CN112524080A - Adjustable two-stage turbocharging system test platform - Google Patents

Adjustable two-stage turbocharging system test platform Download PDF

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Publication number
CN112524080A
CN112524080A CN202011520241.0A CN202011520241A CN112524080A CN 112524080 A CN112524080 A CN 112524080A CN 202011520241 A CN202011520241 A CN 202011520241A CN 112524080 A CN112524080 A CN 112524080A
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China
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inlet
pressure stage
turbine
supercharger
compressor
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CN202011520241.0A
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Chinese (zh)
Inventor
李琦
黄佳伟
金德郁
初永春
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CRRC Dalian Institute Co Ltd
Dalian CRRC Zetong Machinery Co Ltd
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CRRC Dalian Institute Co Ltd
Dalian CRRC Zetong Machinery Co Ltd
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Priority to CN202011520241.0A priority Critical patent/CN112524080A/en
Publication of CN112524080A publication Critical patent/CN112524080A/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/001—Testing thereof; Determination or simulation of flow characteristics; Stall or surge detection, e.g. condition monitoring
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/10—Centrifugal pumps for compressing or evacuating
    • F04D17/12—Multi-stage pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D25/00—Pumping installations or systems
    • F04D25/02—Units comprising pumps and their driving means
    • F04D25/04—Units comprising pumps and their driving means the pump being fluid-driven
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/009—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids by bleeding, by passing or recycling fluid

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Supercharger (AREA)

Abstract

The adjustable two-stage turbocharging system test platform provided by the invention comprises a high-pressure stage supercharger and a low-pressure stage supercharger, can simultaneously measure the performance of a high-pressure stage single supercharger and the performance of a low-pressure stage single supercharger and the performance of a two-stage turbocharging system, can work in an open circulation mode or a self-circulation mode, tests and evaluates the performance and the matching performance of the turbocharger in advance, and provides data support for the matching of the supercharger and an internal combustion engine. By adjusting the first bypass valve and the second bypass valve, the continuous adjustment of the supercharging ratio can be realized, and the performance of the two-stage turbocharger under different opening degrees of the bypass valves is tested. And for the arrangement of the front air inlet pipelines of the two low-pressure stage turbochargers, the air flow and the pressure distributed to the two low-pressure stage turbochargers are basically consistent, and the accuracy and the stability of the test are ensured.

Description

Adjustable two-stage turbocharging system test platform
Technical Field
The invention relates to the field of a test platform of a supercharging system, in particular to an adjustable two-stage turbocharging system test platform.
Background
With the development of internal combustion engine technology and the increasing strictness of emission regulations, superchargers are required to have as high a supercharge pressure as possible and a wide operating range. The adjustable two-stage supercharging technology is one of the most advanced supercharging technologies at present due to the advantages of high supercharging ratio, wide flow range and high efficiency. The turbocharging system platform test is an indispensable means for detecting the performance and the reliability of the turbocharging system and improving the machine matching success rate of the turbocharging system, and meanwhile, the platform test data can provide a basis for optimizing and upgrading products.
The two-stage supercharging test method is researched at home and abroad, but a standard test method is not established yet. At present, a two-stage supercharging system needs a test platform with high flexibility and wide application range so as to meet the requirements of production and research.
Disclosure of Invention
The invention provides an adjustable two-stage turbocharging system test platform, which aims to solve the problems.
An adjustable two-stage turbocharging system test platform, comprising: the device comprises a combustion chamber, a high-pressure stage supercharger and a low-pressure stage supercharger;
the high-pressure stage supercharger comprises a high-pressure stage compressor and a high-pressure stage turbine, the low-pressure stage supercharger comprises a first supercharger and a second supercharger, the first supercharger comprises a first compressor and a first turbine, and the second supercharger comprises a second compressor and a second turbine;
the inlet end of the combustion chamber is communicated with a fan, the outlet end of the combustion chamber is connected with the inlet end of the high-pressure stage turbine, and the outlet end of the high-pressure stage turbine is connected with 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 with the inlet end of the high-pressure stage compressor, the outlet end of the high-pressure stage compressor is connected with the inlet end of the combustion chamber, and a release valve is arranged between the outlet end of the high-pressure stage compressor and the inlet end of the combustion chamber.
Furthermore, the outlet end of the high-pressure stage turbine is provided with a high-pressure outlet pipeline, the inlet end of the first turbine is provided with a first inlet pipeline, the inlet end of the second turbine is provided with a second inlet pipeline, and the high-pressure outlet pipeline, the first inlet pipeline and the second inlet pipeline are in the same plane and are parallel to each other.
The high-pressure outlet pipeline is arranged between the first inlet pipeline and the second inlet pipeline and is close to the second inlet pipeline, the inlet end of the main pipe is connected with the high-pressure outlet pipeline, and the outlet end of the main pipe inclines towards the first inlet pipeline;
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 with the inlet end of the branch pipe, the branch pipe is perpendicular to the main pipe, one end of the branch pipe is communicated with the first inlet pipeline through the first branch pipe, and the other end of the branch pipe is communicated with the second inlet pipeline through the second branch pipe;
the sum of the lengths of the second inlet pipeline and the second branch pipe is equal to the sum of the lengths of the first inlet pipeline and the first branch pipe, and the included angle between the axis of the second inlet pipeline and the axis of the second branch pipe is smaller than the included angle between the axis of the first inlet pipeline and the axis of the first branch pipe.
Furthermore, a first bypass pipeline is arranged between the outlet end of the combustion chamber and the outlet end of the high-pressure stage turbine, and a first bypass valve is arranged on the first bypass pipeline.
Further, a second bypass pipeline is arranged between the outlet and the inlet of the high-pressure stage compressor, and a second bypass valve is arranged on the second bypass pipeline.
Further, the outlet end of the first compressor is connected with a first intercooler, and the outlet end of the second compressor is connected with a second intercooler.
Further, a first turbine inlet valve is arranged at the inlet end of the first turbine, and a first compressor outlet valve is arranged at the outlet end of the first compressor.
The adjustable two-stage turbocharging system test platform disclosed by the invention can simultaneously measure the performance of a high-pressure single turbocharger and the performance of a low-pressure single turbocharger and the performance of a two-stage turbocharging system, can work in an open circulation mode or a self-circulation mode, and can test and evaluate the performance and the matching performance of the turbocharger in advance to provide data support for the matching of the turbocharger and an internal combustion engine. By adjusting the first bypass valve and the second bypass valve, the continuous adjustment of the supercharging ratio can be realized, and the performance of the two-stage turbocharger under different opening degrees of the bypass valves is tested. And for the arrangement of the front air inlet pipelines of the two low-pressure stage turbochargers, the air flow and the pressure distributed to the two low-pressure stage turbochargers are basically consistent, and the accuracy and the stability of the test are ensured.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and those skilled in the art can also obtain other drawings according to the drawings without creative efforts.
FIG. 1 is a schematic flow chart of a turbine test platform according to an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of a turbine test platform according to an embodiment of the present invention;
fig. 3 is a schematic connection diagram of a high-pressure stage supercharger and a low-pressure stage supercharger disclosed by the embodiment of the invention.
In the figure: 1. a fan; 2. a turbine-end intake valve; 3. a combustion chamber; 4. a first bypass valve; 5. a first compressor outlet valve; 6. a first turbine inlet valve; 7. a first supercharger; 71. a first compressor; 72. a first turbine; 721. a first inlet conduit; 8. a second supercharger; 81. a second compressor; 82. a second turbine; 821. a second inlet conduit; 9. a first flow meter; 10. a second flow meter; 11. a second intercooler; 12. a first intercooler; 13. a high-pressure stage supercharger; 131. a high-pressure stage compressor; 132. a high pressure stage turbine; 133. a high pressure outlet conduit; 134. a first bypass conduit; 135. a second bypass conduit; 14. an orifice plate flowmeter; 15. a second bypass valve; 16. a deflation valve; 17. a self-circulation valve; 18. a main pipe; 19. pipe distribution; 20. a first branch pipe; 21. a second branch pipe.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
As shown in fig. 1 and fig. 2, an adjustable two-stage turbocharging system test platform includes: the combustion chamber 3, the high-pressure stage supercharger 13 and the 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, and the second supercharger 8 comprises a second compressor 81 and a second turbine 82;
the inlet end of the combustion chamber 3 is communicated with the fan 1, the outlet end of the combustion chamber 3 is connected with the inlet end of the high-pressure stage turbine 132, and the outlet end of the high-pressure stage turbine 132 is connected with 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 with the inlet end of the high-pressure stage compressor 131, the outlet end of the high-pressure stage compressor 131 is connected with the inlet end of the combustion chamber 3, and a deflation valve 16 is arranged between the outlet end of the high-pressure stage compressor 131 and the inlet end of the combustion chamber 3.
In the open circulation mode, namely the mode that the turbine end air inlet valve 2 is opened, the air release valve 16 is opened, and the self-circulation valve 17 is closed, the fan 1 provides air for the pipeline to drive the whole supercharging system for the initial operation test and the turbine characteristic test of the supercharger, and the turbine end air inlet valve 2 is used for adjusting the flow and the pressure of compressed air entering the pipeline in the open circulation mode.
And in a self-circulation mode, namely a mode that the air inlet valve 2 at the turbine end is closed, the air release valve 16 is closed, and the self-circulation valve 17 is opened, the combustion of the injected natural gas generates high-temperature and high-pressure gas to drive the whole supercharger system.
The first supercharger 7 and the second supercharger 8 are connected in parallel in a pipeline, inlets of the first turbine and the second turbine are connected with an outlet of the high-pressure stage turbine 132 through the pipeline, outlets of the first turbine and the second turbine are communicated with the atmosphere, inlets of the first compressor and the second compressor are communicated with the atmosphere, and outlets of the first compressor and the second compressor are connected with the adjustable intercooler through the pipeline; the first intercooler and the second intercooler are adjustable intercoolers, the outlet end of the first compressor 71 is connected with the first intercooler 12, and the outlet end of the second compressor 81 is connected with the second intercooler 11.
The two intercoolers are provided with cooling water regulating valves, and the regulation of the temperature of the air at the inlet of the compressor of the high-pressure stage supercharger 13 can be realized by regulating the flow of cooling water entering the intercoolers;
the first booster inlet is provided with a first flowmeter 9, the second booster inlet is provided with a second flowmeter 10, and the first flowmeter 9 and the second flowmeter 10 are both lemniscate flowmeters.
The outlet of the high-pressure stage compressor is connected with an orifice flowmeter 14 through a pipeline. And the orifice plate flowmeter 14 is used for measuring the air flow of the outlet of the compressor of the high-pressure stage supercharger 13.
A first bypass pipeline 134 is arranged 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 arranged on the first bypass pipeline 134. The adjustment of the flow of the high-temperature gas entering the high-pressure-stage supercharger is realized by adjusting the opening degree of the first bypass valve 4.
A second bypass pipeline 135 is arranged between the outlet and the inlet of the high-pressure stage compressor 132, and a second bypass valve 15 is arranged on the second bypass pipeline 135. The method is used for adjusting the inlet flow of the compressor of the high-pressure stage supercharger 13, thereby adjusting the total pressure ratio of the two-stage supercharging system.
And the self-circulation valve 17 is connected with the turbine-end air inlet valve 2 in parallel, and in the open circulation mode, the self-circulation valve 17 is closed and the turbine-end air inlet valve 2 is opened. In the self-circulation mode, the self-circulation valve 17 is opened and the turbine-side intake valve 2 is closed. One side of the self-circulation valve 17 is connected with the orifice plate flowmeter 14 through a pipeline, and the other side of the self-circulation valve is connected with the combustion chamber 3 through a pipeline, and the self-circulation valve is used for adjusting the air flow of the outlet of the compressor of the high-pressure stage supercharger 13 during performance tests.
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. And the first compressor outlet valve 5 and the first turbine inlet valve 6 are opened or closed simultaneously, so that the free conversion in the forms of 1 high pressure stage +2 low pressure stage or 1 high pressure stage +1 low pressure stage can be realized, and different test requirements are met.
The working process of the invention is as follows:
firstly, high-temperature gas in a combustion chamber enters a turbine end of a high-pressure stage supercharger to drive the high-pressure stage turbine to rotate, and simultaneously, a gas compressor of the high-pressure stage supercharger sucks air which is compressed and cooled for one time under the driving of the turbine;
secondly, high-temperature gas enters turbine ends of two low-pressure stage superchargers after passing through a turbine of the high-pressure stage supercharger to drive the low-pressure stage turbine to rotate;
thirdly, under the drive of the low-pressure stage turbine, outside air is respectively sucked by the air compressors of the two low-pressure stage superchargers through the two twisted-pair flow meters;
fourthly, the air is compressed by two low-pressure stage superchargers and then respectively enters two intercoolers;
fifthly, the cooled compressed air enters a compressor end of the high-pressure stage supercharger and is compressed again;
and sixthly, the gas after secondary compression enters the combustion chamber after passing through the orifice plate flowmeter and the self-circulation valve.
In the test process, partial air bypasses the inlet of the air compressor of the high-pressure stage supercharger and directly enters the combustion chamber by adjusting the bypass valve of the air compressor; by adjusting the turbine waste gas bypass valve, part of high-temperature gas bypasses the inlet of the turbine end of the high-pressure stage supercharger and directly enters the low-pressure stage supercharger, so that the supercharging ratio of the system can be continuously adjusted, and the optimal total efficiency operation line of the two-stage supercharging system is further researched.
The invention can realize the system test of various adjustable two-stage turbochargers in the forms of 1 high-pressure stage +2 low-pressure stage and 1 high-pressure stage +1 low-pressure stage; the performance of a single high-pressure booster and the performance of a two-stage boosting system can be measured simultaneously. The performance of a two-stage turbocharger with high flow (1-10 kg/s) and high pressure ratio (the highest pressure ratio can reach 15) can be tested, and the turbocharger can work in an open circulation mode or a self-circulation mode; a turbine waste gas bypass valve and a compressor bypass valve are arranged between the high-pressure stage supercharger and the low-pressure stage supercharger, the continuous adjustment of the supercharging ratio can be realized by adjusting the opening degrees of the turbine waste gas bypass valve and the compressor bypass valve, and the performance of the two-stage turbocharger under different opening degrees of the turbine waste gas bypass valve and the compressor bypass valve is tested; the temperature of the inlet gas of the high-pressure compressor can be controlled by adjusting the flow of water flow through an intercooler water-cooling regulating valve; the invention tests and evaluates the performance and the matching performance of the two-stage turbocharger in advance, and provides data support for matching the turbocharger and the diesel engine.
The invention has compact space structure, reasonable arrangement and strong reliability, and can meet the requirement of the supercharger on long-term frequent tests; in order to complete the layout of a test platform in a limited space and meet the aim of compact space structure, a pipeline connected between a high-pressure stage supercharger and a low-pressure stage supercharger is designed asymmetrically, and meanwhile, in order to ensure the consistency of air flow distributed to the two low-pressure stage turbochargers, the invention designs the high-pressure stage supercharger and the low-pressure stage supercharger as follows:
the outlet end of the high-pressure stage turbine 132 is provided with a high-pressure outlet pipe 133, the inlet end of the first turbine 72 is provided with a first inlet pipe 721, the inlet end of the second turbine 82 is provided with a second inlet pipe 821, and the high-pressure outlet pipe 133, the first inlet pipe 721 and the second inlet pipe 821 are in the same plane and are parallel to each other.
Further comprising a main pipe 18, a branch pipe 19, a first branch pipe 20 and a second branch pipe 21, wherein 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 with the high-pressure outlet pipe 133, and the outlet end of the main pipe 18 is inclined to the first inlet pipe 721;
the inlet end of the branch pipe 19 is arranged at the middle point of the length direction of the branch pipe 19, the outlet end of the main pipe 18 is connected with 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 communicated with the first inlet pipeline 721 through the first branch pipe 20, and the other end of the branch pipe 19 is communicated with the second inlet pipeline 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 included angle between the axis of the second inlet pipe 821 and the axis of the second branch pipe 21 is smaller than the included angle between the axis of the first inlet pipe 721 and the axis of the first branch pipe 20.
According to the invention, the pipeline arrangement before the air inlet of the 2 low-pressure stage superchargers is realized by firstly inclining the main pipe 18 by a certain angle and then matching the bending of the two branch pipes at different angles, so that the overall length of the two branch pipes is equal, the air flow distributed to the two low-pressure stage superchargers is basically consistent, and through actual tests, the rotating speed deviation is not more than +/-2%, the flow deviation is not more than 3% and the pressure ratio is not more than 2% when the two low-pressure stage superchargers operate.
The test process of the turbine test platform disclosed by the invention is as follows:
firstly, high-temperature gas in the combustion chamber 3 enters a turbine end of a high-pressure stage supercharger 13 to drive a high-pressure stage turbine 132 to rotate, and simultaneously, a compressor 131 of the high-pressure stage supercharger sucks air which is compressed and cooled for the first time under the driving of the turbine; [ measurement of high-pressure stage supercharger turbine inlet temperature TTHHigh voltage stageTurbocharger turbine inlet flow GTPressure P at the inlet of the turbine of the high-pressure stage superchargerTHPressure P at the outlet of the turbine of the high-pressure stage supercharger2H]
Secondly, after passing through a turbine 132 of the high-pressure stage supercharger, the high-temperature gas enters turbine ends 72 and 82 of the low-pressure stage supercharger to drive the low-pressure stage turbine to rotate;
thirdly, under the drive of the low-pressure stage turbine, outside air is sucked by the air compressors of the two low-pressure stage superchargers 7 and 8 through the twisted pair flow meters 9 and 10 respectively; [ measurement of the compressor inlet flow G of the first supercharger 7KAInlet flow G of compressor of second supercharger 8KBThe temperature T at the inlet of the compressor of the first supercharger 71LAThe temperature T at the inlet of the compressor of the second supercharger 81LBPressure P at the inlet of the compressor of the first supercharger 71LAPressure P at the inlet of the compressor of the second supercharger 81LB]
Fourthly, the air is compressed by two low-pressure stage superchargers 7 and 8 and then enters two intercoolers 11 and 12 respectively;
fifthly, the cooled compressed air enters the compressor end of the high-pressure stage supercharger 13 and is compressed again;
sixthly, the gas after secondary compression enters the combustion chamber 3 after passing through the orifice plate flowmeter 14 and the self-circulation valve 17; [ measurement of the compressor outlet pressure P of the high-pressure supercharger 131LH]
Seventhly, in the test process, adjusting a bypass valve 15 of the air compressor to realize that part of air bypasses an air compressor inlet of the high-pressure stage supercharger 13 and directly enters the combustion chamber 3; the turbine waste gas bypass valve 4 is adjusted to realize that part of high-temperature gas bypasses the inlet of the turbine end of the high-pressure stage supercharger 13 and directly enters the low-pressure stage superchargers 7 and 8, so that the continuous adjustment of the supercharging ratio of the system is realized, and the optimal total efficiency operating line of the two-stage supercharging system can be further researched;
the total efficiency formula of the two-stage turbocharging system is as follows:
Figure BDA0002849245860000071
wherein:
GKmeasured compressor flow, GK＝GKA+GKBUnit kg/s
K-air adiabatic index, value 1.4
R-air gas constant, value 287.14, unit J/(kg x K)
T1LATemperature at the compressor inlet of the low-pressure stage supercharger 7, in K
T1LBTemperature at the compressor inlet of the low-pressure stage supercharger 8, in K
ΠkTotal pressure ratio, Π, of two-stage supercharging systemk＝2P1LH/(P1LA+P1LB)，P1LH-compressor outlet pressure, P, of the high-pressure stage supercharger 131LAInlet pressure, P, of the compressor of the low-pressure stage supercharger 71LBInlet pressure of the compressor of the low-pressure stage supercharger 8
GTInlet flow of the turbine of the high-pressure stage supercharger in kg/s
KTTurbine gas adiabatic index, value 1.36
RTGas constant value 286.45, unit J/(kg. K)
TTHHigh-pressure stage supercharger 13 turbine inlet temperature, in K
ΠT-turbo expansion ratio, Π, of the high-pressure stage supercharger 13T＝PTH/P2H，PTHPressure at the turbine inlet of the high-pressure stage supercharger 13, P2HPressure at the turbine outlet of the high-pressure stage supercharger 13, in KPa
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.

Claims (7)

1. The utility model provides an adjustable two-stage turbocharging system test platform which characterized in that includes: the combustion chamber (3), the high-pressure stage supercharger (13) and the 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), and the second supercharger (8) comprises a second compressor (81) and a second turbine (82);
the inlet end of the combustion chamber (3) is communicated with a fan (1), the outlet end of the combustion chamber (3) is connected with the inlet end of the high-pressure stage turbine (132), and the outlet end of the high-pressure stage turbine (132) is connected with 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 with the inlet end of the high-pressure stage compressor (131), the outlet end of the high-pressure stage compressor (131) is connected with the inlet end of the combustion chamber (3), and a release valve (16) is arranged between the outlet end of the high-pressure stage compressor (131) and the inlet end of the combustion chamber (3).
2. The adjustable two-stage turbocharging system test platform according to claim 1, characterized in that the outlet end of the high-pressure stage turbine (132) is provided with a high-pressure outlet pipe (133), the inlet end of the first turbine (72) is provided with a first inlet pipe (721), the inlet end of the second turbine (82) is provided with a second inlet pipe (821), and the high-pressure outlet pipe (133), the first inlet pipe (721) and the second inlet pipe (821) are in the same plane and are parallel to each other.
3. An adjustable two-stage turbocharging system test platform according to claim 2, further comprising a main pipe (18), a branch pipe (19), a first branch pipe (20) and a second branch pipe (21), wherein the axis of the high pressure outlet duct (133) is located between the first inlet duct (721) and the second inlet duct (821) and close to the second inlet duct (821), the inlet end of the main pipe (18) is connected with the high pressure outlet duct (133), and the outlet end of the main pipe (18) is inclined towards the first inlet duct (721);
the inlet end of the branch pipe (19) is arranged at the middle point of the length direction of the branch pipe (19), the outlet end of the main pipe (18) is connected with 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 communicated with the first inlet pipeline (721) through the first branch pipe (20), and the other end of the branch pipe is communicated with the second inlet pipeline (821) through the second branch pipe (21);
the sum of the lengths of the second inlet pipeline (821) and the second branch pipe (21) is equal to the sum of the lengths of the first inlet pipeline (721) and the first branch pipe (20), and the included angle between the axis of the second inlet pipeline (821) and the axis of the second branch pipe (21) is smaller than the included angle between the axis of the first inlet pipeline (721) and the axis of the first branch pipe (20).
4. The adjustable two-stage turbocharging system test platform according to claim 1, characterized in that a first bypass pipe (134) is arranged 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 arranged on the first bypass pipe (134).
5. The adjustable two-stage turbocharging system test platform according to claim 1, wherein a second bypass pipeline (135) is arranged between the outlet and the inlet of the high-pressure stage compressor (132), and a second bypass valve (15) is arranged on the second bypass pipeline (135).
6. The adjustable two-stage turbocharging system test platform according to claim 1, characterized in that the outlet end of the first compressor (71) is connected with a first intercooler (12) and the outlet end of the second compressor (81) is connected with a second intercooler (11).
7. The adjustable two-stage turbocharging 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).
CN202011520241.0A 2020-12-21 2020-12-21 Adjustable two-stage turbocharging system test platform Pending CN112524080A (en)

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113309728A (en) * 2021-06-21 2021-08-27 中车大连机车研究所有限公司 Magnetic suspension blower comprehensive test bed
CN114486271A (en) * 2022-01-28 2022-05-13 重庆江增船舶重工有限公司 Two-stage sequential supercharging system foundation module test platform and test method

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113309728A (en) * 2021-06-21 2021-08-27 中车大连机车研究所有限公司 Magnetic suspension blower comprehensive test bed
CN114486271A (en) * 2022-01-28 2022-05-13 重庆江增船舶重工有限公司 Two-stage sequential supercharging system foundation module test platform and test method

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