CN113375944A - Comprehensive test bed system of exhaust gas turbocharger - Google Patents
Comprehensive test bed system of exhaust gas turbocharger Download PDFInfo
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- CN113375944A CN113375944A CN202110618605.7A CN202110618605A CN113375944A CN 113375944 A CN113375944 A CN 113375944A CN 202110618605 A CN202110618605 A CN 202110618605A CN 113375944 A CN113375944 A CN 113375944A
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- 238000012360 testing method Methods 0.000 title claims abstract description 29
- 238000002485 combustion reaction Methods 0.000 claims abstract description 23
- 230000003068 static effect Effects 0.000 claims abstract description 9
- 239000007789 gas Substances 0.000 claims description 64
- 239000002912 waste gas Substances 0.000 claims description 3
- 238000011056 performance test Methods 0.000 abstract description 14
- 238000005259 measurement Methods 0.000 abstract description 4
- 238000005265 energy consumption Methods 0.000 description 3
- 230000005855 radiation Effects 0.000 description 2
- 239000006229 carbon black Substances 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 238000005245 sintering Methods 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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Abstract
The invention aims to provide an integrated test bed system of an exhaust gas turbocharger, wherein a gas compressor is coaxial with a turbine, a high-temperature gas compressor is coaxial with a gas turbine, a static chamber is connected with the gas compressor, an outlet pipeline of the gas compressor is connected with a first air inlet valve, the first air inlet valve is connected with an inlet pipeline of a combustion chamber, a first outlet of a wind source is connected with the inlet pipeline of the combustion chamber through a second air inlet valve, an outlet pipeline of the combustion chamber is connected with the gas turbine, and the gas turbine is connected with an exhaust pipe; the second outlet of the air source is connected with the inlet pipeline of the electric heater through a third air inlet valve, the inlet and the outlet of the high-temperature gas compressor are respectively connected with the electric heater and the turbine, and the outlet pipeline of the turbine is connected with the inlet pipeline of the electric heater through a fourth air inlet valve. The closed turbine performance test loop of the invention takes air as working medium, does not pollute the turbine, enables the turbine compressor to operate stably and has high accuracy of parameter measurement. The performance test loop of the gas compressor and the closed turbine performance test loop are relatively independent and do not interfere with each other.
Description
Technical Field
The invention relates to a test bed, in particular to a test bed of an exhaust gas turbocharger.
Background
The turbine performance mainly comprises parameters such as turbine expansion ratio, turbine rotating speed, turbine flow, turbine efficiency and turbine expansion work. Because the performance parameter variation domain of the turbine is wide, the performance parameter variation domain of the compressor can be covered in the supercharging matching, so the performance of the turbine is ignored frequently, only the performance of the compressor is emphasized, and the performance is a miszone. With current increasingly stringent emission regulations, the aftertreatment device occupies a section of exhaust pressure differential, affecting the turbine to expand sufficiently, and has to be compensated for by increasing boost ratio and overall supercharger efficiency. Increasing turbine performance is therefore becoming more and more important.
The key issue in turbine performance testing is mainly the testing of the work of expansion of the turbine. The rotating speed of the supercharger is as high as about 30 ten thousand r/min, so that certain difficulty is brought to the test of the turbine expansion work. The best solution for measuring the work of turbine expansion is to use a special high-speed dynamometer, but the high-speed dynamometer has high cost and is not popularized at present.
The compressor is generally used as a dynamometer in the test of the work of turbine expansion, and the main advantages of the test method are as follows:
1. the performance of the turbine and the performance of the compressor are measured simultaneously, and the system test error is reduced.
2. The rack structure is relatively simple, the cost is lower, and the operation is also more convenient.
The main disadvantages are:
1. the turbine working condition is unstable, and the testing precision is influenced.
2. The gas is used as a working medium, the temperature of the interface of the turbine inlet is uneven, and the phenomena of carbon black pollution, even local sintering and the like are easy to occur.
3. The combustion chamber and the rear pipe thereof radiate heat to the environment, and the performance drift of the compressor is easily caused.
4. The working medium is electrically heated to test the performance of the turbine, which is a relatively ideal scheme, the working medium is clean, does not damage workpieces, is easy to adjust the inlet temperature, but has poor economy.
Disclosure of Invention
The invention aims to provide an exhaust gas turbocharger comprehensive test bed system for comprehensive test simulation of performances of a gas compressor and a turbine.
The purpose of the invention is realized as follows:
the invention relates to a comprehensive test bed system of an exhaust gas turbocharger, which is characterized in that: the high-temperature gas compressor is coaxial with the turbine, the high-temperature gas compressor is coaxial with the gas turbine, the static chamber is connected with the gas compressor, an outlet pipeline of the gas compressor is connected with a first air inlet valve, the first air inlet valve is connected with an inlet pipeline of the combustion chamber, a first outlet of the air source is connected with the inlet pipeline of the combustion chamber through a second air inlet valve, an outlet pipeline of the combustion chamber is connected with the gas turbine, and the gas turbine is connected with an exhaust pipe; the second outlet of the air source is connected with the inlet pipeline of the electric heater through a third air inlet valve, the inlet and the outlet of the high-temperature gas compressor are respectively connected with the electric heater and the turbine, and the outlet pipeline of the turbine is connected with the inlet pipeline of the electric heater through a fourth air inlet valve.
The present invention may further comprise:
1. and a first exhaust valve is arranged on an outlet pipeline of the compressor behind the first air inlet valve, and a second exhaust valve is arranged on an outlet pipeline of the turbine behind the fourth air inlet valve.
2. The first exhaust valve and the second exhaust valve are closed, and the first air inlet valve, the second air inlet valve, the third air inlet valve and the fourth air inlet valve are all opened; the air in the static chamber flows out through the air compressor, enters the combustion chamber together with the air flowing through the second air inlet valve in the air source, then the high-temperature and high-pressure working medium expands in the gas turbine to do work, simultaneously drives the coaxial high-temperature gas compressor to rotate to work, and then the waste gas is discharged through the exhaust pipe; air in the air source enters the electric heater through the third air inlet valve, the heated normal-pressure high-temperature gas enters the high-temperature gas compressor to be pressurized, the high-temperature high-pressure air enters the turbine to expand to do work, and the gas returns to the electric heater through the fourth air inlet valve through the pipeline to realize closed loop circulation.
3. The inlet pressure and temperature of the turbine are controlled by the high-temperature gas compressor, when the outlet temperature of the high-temperature gas compressor is insufficient, the high-temperature gas compressor is supplemented by the electric heater, and the outlet pressure of the high-temperature gas compressor is controlled by the oil supply amount of the combustion chamber.
The invention has the advantages that: the invention saves energy consumption, reduces air consumption, enhances economy, is suitable for endurance test, improves test environment through shielding, reduces thermal radiation interference during compression performance test, and can be remotely and automatically controlled in the whole process. The closed turbine performance test loop takes air as a working medium, does not pollute the turbine, enables the turbine compressor to operate stably, and has high accuracy of parameter measurement. The performance test loop of the gas compressor and the closed turbine performance test loop are relatively independent and do not interfere with each other.
Drawings
FIG. 1 is a schematic structural diagram of the present invention.
Detailed Description
The invention will now be described in more detail by way of example with reference to the accompanying drawings in which:
with reference to fig. 1, the present invention is composed of an open compressor performance test circuit and a closed turbine performance test circuit in combination. The device comprises a static chamber 1, a compressor 2, a gas turbine 3, a combustion chamber 4, an air inlet valve, an exhaust valve, an air source 8, an electric heater 12, a centrifugal high-temperature gas compressor 13 and a turbine 14. The air inlet valve comprises an air inlet valve I6, an air inlet valve II 7, an air inlet valve III 9 and an air inlet valve IV 11 which are respectively connected behind the air compressor 2, the air source 8 and the turbine 14. The exhaust valve comprises an exhaust valve I5 and an exhaust valve II 10 which are respectively an exhaust valve of an open compressor loop and an exhaust valve of a closed turbine loop.
The open type compressor performance testing loop comprises a static chamber 1, a compressor 2, an exhaust valve I5, an air inlet valve I6, an air inlet valve II 7, an air source 8, a combustion chamber 4 and a gas turbine 3. The static chamber 1 is connected to a compressor 2, connected to a combustion chamber 4 through an air inlet valve I6, a wind source 8 is connected to the combustion chamber 4 through an air inlet valve II 7, and the combustion chamber 4 is connected to the gas turbine 3 and then discharges expansion waste gas through an exhaust pipe.
The closed turbine performance testing loop comprises an air source 8, an air inlet valve III 9, an electric heater 12, a high-temperature gas compressor 13, a turbine 14, an air inlet valve IV 11 and an exhaust valve II 10. The air source 8 is connected to the electric heater 12 through an air inlet valve III 9, then connected to a high-temperature gas compressor 13, connected to a turbine 14, and then flows through a pipeline to be optionally connected to an air inlet valve IV 11 and returned to the electric heater 12 or connected to an exhaust valve II 10 for exhaust.
The test bed system for the comprehensive test of the performance of the gas compressor and the turbine is characterized in that:
1) the turbine compressor operates stably, and the accuracy of parameter measurement is high
2) Clean working medium and no pollution to turbine
3) The loop is closed, and the electric heater Dc consumes less energy; self-circulation can be realized in an open loop of the compressor, so that energy consumption is saved. The air source mainly supplements air to the loop, the air consumption is low, the energy consumption of the air source is low, so that the economical efficiency of the rack is good, and the air source is particularly suitable for a durability test.
4) The two loops are shielded to improve the testing environment and reduce the thermal radiation interference during the performance measurement of the compressor.
5) The bench realizes remote whole-course automatic control, and the working condition can be greatly improved.
And the exhaust valve I and the exhaust valve II are exhaust valves of an open compressor loop and a closed turbine loop respectively. The air inlet valve I is connected with the air compressor and the combustion chamber, the air inlet valve II is connected with the air source and the combustion chamber, the air inlet valve III is connected with the air source and the electric heater, and the air inlet valve IV is connected with the turbine and the electric heater.
The open type compressor performance testing loop and the closed type turbine performance testing loop are both connected with the atmosphere. The direction of the arrows in fig. 1 is the direction of gas flow.
When the valve works, the exhaust valve I and the exhaust valve II are closed, and the intake valves I, II, III and IV are all opened. In an open compressor performance test loop: air in the static chamber 1 flows out through the air compressor 2, enters the combustion chamber 4 together with air flowing through the air inlet valve II in the air source 8, and then expands in the gas turbine 3 to do work under high temperature and high pressure, and drives the coaxial high-temperature gas compressor 13 to rotate to work. The exhaust gases are then discharged through an exhaust pipe. In a closed turbine performance test loop: air in the air source enters the electric heater 12 through the air inlet valve III, and the heated normal-pressure high-temperature gas enters the high-temperature gas compressor 13 to be pressurized. Then, the high-temperature and high-pressure air enters the turbine 14 to expand and do work, other gases can return to the electric heater 12 through the air inlet valve IV through a pipeline to realize closed loop circulation except a small amount of pipeline leakage air, and the small amount of leakage can be supplemented by the air source 8.
In the closed turbine performance test loop, air is used as a working medium, the inlet pressure and the temperature of a turbine 14 to be tested are ensured by the high-temperature gas compressor 13, and if the outlet temperature of the high-temperature gas compressor is not high enough, the high-temperature gas compressor can be supplemented by the electric heater 12. The outlet pressure of the high-temperature gas compressor 13 is controlled by the oil supply amount of the combustion chamber 4 in the open compressor performance test loop, thereby influencing the rotating speed of the gas turbine 3. The leakage in the closed circuit can be supplemented by the wind source. The working medium in the closed loop is stable and clean, and the accuracy of the turbine performance test can be ensured. The turbine runs stably, so that the parameter accuracy of the compressor 2 of the tested piece is ensured.
Claims (4)
1. Exhaust-gas turbocharger combined test platform system, characterized by: the high-temperature gas compressor is coaxial with the turbine, the high-temperature gas compressor is coaxial with the gas turbine, the static chamber is connected with the gas compressor, an outlet pipeline of the gas compressor is connected with a first air inlet valve, the first air inlet valve is connected with an inlet pipeline of the combustion chamber, a first outlet of the air source is connected with the inlet pipeline of the combustion chamber through a second air inlet valve, an outlet pipeline of the combustion chamber is connected with the gas turbine, and the gas turbine is connected with an exhaust pipe; the second outlet of the air source is connected with the inlet pipeline of the electric heater through a third air inlet valve, the inlet and the outlet of the high-temperature gas compressor are respectively connected with the electric heater and the turbine, and the outlet pipeline of the turbine is connected with the inlet pipeline of the electric heater through a fourth air inlet valve.
2. The exhaust-gas turbocharger integrated test stand system according to claim 1, characterized in that: and a first exhaust valve is arranged on an outlet pipeline of the compressor behind the first air inlet valve, and a second exhaust valve is arranged on an outlet pipeline of the turbine behind the fourth air inlet valve.
3. The exhaust-gas turbocharger integrated test stand system according to claim 2, characterized in that: the first exhaust valve and the second exhaust valve are closed, and the first air inlet valve, the second air inlet valve, the third air inlet valve and the fourth air inlet valve are all opened; the air in the static chamber flows out through the air compressor, enters the combustion chamber together with the air flowing through the second air inlet valve in the air source, then the high-temperature and high-pressure working medium expands in the gas turbine to do work, simultaneously drives the coaxial high-temperature gas compressor to rotate to work, and then the waste gas is discharged through the exhaust pipe; air in the air source enters the electric heater through the third air inlet valve, the heated normal-pressure high-temperature gas enters the high-temperature gas compressor to be pressurized, the high-temperature high-pressure air enters the turbine to expand to do work, and the gas returns to the electric heater through the fourth air inlet valve through the pipeline to realize closed loop circulation.
4. The exhaust-gas turbocharger integrated test stand system according to claim 3, characterized in that: the inlet pressure and temperature of the turbine are controlled by the high-temperature gas compressor, when the outlet temperature of the high-temperature gas compressor is insufficient, the high-temperature gas compressor is supplemented by the electric heater, and the outlet pressure of the high-temperature gas compressor is controlled by the oil supply amount of the combustion chamber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202110618605.7A CN113375944A (en) | 2021-06-03 | 2021-06-03 | Comprehensive test bed system of exhaust gas turbocharger |
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| CN202110618605.7A CN113375944A (en) | 2021-06-03 | 2021-06-03 | Comprehensive test bed system of exhaust gas turbocharger |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113654787A (en) * | 2021-09-17 | 2021-11-16 | 重庆德蚨乐机械制造有限公司 | Supercharger working state inspection test method |
| CN114323613A (en) * | 2021-12-23 | 2022-04-12 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Comprehensive performance test bed and test method for micro-miniature compressor and turbine |
| CN114753925A (en) * | 2022-05-12 | 2022-07-15 | 沈阳漠南动力科技有限公司 | Electric energy turbine engine |
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2021
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Patent Citations (10)
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| US20060196256A1 (en) * | 2005-03-02 | 2006-09-07 | Christian Rohde | Method for the testing of exhaust gas turbochargers |
| CN101149308A (en) * | 2007-11-01 | 2008-03-26 | 北京理工大学 | Turbine supercharger property test platform with assistant braking system |
| CN101832862A (en) * | 2010-04-22 | 2010-09-15 | 浙江大学 | System for testing performance of exhaust reflux electric heating turbine |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113654787A (en) * | 2021-09-17 | 2021-11-16 | 重庆德蚨乐机械制造有限公司 | Supercharger working state inspection test method |
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| CN114323613A (en) * | 2021-12-23 | 2022-04-12 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Comprehensive performance test bed and test method for micro-miniature compressor and turbine |
| CN114753925A (en) * | 2022-05-12 | 2022-07-15 | 沈阳漠南动力科技有限公司 | Electric energy turbine engine |
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