An adjustable two-stage turbocharger system test platform

Abstract

The present invention provides an adjustable two-stage turbocharger system test platform, including a high-pressure stage supercharger and a low-pressure stage supercharger, which can simultaneously measure the performance of a single high-pressure and low-pressure stage supercharger and the performance of a two-stage supercharging system, and can work in an open cycle mode or a self-circulation mode, and test and evaluate the performance and matching of the turbocharger in advance, so as to provide data support for the matching of the supercharger and the internal combustion engine. By adjusting the first bypass valve and the second bypass valve, the boost ratio can be continuously adjustable, and the performance of the two-stage turbocharger can be tested at different openings of the bypass valve. For the layout of the front intake ducts of the two low-pressure stage turbochargers, the air flow and pressure distributed to the two low-pressure stage turbochargers are basically consistent, so as to ensure the accuracy and stability of the test.

Description

Technical Field

[0001] The invention relates to the field of supercharging system test platforms, and in particular to an adjustable two-stage turbocharger system test platform. Background Art

[0002] With the development of internal combustion engine technology and increasingly stringent emission regulations, superchargers are required to have the highest possible boost pressure and wide operating range. Adjustable two-stage supercharging technology has become one of the most advanced supercharging technologies today due to its advantages of high boost ratio, wide flow range and high efficiency. The platform test of the turbocharger system is an indispensable means to detect the performance and reliability of the supercharging system and improve the success rate of the supercharging system. At the same time, the platform test data can provide a basis for product optimization and upgrading.

[0003] The two-stage boost test method has been studied at home and abroad, but no standard test method has been formulated. At present, for the two-stage boost system, a test platform with high flexibility and wide application range is needed to meet the needs of production and research. Summary of the invention

[0004] The present invention provides an adjustable two-stage turbocharging system test platform to solve the above problems.

[0005] An adjustable two-stage turbocharger system test platform includes: a combustion chamber, a high-pressure stage supercharger and a low-pressure stage supercharger;

[0006] The high-pressure stage supercharger includes a high-pressure stage compressor and a high-pressure stage turbine, and the low-pressure stage supercharger includes a first supercharger and a second supercharger, the first supercharger includes a first compressor and a first turbine, and the second supercharger includes a second compressor and a second turbine;

[0007] The inlet end of the combustion chamber is connected to the fan, and the outlet end of the combustion chamber is connected to the inlet end of the high-pressure stage turbine, and the outlet end of the high-pressure stage turbine is connected to the inlet end of the first turbine and the inlet end of the second turbine; the outlet end of the first compressor and the outlet end of the second compressor are both connected to the inlet end of the high-pressure stage compressor, and the outlet end of the high-pressure stage compressor is connected to the inlet end of the combustion chamber, and a bleed valve is provided between the outlet end of the high-pressure stage compressor and the inlet end of the combustion chamber.

[0008] Furthermore, a high-pressure outlet pipe is provided at the outlet end of the high-pressure stage turbine, a first inlet pipe is provided at the inlet end of the first turbine, and a second inlet pipe is provided at the inlet end of the second turbine. The high-pressure outlet pipe, the first inlet pipe and the second inlet pipe are in the same plane and parallel to each other.

[0009] Furthermore, it also includes a main pipe, a branch pipe, a first branch pipe and a second branch pipe, the axis of the high-pressure outlet pipe is located between the first inlet pipe and the second inlet pipe and close to the second inlet pipe, the inlet end of the main pipe is connected to the high-pressure outlet pipe, and the outlet end of the main pipe is inclined toward the first inlet pipe;

[0010] The inlet end of the branch pipe is arranged at the midpoint of the length direction of the branch pipe, the outlet end of the main pipe is connected to the inlet end of the branch pipe, the branch pipe is perpendicular to the main pipe, one end of the branch pipe is connected to the first inlet pipe through the first branch pipe, and the other end of the branch pipe is connected to the second inlet pipe through the second branch pipe;

[0011] The sum of the lengths of the second inlet pipe and the second branch pipe is equal to the sum of the lengths of the first inlet pipe and the first branch pipe, and the angle between the axis of the second inlet pipe and the axis of the second branch pipe is smaller than the angle between the axis of the first inlet pipe and the axis of the first branch pipe.

[0012] Furthermore, a first bypass pipe is provided between the outlet end of the combustion chamber and the outlet end of the high-pressure stage turbine, and a first bypass valve is provided on the first bypass pipe.

[0013] Furthermore, a second bypass pipeline is provided between the outlet and the inlet of the high-pressure stage compressor, and a second bypass valve is provided on the second bypass pipeline.

[0014] Furthermore, the outlet end of the first compressor is connected to a first intercooler, and the outlet end of the second compressor is connected to a second intercooler.

[0015] Furthermore, a first turbine inlet valve is provided at the inlet end of the first turbine, and a first compressor outlet valve is provided at the outlet end of the first compressor.

[0016] The present invention discloses an adjustable two-stage turbocharger system test platform, which can simultaneously measure the performance of a single high-pressure and low-pressure turbocharger and the performance of a two-stage turbocharger system, and can work in an open cycle mode or a self-circulation mode, and can test and evaluate the performance and matching of the turbocharger in advance, and provide data support for the matching of the turbocharger and the internal combustion engine. By adjusting the first bypass valve and the second bypass valve, the boost ratio can be continuously adjustable, and the performance of the two-stage turbocharger can be tested at different openings of the bypass valve. For the layout of the front intake ducts of the two low-pressure stage turbochargers, the air flow and pressure distributed to the two low-pressure stage turbochargers are basically consistent, ensuring the accuracy and stability of the test. 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 work.

[0018] Figure 1 A schematic diagram of a turbine test platform process disclosed in an embodiment of the present invention;

[0019] Figure 2 A schematic diagram of the structure of a turbine test platform disclosed in an embodiment of the present invention;

[0020] Figure 3 This is a schematic diagram of the connection between the high-pressure stage supercharger and the low-pressure stage supercharger disclosed in an embodiment of the present invention.

[0021] In the figure: 1, fan; 2, turbine end intake valve; 3, combustion chamber; 4, first bypass valve; 5, first compressor outlet valve; 6, first turbine inlet valve; 7, first supercharger; 71, first compressor; 72, first turbine; 721, first inlet pipeline; 8, second supercharger; 81, second compressor; 82, second turbine; 821, second inlet pipeline; 9, first flow meter; 10, second flow meter; 11, second intercooler; 12, first intercooler; 13, high-pressure stage supercharger; 131, high-pressure stage compressor; 132, high-pressure stage turbine; 133, high-pressure outlet pipeline; 134, first bypass pipeline; 135, second bypass pipeline; 14, orifice flowmeter; 15, second bypass valve; 16, bleed valve; 17, self-circulation valve; 18, main pipe; 19, branch pipe; 20, first branch pipe; 21, second branch pipe. 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] like Figure 1 , Figure 2 As shown, an adjustable two-stage turbocharger system test platform includes: a combustion chamber 3, a high-pressure stage supercharger 13 and a low-pressure stage supercharger;

[0024] The high-pressure stage supercharger 13 includes a high-pressure stage compressor 131 and a high-pressure stage turbine 132, and the low-pressure stage supercharger includes a first supercharger 7 and a second supercharger 8, wherein the first supercharger 7 includes a first compressor 71 and a first turbine 72, and the second supercharger 8 includes a second compressor 81 and a second turbine 82;

[0025] The inlet end of the combustion chamber 3 is connected to the fan 1, and the outlet end of the combustion chamber 3 is connected to the inlet end of the high-pressure stage turbine 132, and the outlet end of the high-pressure stage turbine 132 is connected to the inlet end of the first turbine 72 and the inlet end of the second turbine 82; the outlet end of the first compressor 71 and the outlet end of the second compressor 81 are both connected to the inlet end of the high-pressure stage compressor 131, and the outlet end of the high-pressure stage compressor 131 is connected to the inlet end of the combustion chamber 3, and a vent valve 16 is provided between the outlet end of the high-pressure stage compressor 131 and the inlet end of the combustion chamber 3.

[0026] In the open cycle mode, that is, the turbine-end intake valve 2 is open, the exhaust valve 16 is open, and the self-circulation valve 17 is closed, the fan 1 provides air to the pipeline to drive the entire supercharging system for the initial operation test of the supercharger and the turbine characteristic test. The turbine-end intake valve 2 is used to adjust the flow and pressure of the compressed air entering the pipeline in the open cycle mode.

[0027] In the self-circulation mode, that is, the turbine-end intake valve 2 is closed, the exhaust valve 16 is closed, and the self-circulation valve 17 is opened, the combustion chamber 3 generates high-temperature and high-pressure gas by injecting natural gas for combustion to drive the entire supercharger system.

[0028] The first supercharger 7 and the second supercharger 8 are connected in parallel in the pipeline, the inlet of the first turbine and the second turbine are connected to the outlet of the high-pressure stage turbine 132 through the pipeline, the outlet of the first turbine and the second turbine are connected to the atmosphere, the inlet of the first compressor and the second compressor are connected to the atmosphere, and the outlet of the first compressor and the second compressor are connected to the adjustable intercooler through the pipeline; the first intercooler and the second intercooler are both adjustable intercoolers, the outlet end of the first compressor 71 is connected to the first intercooler 12, and the outlet end of the second compressor 81 is connected to the second intercooler 11.

[0029] The intercooler is used to cool the compressed air at the outlet of the compressor of the low-pressure stage supercharger. The two intercoolers are equipped with cooling water regulating valves. By adjusting the flow of cooling water entering the intercooler, the inlet air temperature of the high-pressure stage supercharger 13 compressor can be adjusted;

[0030] A first flow meter 9 is disposed at the inlet of the first supercharger, and a second flow meter 10 is disposed at the inlet of the second supercharger. Both the first flow meter 9 and the second flow meter 10 are double-twist flow meters.

[0031] The outlet of the high-pressure stage compressor is connected to the orifice flowmeter 14 through a pipeline. The orifice flowmeter 14 is used to measure the air flow rate at the outlet of the high-pressure stage supercharger 13 compressor.

[0032] A first bypass pipe 134 is provided between the outlet of the combustion chamber 3 and the outlet of the high-pressure stage turbine 132, and a first bypass valve 4 is provided on the first bypass pipe 134. By adjusting the opening of the first bypass valve 4, the flow rate of high-temperature gas entering the high-pressure stage supercharger is adjusted.

[0033] A second bypass pipe 135 is provided between the outlet and the inlet of the high-pressure compressor 132, and a second bypass valve 15 is provided on the second bypass pipe 135 to adjust the inlet flow of the high-pressure supercharger 13 compressor, thereby adjusting the total pressure ratio of the two-stage supercharging system.

[0034] The self-circulation valve 17 is connected in parallel with the turbine-end intake valve 2. In the open circulation mode, the self-circulation valve 17 is closed and the turbine-end intake valve 2 is opened. In the self-circulation mode, the self-circulation valve 17 is opened and the turbine-end intake valve 2 is closed. One side of the self-circulation valve 17 is connected to the orifice flowmeter 14 through a pipeline, and the other side is connected to the combustion chamber 3 through a pipeline, and is used to adjust the air flow at the compressor outlet of the high-pressure stage supercharger 13 during the performance test.

[0035] The inlet end of the first turbine 72 is provided with a first turbine inlet valve 6, and the outlet end of the first compressor 71 is provided with a first compressor outlet valve 5. By opening or closing the first compressor outlet valve 5 and the first turbine inlet valve 6 at the same time, free conversion of "1 high pressure stage + 2 low pressure stages" or "1 high pressure stage + 1 low pressure stage" can be achieved to meet different test requirements.

[0036] The working process of the present invention is as follows:

[0037] 1. The high-temperature gas in the combustion chamber enters the turbine end of the high-pressure stage supercharger, driving the high-pressure stage turbine to rotate. At the same time, the compressor of the high-pressure stage supercharger inhales the compressed and cooled air driven by the turbine.

[0038] Second, after the high-temperature gas passes through the high-pressure stage supercharger turbine, it enters the turbine end of the two low-pressure stage superchargers, driving the low-pressure stage turbine to rotate;

[0039] 3. Driven by the low-pressure stage turbine, the outside air is sucked into the compressors of the two low-pressure stage superchargers through two twisted-wire flow meters;

[0040] 4. The air is compressed by two low-pressure stage superchargers and then enters two intercoolers respectively;

[0041] 5. The cooled compressed air enters the compressor end of the high-pressure stage supercharger and is compressed again;

[0042] 6. The gas after secondary compression passes through the orifice flowmeter and the self-circulation valve and enters the combustion chamber.

[0043] During the test, by adjusting the compressor bypass valve, part of the air can bypass the compressor inlet of the high-pressure stage supercharger and enter the combustion chamber directly; by adjusting the turbine exhaust bypass valve, part of the high-temperature gas can bypass the turbine end inlet of the high-pressure stage supercharger and enter the low-pressure stage supercharger directly, thereby realizing continuous adjustment of the system's boost ratio and further studying the optimal overall efficiency operating line of the two-stage supercharging system.

[0044] The present invention can realize multiple adjustable two-stage turbocharger system tests in the form of "1 high pressure stage + 2 low pressure stages" and "1 high pressure stage + 1 low pressure stage"; the performance of a single high and low pressure stage turbocharger and the performance of a two-stage turbocharging system can be measured simultaneously. The performance of a two-stage turbocharger with a large flow rate (flow rate 1-10kg / s) and a high boost ratio (the highest boost ratio can reach 15) can be tested, and it can work in an open cycle mode or in a self-circulation mode; a turbine exhaust bypass valve and a compressor bypass valve are installed between the high and low pressure stage turbochargers, and the boost ratio can be continuously adjustable by adjusting the opening of the turbine exhaust bypass valve and the compressor bypass valve, and the performance of the two-stage turbocharger under different turbine exhaust bypass valve and compressor bypass valve openings can be tested; the inlet gas temperature of the high pressure stage compressor can be controlled, and this is achieved by adjusting the water flow rate through the intercooler water cooling regulating valve; the present invention tests and evaluates the performance and matching of the two-stage turbocharger in advance, and provides data support for the matching of the turbocharger and the diesel engine.

[0045] The present invention has a compact spatial structure, reasonable layout, high reliability, and can meet the needs of long-term and frequent tests of the supercharger. In order to complete the layout of the test platform in a limited space and meet the purpose of compact spatial structure, the pipeline connecting the high-pressure stage supercharger and the low-pressure stage supercharger is designed asymmetrically. At the same time, in order to ensure the consistency of the air flow distributed to the two low-pressure stage turbochargers, the present invention designs the high-pressure stage supercharger and the low-pressure stage supercharger as follows:

[0046] A high-pressure outlet pipe 133 is provided at the outlet end of the high-pressure stage turbine 132, a first inlet pipe 721 is provided at the inlet end of the first turbine 72, and a second inlet pipe 821 is provided at the inlet end of the second turbine 82. The high-pressure outlet pipe 133, the first inlet pipe 721 and the second inlet pipe 821 are in the same plane and parallel to each other.

[0047] It also includes a main pipe 18, a branch pipe 19, a first branch pipe 20 and a second branch pipe 21. The axis of the high-pressure outlet pipe 133 is located between the first inlet pipe 721 and the second inlet pipe 821 and close to the second inlet pipe 821. The inlet end of the main pipe 18 is connected to the high-pressure outlet pipe 133, and the outlet end of the main pipe 18 is inclined toward the first inlet pipe 721.

[0048] The inlet end of the branch pipe 19 is located at the midpoint of the length direction of the branch pipe 19, the outlet end of the main pipe 18 is connected to the inlet end of the branch pipe 19, the branch pipe 19 is perpendicular to the main pipe 18, one end of the branch pipe 19 is connected to the first inlet pipe 721 through the first branch pipe 20, and the other end of the branch pipe 19 is connected to the second inlet pipe 821 through the second branch pipe 21;

[0049] The sum of the lengths of the second inlet pipe 821 and the second branch pipe 21 is equal to the sum of the lengths of the first inlet pipe 721 and the first branch pipe 20 , and the angle between the axis of the second inlet pipe 821 and the axis of the second branch pipe 21 is smaller than the angle between the axis of the first inlet pipe 721 and the axis of the first branch pipe 20 .

[0050] The pipeline arrangement before the turbine intake of two low-pressure stage turbochargers of the present invention is to first tilt the main pipe 18 at a certain angle, and then coordinate the bending of the two branch pipes at different angles to achieve the equality of the overall length of the two branch pipes, thereby ensuring that the air flow distributed to the two low-pressure stage turbochargers is basically the same. After actual testing, the speed deviation of the two low-pressure stage turbochargers during operation does not exceed ±2%, the flow deviation does not exceed 3%, and the pressure ratio does not exceed 2%.

[0051] The test process of the turbine test platform disclosed in the present invention is as follows:

[0052] 1. The high-temperature gas in the combustion chamber 3 enters the turbine end of the high-pressure stage supercharger 13, driving the high-pressure stage turbine 132 to rotate. At the same time, the compressor 131 of the high-pressure stage supercharger sucks in the compressed and cooled air driven by the turbine. [Measure the inlet temperature T of the high-pressure stage supercharger turbine TH , High-pressure stage turbocharger turbine inlet flow G T , Pressure at the high-pressure stage turbocharger turbine inlet P TH , the pressure at the outlet of the high-pressure stage turbocharger turbine is P 2H ]

[0053] Second, after the high-temperature gas passes through the high-pressure stage supercharger turbine 132, it enters the turbine ends 72 and 82 of the low-pressure stage supercharger, driving the low-pressure stage turbine to rotate;

[0054] 3. Driven by the low-pressure turbine, the outside air is sucked into the compressors of the two low-pressure stage superchargers 7 and 8 respectively through the double twisted wire flowmeters 9 and 10; [Measure the inlet flow rate G of the first supercharger 7 compressorKA , the second turbocharger 8 compressor inlet flow G KB , the temperature at the compressor inlet of the first supercharger 7 T 1LA , the temperature at the compressor inlet of the second supercharger 8 T 1LB , the pressure at the inlet of the first supercharger 7 compressor P 1LA , the pressure at the compressor inlet of the second supercharger 8 P 1LB ]

[0055] Fourth, the air is compressed by two low-pressure stage superchargers 7 and 8 and enters two intercoolers 11 and 12 respectively;

[0056] 5. The cooled compressed air enters the compressor end of the high-pressure stage supercharger 13 and is compressed again;

[0057] 6. The gas after secondary compression passes through the orifice flow meter 14 and the self-circulation valve 17 and enters the combustion chamber 3; [Measure the outlet pressure P of the high-pressure stage supercharger 13 compressor 1LH ]

[0058] 7. During the test, the compressor bypass valve 15 is adjusted to allow part of the air to bypass the compressor inlet of the high-pressure stage supercharger 13 and directly enter the combustion chamber 3; the turbine exhaust bypass valve 4 is adjusted to allow part of the high-temperature gas to bypass the turbine end inlet of the high-pressure stage supercharger 13 and directly enter the low-pressure stage superchargers 7 and 8, thereby achieving continuous adjustment of the system pressure ratio, and further studying the optimal total efficiency operation line of the two-stage supercharging system;

[0059] The total efficiency formula of the two-stage turbocharger system is:

[0060]

[0061] in:

[0062] G K -Actual compressor flow rate, G K =G KA +G KB , unit: kg / s

[0063] K-air adiabatic index, value is 1.4

[0064] R-air gas constant, value 287.14, unit J / (kg*K)

[0065] T 1LA - Temperature at the compressor inlet of low-pressure stage supercharger 7, unit K

[0066] T 1LB - Temperature at the compressor inlet of low-pressure stage supercharger 8, unit K

[0067] Π k-Total pressure ratio of two-stage booster system, Π k =2P 1LH / (P 1LA +P 1LB ), P 1LH - High pressure stage supercharger 13 compressor outlet pressure, P 1LA - Low-pressure stage supercharger 7 compressor inlet pressure, P 1LB - Low pressure stage turbocharger 8 compressor inlet pressure

[0068] G T -High-pressure stage turbocharger turbine inlet flow, kg / s

[0069] K T -Turbine gas adiabatic index, value is 1.36

[0070] R T -Gas constant, value is 286.45, unit is J / (kg*K)

[0071] T TH - High-pressure stage turbocharger 13 turbine inlet temperature, unit K

[0072] Π T -High pressure stage turbocharger 13 turbine expansion ratio, Π T =P TH / P 2H , P TH - Pressure at the turbine inlet of the high-pressure stage supercharger 13, P 2H - Pressure at the outlet of the high-pressure stage turbocharger 13 turbine, unit KPa

[0073] 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. An adjustable two-stage turbocharger system test platform, characterized in that: include: A combustion chamber (3), a high pressure stage supercharger (13) and a low pressure stage supercharger; The high-pressure stage supercharger (13) comprises a high-pressure stage compressor (131) and a high-pressure stage turbine (132); the low-pressure stage supercharger comprises a first supercharger (7) and a second supercharger (8); the first supercharger (7) comprises a first compressor (71) and a first turbine (72); the second supercharger (8) comprises a second compressor (81) and a second turbine (82); The inlet end of the combustion chamber (3) is connected to the fan (1), the outlet end of the combustion chamber (3) is connected to the inlet end of the high-pressure stage turbine (132), and the outlet end of the high-pressure stage turbine (132) is connected to the inlet end of the first turbine (72) and the inlet end of the second turbine (82); the outlet end of the first compressor (71) and the outlet end of the second compressor (81) are both connected to the inlet end of the high-pressure stage compressor (131), and the outlet end of the high-pressure stage compressor (131) is connected to the inlet end of the combustion chamber (3), and a vent valve (16) is provided between the outlet end of the high-pressure stage compressor (131) and the inlet end of the combustion chamber (3); The outlet end of the high-pressure stage turbine (132) is provided with a high-pressure outlet pipeline (133), the inlet end of the first turbine (72) is provided with a first inlet pipeline (721), and the inlet end of the second turbine (82) is provided with a second inlet pipeline (821), wherein the high-pressure outlet pipeline (133), the first inlet pipeline (721) and the second inlet pipeline (821) are located in the same plane and are parallel to each other; It also comprises a main pipe (18), a branch pipe (19), a first branch pipe (20) and a second branch pipe (21); the axis of the high-pressure outlet pipe (133) is located between the first inlet pipe (721) and the second inlet pipe (821) and close to the second inlet pipe (821); the inlet end of the main pipe (18) is connected to the high-pressure outlet pipe (133); and the outlet end of the main pipe (18) is inclined toward the first inlet pipe (721); The inlet end of the branch pipe (19) is arranged at the midpoint of the length direction of the branch pipe (19); the outlet end of the main pipe (18) is connected to the inlet end of the branch pipe (19); the branch pipe (19) is perpendicular to the main pipe (18); one end of the branch pipe (19) is connected to the first inlet pipe (721) through the first branch pipe (20); and the other end of the branch pipe (19) is connected to the second inlet pipe (821) through the second branch pipe (21); The sum of the lengths of the second inlet pipe (821) and the second branch pipe (21) is equal to the sum of the lengths of the first inlet pipe (721) and the first branch pipe (20), and the angle between the axis of the second inlet pipe (821) and the axis of the second branch pipe (21) is smaller than the angle between the axis of the first inlet pipe (721) and the axis of the first branch pipe (20); The outlet end of the first compressor (71) is connected to the first intercooler (12), and the outlet end of the second compressor (81) is connected to the second intercooler (11).

2. The adjustable two-stage turbocharger system test platform according to claim 1, characterized in that: A first bypass pipe (134) is provided between the outlet end of the combustion chamber (3) and the outlet end of the high-pressure stage turbine (132), and a first bypass valve (4) is provided on the first bypass pipe (134).

3. The adjustable two-stage turbocharger system test platform according to claim 1, characterized in that: A second bypass pipeline (135) is provided between the outlet and the inlet of the high-pressure compressor (131), and a second bypass valve (15) is provided on the second bypass pipeline (135).

4. The adjustable two-stage turbocharger system test platform according to claim 1, characterized in that: The inlet end of the first turbine (72) is provided with a first turbine inlet valve (6), and the outlet end of the first compressor (71) is provided with a first compressor outlet valve (5).

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