CN105203288A - Turbocharger starting-stopping impact test stand - Google Patents
Turbocharger starting-stopping impact test stand Download PDFInfo
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- CN105203288A CN105203288A CN201510580380.5A CN201510580380A CN105203288A CN 105203288 A CN105203288 A CN 105203288A CN 201510580380 A CN201510580380 A CN 201510580380A CN 105203288 A CN105203288 A CN 105203288A
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- pneumatic plant
- turbine
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- turbosupercharger
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Abstract
The invention relates to a turbocharger starting-stopping impact test stand, and belongs to the technical field of power machines. The turbocharger starting-stopping impact test stand comprises two loops. The first loop and the second loop are completely same, each comprise a turbocharger and a connecting pipe and share an air flow ejector, a combustor and a high temperature switch valve. Meanwhile, the invention discloses a turbocharger starting-stopping impact test method, and the basis is provided for turbocharger starting-stopping impacting reliability. The turbocharger starting-stopping impact test stand is scientific and reasonable in scheme, easy to achieve, stable and reliable, and has important application value in improving the reliability of the turbocharger.
Description
Technical field
The present invention relates to a kind of turbosupercharger start/stop impact testing table, belong to field of power machinery technology.
Background technology
In the development course of internal combustion engine, the specific power being applied in raising internal combustion engine of turbocharging technology and the aspect such as fuel economy, reduction discharge have played important effect, are described as the important milestone in internal combustion engine development history.Along with the widespread use of supercharger on internal combustion engine, the whole breakdown in the motor caused by supercharger fault and damage event get more and more, fail-test at present for turbine mainly contains the durable thermal cycle certification test of supercharger 120h, thermal shock test, and high and low cycle fatigue test etc.
In order to solve the problem of automobile fuel consume under idling operation, novel energy-conserving automobile all have employed engine start and stop technology.Automobile is completely flame-out when running into red light shuts down, and supercharger is stall thereupon also, starts fast afterwards.Under this technology of application, during engine start, supercharger accelerates to fast state from stationary state at short notice, rotor will be subject to strong impact, automobile is in the urban road driving process that vehicle density is instantly higher, frequent start-stop, therefore rotor is constantly subject to intense impact, and this is a huge large challenge to the reliability of turbosupercharger.Only rely on existing method of testing can not examine the reliability of city vehicle turbosupercharger under frequent start-stop operating mode.All there is not the test method for turbosupercharger start and stop working condition measurement turbine reliability at present both at home and abroad.
Summary of the invention
The object of the invention is to provide a kind of turbosupercharger start/stop impact testing table, this testing table can complete the test of turbine start/stop impact, thus the reliability of examination turbosupercharger under start and stop operating mode.
The object of the invention is to be realized by technical scheme below.
A kind of turbosupercharger start/stop impact testing table, comprise the first loop and second servo loop, two cover turbosupercharger in two loops are identical, and share a firing chamber, combustor exit pipeline, high temperature shift valve, Ejector, each turbosupercharger is furnished with respective lubricating system, according to testing requirements, can automatically cutting off lubricating oil supply while stopping turbocharger operation, automatically connecting lubricating oil supply when starting supercharger.
First turbosupercharger comprises the first pneumatic plant and the first turbine; Second turbosupercharger comprises the second pneumatic plant and the second turbine, and these two superchargers are tested turbosupercharger;
First loop comprises firing chamber, combustor exit pipeline, high temperature shift valve, the first combustor exit pipeline branch road, the first compressor air inlet machine pipeline, the first pneumatic plant, the first turbine, the first turbine outlet pipeline, the first valve, the first pneumatic plant gas outlet, Ejector;
Second servo loop comprises firing chamber, combustor exit pipeline, high temperature shift valve, the second turbine outlet pipeline, the second turbine, the second pneumatic plant, the second compressor air inlet machine pipeline, the second combustor exit pipeline branch road, the second pneumatic plant gas outlet, the second valve, Ejector;
Annexation: firing chamber is connected with high temperature shift valve by combustor exit pipeline; High temperature shift valve connects the first combustor exit pipeline branch road and the second combustor exit pipeline branch road respectively; The other end of the first combustor exit pipeline branch road is connected with the first turbine of the first turbosupercharger; The other end of the second combustor exit pipeline branch road is connected with the second turbine of the second turbosupercharger; Pneumatic plant can be driven while turbine to operate; First pneumatic plant is connected with the first compressor air inlet machine pipeline, the first pneumatic plant gas outlet; First valve is positioned on the first pneumatic plant gas outlet; Second pneumatic plant is connected with the second compressor air inlet machine pipeline, the second pneumatic plant gas outlet; Second valve is positioned on the second pneumatic plant gas outlet; First pneumatic plant gas outlet and the second pneumatic plant gas outlet are connected with two entrances of Ejector respectively; The outlet of Ejector is connected with firing chamber.
The course of work: during the first loop works, the high temperature shift valve being arranged in exhaust outlet of combustion chamber place connects the pipeline in the first loop, the first valve open in first loop, and the second valve closing in second servo loop, high-temperature fuel gas enters the first turbine again through high temperature shift valve and the first combustor exit pipeline branch road, enters air after acting.First turbine obtains energy and drives the first pneumatic plant running from combustion gas, and air, after the first pneumatic plant compression, by the first valve in the first loop, enters air inlet of combustion chamber.After the first loop stability runs, switching high temperature shift valve makes waste gas flow in second servo loop, meanwhile, open the second valve in second servo loop, the first valve in first loop temporarily stays open state, now, first turbine decelerate under inertia effect in first loop, the gaseous tension of the first blower outlet changes from high to low, there is the gas flow of elevated pressures when gas ejector, due to the throttling action in tapered cross section, speed raised pressure reduces, Ejector produces ejector action for the gas in second servo loop, drive the gas flow firing chamber in second servo loop.The second turbine in second servo loop is started running by static under combustion gas effect, the second pneumatic plant is driven to compress air, gas in second servo loop is flowing in combustion chamber under the acting in conjunction of the second pneumatic plant and Ejector, discharge in a combustion chamber with after fuel combustion, the second turbine is entered through high temperature shift valve, the second turbine is made constantly to accelerate to realize starting, until reach the rotating speed preset, and the first turbine in the first loop shuts down gradually owing to not having gas driven, in first pneumatic plant gas outlet, gaseous tension also reduces thereupon gradually, in the first pneumatic plant gas outlet, gaseous tension equals first valve of closing when burning gas pressure inside in the first loop.So far, the first turbosupercharger in the first loop is achieved by the second turbosupercharger run in stopping, second servo loop by the static handoff procedure to running.So repeatedly, the multi cycle start/stop impact test of turbosupercharger can be carried out.In handoff procedure, the gas flow flowing through firing chamber has fluctuation, can adapt to the fluctuation of gas flow, thus realize smooth combustion and smooth transition by automatically regulating distributive value.
Beneficial effect
1, a turbosupercharger start/stop impact testing table, effectively can be used for examining the reliability of turbosupercharger under start and stop operating mode, and compared with traditional turbocharger test platform, not need to provide outer source of the gas, significantly reduce experimentation cost.
2, turbosupercharger start/stop impact testing table of the present invention, can promote carrying out of Reliability of Turbochargers work, to raising turbocharger performance, meets the technical property requirements of internal combustion engine to turbosupercharger increasingly stringent and has important using value.
Accompanying drawing explanation
Fig. 1 is test platform structure vertical view of the present invention, tests for turbine start/stop impact.
Wherein, 1-firing chamber, 2-combustor exit pipeline, 3-high temperature shift valve, 4-first combustor exit pipeline branch road, 5-first compressor air inlet machine pipeline, 6-first pneumatic plant, 7-first turbine, 8-first turbine outlet pipeline, 9-second turbine outlet pipeline, 10-second turbine, 11-second pneumatic plant, 12-second compressor air inlet machine pipeline, 13-second combustor exit pipeline branch road, 14-second pneumatic plant gas outlet, 15-second valve, 16-first valve, 17-first pneumatic plant gas outlet, 18-Ejector.
Embodiment
In order to make those skilled in the art understand the present invention program better, below in conjunction with accompanying drawing and specific implementation method, content of the present invention is described in further detail.
A kind of turbosupercharger start/stop impact testing table, comprise the first loop and second servo loop, two cover turbosupercharger in two loops are identical, and share a firing chamber 1, combustor exit pipeline 2, high temperature shift valve 3, Ejector 18, as shown in Figure 1.
First turbosupercharger comprises the first pneumatic plant 6 and the first turbine 7; Second turbosupercharger comprises the second pneumatic plant 11 and the second turbine 10;
First loop comprises firing chamber 1, combustor exit pipeline 2, high temperature shift valve 3, first combustor exit pipeline branch road 4, first compressor air inlet machine pipeline 5, first pneumatic plant 6, first turbine 7, first turbine outlet pipeline 8, first valve 16, first pneumatic plant gas outlet 17, Ejector 18;
Second servo loop comprises firing chamber 1, combustor exit pipeline 2, high temperature shift valve 3, second turbine outlet pipeline 9, second turbine 10, second pneumatic plant 11, second compressor air inlet machine pipeline 12, second combustor exit pipeline branch road 13, second pneumatic plant gas outlet 14, second valve 15, Ejector 18;
Annexation: firing chamber 1 is connected with high temperature shift valve 3 by combustor exit pipeline 2; High temperature shift valve 3 connects the first combustor exit pipeline branch road 4 and the second combustor exit pipeline branch road 13 respectively; The other end of the first combustor exit pipeline branch road 4 is connected with the first turbine 7 of the first turbosupercharger; The other end of the second combustor exit pipeline branch road 13 is connected with the second turbine 10 of the second turbosupercharger; Pneumatic plant can be driven while turbine to operate; First pneumatic plant 6 is connected with the first compressor air inlet machine pipeline 5, first pneumatic plant gas outlet 17; First valve 16 is positioned on the first pneumatic plant gas outlet 17; Second pneumatic plant 11 is connected with the second compressor air inlet machine pipeline 12, second pneumatic plant gas outlet 14; Second valve 15 is positioned on the second pneumatic plant gas outlet 14; First pneumatic plant gas outlet 17 and the second pneumatic plant gas outlet 14 are connected with two entrances of Ejector 18 respectively; The outlet of Ejector 18 is connected with firing chamber 1.
The course of work: during the first loop works, the high temperature shift valve 3 being arranged in exhaust outlet of combustion chamber place connects the pipeline in the first loop, the first valve 16 in first loop is opened, and the second valve 15 in second servo loop is closed, high-temperature fuel gas enters the first turbine 7 again through high temperature shift valve 3 and the first combustor exit pipeline branch road 4, enters air after acting.First turbine 7 obtains energy and drives the first pneumatic plant 6 to operate from combustion gas, and air, after the first pneumatic plant 6 compresses, by the first valve 16 in the first loop, enters air inlet of combustion chamber.After the first loop stability runs, switching high temperature shift valve 3 makes waste gas flow in second servo loop, meanwhile, open the second valve 15 in second servo loop, the first valve 16 in first loop temporarily stays open state, now, first turbine 7 decelerate under inertia effect in first loop, the gaseous tension that first pneumatic plant 6 exports changes from high to low, there is the gas flow of elevated pressures when gas ejector 18, due to the throttling action in tapered cross section, speed raised pressure reduces, Ejector 18 produces ejector action for the gas in second servo loop, drive the gas flow firing chamber 1 in second servo loop.The second turbine 10 in second servo loop is started running by static under combustion gas effect, the second pneumatic plant 11 pairs of air are driven to compress, gas in second servo loop is flowing in combustion chamber 1 under the acting in conjunction of the second pneumatic plant 11 and Ejector 18, discharge in firing chamber 1 with after fuel combustion, the second turbine 10 is entered through high temperature shift valve 3, the second turbine 10 is made constantly to accelerate to realize starting, until reach the rotating speed preset, and the first turbine 7 in the first loop shuts down gradually owing to not having gas driven, in first pneumatic plant gas outlet 17, gaseous tension also reduces thereupon gradually, the first valve 16 in the first loop is closed when gaseous tension equals gaseous tension in firing chamber 1 in the first pneumatic plant gas outlet 17.So far, the first turbosupercharger in the first loop is achieved by the second turbosupercharger run in stopping, second servo loop by the static handoff procedure to running.So repeatedly, the multi cycle start/stop impact test of turbosupercharger can be carried out.In handoff procedure, the gas flow flowing through firing chamber has fluctuation, can adapt to the fluctuation of gas flow, thus realize smooth combustion and smooth transition by automatically regulating distributive value.
Claims (3)
1. a turbosupercharger start/stop impact testing table, it is characterized in that: comprise the first loop and second servo loop, two cover turbosupercharger in two loops are identical, and share a firing chamber (1), combustor exit pipeline (2), high temperature shift valve (3), Ejector (18), each turbosupercharger is furnished with respective lubricating system, according to testing requirements, can automatically cutting off lubricating oil supply while stopping turbocharger operation, automatically connecting lubricating oil supply when starting supercharger;
First loop comprises firing chamber (1), combustor exit pipeline (2), high temperature shift valve (3), the first combustor exit pipeline branch road (4), the first compressor air inlet machine pipeline (5), the first pneumatic plant (6), the first turbine (7), the first turbine outlet pipeline (8), the first valve (16), the first pneumatic plant gas outlet (17), Ejector (18);
Second servo loop comprises firing chamber (1), combustor exit pipeline (2), high temperature shift valve (3), the second turbine outlet pipeline (9), the second turbine (10), the second pneumatic plant (11), the second compressor air inlet machine pipeline (12), the second combustor exit pipeline branch road (13), the second pneumatic plant gas outlet (14), the second valve (15), Ejector (18);
Firing chamber (1) is connected with high temperature shift valve (3) by combustor exit pipeline (2); High temperature shift valve (3) connects the first combustor exit pipeline branch road (4) and the second combustor exit pipeline branch road (13) respectively; The other end of the first combustor exit pipeline branch road (4) is connected with first turbine (7) of the first turbosupercharger; The other end of the second combustor exit pipeline branch road (13) is connected with second turbine (10) of the second turbosupercharger; Pneumatic plant can be driven while turbine to operate; First pneumatic plant (6) is connected with the first compressor air inlet machine pipeline (5), the first pneumatic plant gas outlet (17); First valve (16) is positioned on the first pneumatic plant gas outlet (17); Second pneumatic plant (11) is connected with the second compressor air inlet machine pipeline (12), the second pneumatic plant gas outlet (14); Second valve (15) is positioned on the second pneumatic plant gas outlet (14); First pneumatic plant gas outlet (17) is connected with two entrances of Ejector (18) respectively with the second pneumatic plant gas outlet (14); The outlet of Ejector (18) is connected with firing chamber 1.
2. a kind of turbosupercharger start/stop impact testing table as claimed in claim 1, is characterized in that: described first turbosupercharger comprises the first pneumatic plant (6) and the first turbine (7); Second turbosupercharger comprises the second pneumatic plant (11) and the second turbine (10).
3. a kind of turbosupercharger start/stop impact testing table as claimed in claim 1, it is characterized in that: the course of work is as follows: during the first loop works, the high temperature shift valve (3) being arranged in exhaust outlet of combustion chamber place connects the pipeline in the first loop, the first valve (16) in first loop is opened, and the second valve (15) in second servo loop is closed, high-temperature fuel gas enters the first turbine (7) again through high temperature shift valve (3) and the first combustor exit pipeline branch road (4), enters air after acting, first turbine (7) obtains energy and drives the first pneumatic plant (6) to operate from combustion gas, air is after the first pneumatic plant (6) compression, by the first valve (16) in the first loop, enter air inlet of combustion chamber, after the first loop stability runs, switching high temperature shift valve (3) makes waste gas flow in second servo loop, meanwhile, open the second valve (15) in second servo loop, the first valve (16) in first loop temporarily stays open state, now, first turbine (7) decelerate under inertia effect in first loop, the gaseous tension that first pneumatic plant (6) exports changes from high to low, there is the gas flow of elevated pressures when gas ejector (18), due to the throttling action in tapered cross section, speed raised pressure reduces, Ejector (18) produces ejector action for the gas in second servo loop, drive the gas flow firing chamber (1) in second servo loop, the second turbine (10) in second servo loop is started running by static under combustion gas effect, the second pneumatic plant (11) is driven to compress air, gas in second servo loop is flowing in combustion chamber (1) under the acting in conjunction of the second pneumatic plant (11) and Ejector (18), discharge in firing chamber (1) with after fuel combustion, the second turbine (10) is entered through high temperature shift valve (3), the second turbine (10) is made constantly to accelerate to realize starting, until reach the rotating speed preset, and the first turbine (7) in the first loop shuts down gradually owing to not having gas driven, in first pneumatic plant gas outlet (17), gaseous tension also reduces thereupon gradually, the first valve (16) in the first loop is closed when gaseous tension equals gaseous tension in firing chamber (1) in the first pneumatic plant gas outlet (17).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201510580380.5A CN105203288B (en) | 2015-09-11 | 2015-09-11 | A kind of turbocharger start/stop impact testing stand |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510580380.5A CN105203288B (en) | 2015-09-11 | 2015-09-11 | A kind of turbocharger start/stop impact testing stand |
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| CN105203288A true CN105203288A (en) | 2015-12-30 |
| CN105203288B CN105203288B (en) | 2018-07-27 |
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Cited By (3)
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| CN106596084A (en) * | 2016-12-08 | 2017-04-26 | 北京理工大学 | Device for testing start/stop service life of turbocharger |
| CN109888333A (en) * | 2019-04-24 | 2019-06-14 | 吉林大学 | A kind of hydrogen fuel cell cold start and emergency starting device based on injector |
| CN109888333B (en) * | 2019-04-24 | 2024-05-03 | 吉林大学 | Hydrogen fuel cell cold start and emergency start device based on ejector |
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| CN109888333A (en) * | 2019-04-24 | 2019-06-14 | 吉林大学 | A kind of hydrogen fuel cell cold start and emergency starting device based on injector |
| CN109888333B (en) * | 2019-04-24 | 2024-05-03 | 吉林大学 | Hydrogen fuel cell cold start and emergency start device based on ejector |
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| CN105203288B (en) | 2018-07-27 |
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