycomb 16, significantly extending the heat conduction path and reducing the heat conduction efficiency.

[0046] In this embodiment, a plurality of heat-conducting honeycombs 16 are provided, and the plurality of heat-conducting honeycombs 16 are arranged at equal intervals in sequence along the direction of the heat-insulating block 13.

[0047] In this embodiment, the arrangement structure, size, quantity, etc. of the heat-conducting honeycombs 16 can be adjusted according to actual conditions to meet different requirements.

[0048] In summary, a back-to-back compact impeller temperature control device for a turbocharger according to the present invention mainly innovatively utilizes the negative pressure formed at the front end of the compressor impeller 5 during the operation of the supercharger to drive air flow into the intake pipe 11, the heat-insulating chamber 19, and the outlet pipe 18 and perform unidirectional flow; cold air enters the heat-insulating chamber 19 in the heat-insulating block 13 from the front end of the compressor, realizes taking away part of the heat and then enters the compressor 20, appropriately raises the intake air temperature of the compressor 20, solves the problem that the intake end temperature of the compressor 20 is too low in the high-altitude environment, and at the same time, the cold air enters the heat-insulating block 13, cooperates with the structure of the heat-insulating block 13, and better reduces the rate of heat transfer from the turbine 21 to the compressor 20, avoiding the generation of thermal cracks at the position of the back side 7 of the compressor impeller 5.

[0049] A gas throttle valve 12 is connected in series on the intake pipe 11, and during actual operation, the gas flow rate passing through the heat-insulating chamber 19 can be adjusted according to actual requirements to ensure that the intake end temperature of the compressor 20 can be appropriately adjusted to meet the requirements of the engine under different working conditions.

[0050] The overall structural design of the heat-insulating block 13 improves the way of pasting multiple heat-insulating gaskets 8 in the original supercharger, solves the problem that the tolerance after axial assembly of the original supercharger is relatively large and the final axial clearance is difficult to guarantee, and the assembly method of the heat-insulating block 13 adopted in this embodiment is simpler and the installation accuracy can be better guaranteed.

[0051] The present invention also provides a control method for a back-to-back compact impeller temperature control device of a turbocharger. Based on the above back-to-back compact impeller temperature control device of a turbocharger, the method includes the following steps: S1. The exhaust gas emitted by the engine enters the turbine 21 and drives the turbine 21 and the compressor 20 to work. When the compressor 20 works, a certain negative pressure value is formed at the position of the compressor impeller inlet 4. At this time, the low-temperature gas flows from the front end 10 of the compressor intake through the intake pipe 11 to the heat-insulating block 13, and the gas enters the heat-insulating chamber 19 from the heat-insulating block inlet 14. The cold air in the heat-insulating chamber 19 dissipates the heat on the turbine 21 through the heat exchange principle. After the heat transfer is completed, the hot air flows out from the heat-insulating block outlet 15, and then through the diversion of the outlet pipe 18, finally, the gas with a certain temperature flows into the compressor impeller inlet 4 and then enters the compressor 20.

[0052] In the step S1, the exhaust gas emitted by the engine enters the turbine housing 9 through the turbine end air inlet, and then the exhaust gas is discharged through the turbine end exhaust port. When flowing through the turbine housing 9, the exhaust gas is used to drive the turbine to rotate, and the rotation of the turbine synchronously drives the compressor impeller 5 to rotate; thereby realizing the synchronous operation of the turbine 21 and the compressor 20.

[0053] S2. The gas flows unidirectionally in the heat insulation chamber 19, reducing the rate of heat transfer from the turbine 21 to the compressor 20. And the air that has completed heating in the heat insulation chamber 19 returns to the position of the inlet of the compressor impeller 4. At this time, the gas temperature is appropriately increased, so that the intake air temperature of the compressor 20 is appropriately adjusted, solving the problem of too low intake air temperature at the compressor 20 in the high-altitude environment.

[0054] S3. The special external structural shape of the heat insulation block 13 enables the heat of the turbine 21 to be transferred along a tortuous path, significantly extending the heat conduction path, thereby reducing the rate of heat transfer from the turbine 21 to the compressor 20 and avoiding the generation of heat cracks at the back side 7 of the compressor impeller 5.

[0055] In the step S3, based on the above-mentioned embodiment 1, a plurality of heat-conducting honeycombs 16 are respectively arranged on the left and right side surfaces of the heat insulation block 13. The heat on the turbine 21 needs to be transferred along the tortuous path on the outer wall of the heat-conducting honeycomb 16, significantly extending the heat conduction path and reducing the heat conduction efficiency, thereby being able to avoid the generation of heat cracks at the back side 7 of the compressor impeller 5.

[0056] S4. By regulating the gas throttle valve 12 on the intake pipeline 11 according to actual requirements, it is possible to adjust the gas flow rate passing through the heat insulation chamber 19, realize appropriate adjustment of the intake air temperature of the compressor 20, and meet the requirements of the engine under different working conditions.

[0057] Embodiment 2: As Figure 7 shown, based on the above-mentioned embodiment 1, in this embodiment 2, the overall structure of the heat insulation block 13 can also adopt Figure 7 the structure shown. There are heat-conducting rib plates 17 on the outer surface of the heat insulation block 13. The heat-conducting rib plates 17 are arranged in a ring shape along the outer surface of the heat insulation block 13, and a plurality of heat-conducting rib plates 17 are provided. The plurality of heat-conducting rib plates 17 are arranged at equal intervals in sequence along the trend of the heat insulation block 13.

[0058] In this embodiment 2, the heat-conducting rib plates 17 can disperse the thermal stress, avoid warping or cracking caused by temperature gradient. At the same time, the heat-conducting rib plates 17 can increase the path length of heat conduction, effectively increase the thermal resistance, and reduce the heat conduction efficiency.

[0059] In this embodiment, the arrangement structure, size and quantity of the heat-conducting rib plates 17 can be adjusted according to actual requirements to meet different needs.

[0060] For those of ordinary skill in the art, according to the teachings of the present invention, changes, modifications, substitutions, and variations made to the embodiments without departing from the principles and spirit of the present invention still fall within the protection scope of the present invention.

Claims

1. Temperature control device for a back-to-back compact impeller of a turbocharger, comprising an intermediate body (6), with a compressor (20) and a turbine (21) mounted back-to-back on both sides of the intermediate body (6), characterized in that: The back side of the turbine (21) is provided with a heat insulation block (13). An insulation chamber (19) is formed inside the heat insulation block (13). The air inlet and outlet of the insulation chamber (19) are communicated with the air inlet side of the compressor (20) through an external pipeline. When the compressor (20) operates, a negative pressure is formed on its air inlet side and acts on the external pipeline, so that a part of the air flow enters the insulation chamber (19) through the external pipeline. The cold air in the insulation chamber (19) dissipates heat to the back side of the turbine (21) through heat exchange, so as to reduce the transfer of the heat of the turbine (21) to the compressor (20). The heat-dissipating air carrying heat then flows back to the air inlet side of the compressor (20), so that the gas with a certain temperature flows into the compressor (20).

2. The temperature control device for the back-to-back compact impeller of the turbocharger according to claim 1, characterized in that: The heat insulation block (13) has a C-shaped structure.

3. The temperature control device for the back-to-back compact impeller of a turbocharger according to claim 2, characterized in that: The two ends of the heat insulation block (13) are close to each other and are respectively provided with a heat insulation block air inlet (14) and a heat insulation block air outlet (15). The heat insulation block air inlet (14) and the heat insulation block air outlet (15) are respectively communicated with the insulation chamber (19).

4. The temperature control device for the back-to-back compact impeller of a turbocharger according to claim 3, characterized in that: The external pipeline includes an intake pipeline (11). One end of the intake pipeline (11) is communicated with the heat insulation block air inlet (14), and the other end of the intake pipeline (11) is communicated with a position inside the compressor (20) close to the front end (10) of the compressor air inlet.

5. The temperature control device for the back-to-back compact impeller of the turbocharger according to claim 4, characterized in that: The external pipeline further includes an exhaust pipeline (18). One end of the exhaust pipeline (18) is communicated with the heat insulation block air outlet (15), and the other end of the exhaust pipeline (18) is communicated with a position inside the compressor (20) close to the inlet (4) of the compressor impeller.

6. The temperature control device for the back-to-back compact impeller of a turbocharger according to claim 4, characterized in that: A gas throttle valve (12) is serially installed on the intake pipeline (11). The gas throttle valve (12) is used to regulate the gas flow rate passing through the insulation chamber (19).

7. The temperature control device for the back-to-back compact impeller of a turbocharger according to claim 1, characterized in that: The heat insulation block (13) adopts an integral structure. A connection disk (22) is arranged at a position on the compressor housing (2) of the compressor (20) close to the heat insulation block (13); a support disk (23) is arranged at a position on the turbine housing (9) of the turbine (21) close to the heat insulation block (13). After the compressor (20) and the turbine (21) are installed on the intermediate body (6), the connection disk (22) and the support disk (23) press both sides of the heat insulation block (13) to fixedly install the heat insulation block (13).

8. The temperature control device for the back-to-back compact impeller of a turbocharger according to claim 1, characterized in that: A plurality of heat-conducting honeycombs (16) are respectively arranged on the left and right side surfaces of the heat insulation block (13). The heat of the turbine (21) needs to be transferred along the zigzag path on the outer wall of the heat-conducting honeycomb (16), significantly extending the heat conduction path and reducing the heat conduction efficiency.

9. The temperature control device for the back-to-back compact impeller of a turbocharger according to claim 1, characterized in that: A plurality of heat-conducting rib plates (17) are arranged on the outer surface of the heat insulation block (13). Each heat-conducting rib plate (17) is arranged in a ring shape along the outer surface of the heat insulation block (13). The plurality of heat-conducting rib plates (17) are arranged at equal intervals in sequence along the direction of the heat insulation block (13); the heat-conducting rib plates (17) are used to disperse the thermal stress and at the same time increase the path length of heat conduction, improve the thermal resistance and reduce the heat conduction efficiency.

10. A control method for a temperature control device of a back-to-back compact impeller of a turbocharger, based on the temperature control device of the back-to-back compact impeller of a turbocharger according to any one of claims 1-9, characterized in that: Including the following steps: S1. The exhaust gas emitted by the engine enters the turbine (21) and drives the turbine (21) and the compressor (20) to work. When the compressor (20) works, a negative value is formed on the intake side, and the low-temperature air flows into the heat insulation chamber (19) through the peripheral pipeline. At this time, the cold air dissipates the heat on the turbine (21) through the heat exchange principle, and the hot air after heat transfer flows into the compressor (20). S2. The gas flows unidirectionally in the heat insulation chamber (19), reducing the rate of heat transfer from the turbine (21) to the compressor (20). The air heated in the heat insulation chamber (19) returns to the compressor (20) to appropriately adjust the intake temperature of the compressor (20). S3. The special external structural shape of the heat insulation block (13) enables the heat of the turbine (21) to be transferred along a tortuous path, significantly extending the heat conduction path and reducing the rate of heat transfer from the turbine (21) to the compressor (20). S4. Regulate the gas throttle valve (12) on the intake pipeline (11) according to actual needs to adjust the gas flow rate passing through the heat insulation chamber (19) and achieve adjustment of the intake temperature of the compressor (20).

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