CN105203330A - Device for start and stop impact test of turbochargers - Google Patents
Device for start and stop impact test of turbochargers Download PDFInfo
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- CN105203330A CN105203330A CN201510580377.3A CN201510580377A CN105203330A CN 105203330 A CN105203330 A CN 105203330A CN 201510580377 A CN201510580377 A CN 201510580377A CN 105203330 A CN105203330 A CN 105203330A
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Abstract
The invention relates to a device for a start and stop impact test of turbochargers, and belongs to the technical field of power machinery. The device comprises a first loop, a second loop and an intermediate connecting valve 17, and the turbochargers and combustion chambers in the two loops are completely same. The invention further discloses a testing method for start and stop impact of the turbochargers, and a basis is supplied to the reliability of turbine start and stop impact. The device for the start and stop impact test of the turbochargers is scientific and reasonable in test table scheme, easy to achieve, stable and reliable and has the important application value for improving the reliability of the turbochargers.
Description
Technical field
The present invention relates to a kind of device for the test of turbosupercharger start/stop impact, 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 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 device for the test of turbosupercharger start/stop impact, this device 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.
It is a kind of that the device for the test of turbosupercharger start/stop impact comprises the first loop, second servo loop is connected valve with centre, two cover turbosupercharger in two loops are identical with firing chamber, 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 the first firing chamber, the first combustor exit pipeline, the first turbine, the first turbine outlet pipeline, the first compressor air inlet machine pipeline, the first pneumatic plant, the first blower outlet pipeline, first with Ejector, the first valve, the first combustion chamber charge pipeline of retaining valve;
Second servo loop comprises the second firing chamber, the second combustor exit pipeline, the second turbine, the second turbine outlet pipeline, the second pneumatic plant, the second compressor air inlet machine pipeline, the second pneumatic plant gas outlet, second with Ejector, the second valve, the second combustion chamber charge pipeline of retaining valve;
Annexation: the first firing chamber is connected with the first turbine of the first turbosupercharger by the first combustor exit pipeline; First pneumatic plant is connected with the first compressor air inlet machine pipeline, the first blower outlet pipeline respectively; The other end of the first blower outlet pipeline is connected with the A mouth of the Ejector of retaining valve with first; First is connected with the first valve with the C mouth of the Ejector of retaining valve; First valve is connected with the first firing chamber by the first combustion chamber charge pipeline; Second firing chamber is connected with the second turbine of the second turbosupercharger by the second combustor exit pipeline; Second pneumatic plant is connected with the second compressor air inlet machine pipeline, the second blower outlet pipeline respectively; The second blower outlet pipeline other end is connected with the D mouth of the Ejector of retaining valve with second; Second is connected with the second valve with the F mouth of the Ejector of retaining valve; Second valve is connected with the second firing chamber by the second combustion chamber charge pipeline; First is connected valve with the B mouth and second of the Ejector of retaining valve respectively with the E mouth of the Ejector of retaining valve connects with centre; First unidirectionally can flow to B mouth from A mouth with gas in the Ejector of retaining valve, and second unidirectionally can flow to E mouth from D mouth with gas in the Ejector of retaining valve.
The course of work:
(1) start: open the first valve, connect valve, close the second valve in the middle of closing, now the first loop is connected, and second servo loop disconnects, and start the first firing chamber, the heat-driven provided in the first firing chamber is issued to predetermined stabilized (steady-state) speed.
(2) handoff procedure: the first valve closing, meanwhile, centre connects valve open and stops the fuel delivery of the first firing chamber, the second valve open, and now the first loop disconnects, and second servo loop is connected; The first turbine in first loop and the first pneumatic plant are decelerated to stationary state gradually from fast state, the ducted gas of first blower outlet enters first with the A mouth of the Ejector of retaining valve under the drive of the first pneumatic plant dump energy, flowed out from B mouth by retaining valve, enter second firing chamber with the E mouth, second of the Ejector of retaining valve with the F mouth of the Ejector of retaining valve, the second valve and the second combustion chamber charge pipeline by the middle valve, second that connects successively again, in good time oil spout point connects valve in the middle of fighting and closing; After second servo loop is connected, second turbine and the second pneumatic plant accelerate to fast state from stationary state gradually, gas in second pneumatic plant gas outlet flows into second with the D mouth of the Ejector of retaining valve under the drive of the second pneumatic plant, flow out from F mouth, enter the second firing chamber by the second valve and the second combustion chamber charge pipeline successively again, the heat-driven provided in the second firing chamber is issued to predetermined stabilized (steady-state) speed.
(3) reverse handoff procedure: the first valve open, meanwhile, open middle connection valve, the second valve closing, now the first loop is connected, and second servo loop disconnects, and stops the fuel delivery of the second firing chamber simultaneously; The second turbine in second servo loop and the second pneumatic plant are decelerated to stationary state gradually from fast state, the ducted gas of second blower outlet enters second with the D mouth of the Ejector of retaining valve under the drive of the second pneumatic plant dump energy, flowed out from E mouth by retaining valve, the first firing chamber is entered, in good time oil spout igniting with the B mouth, first of the Ejector of retaining valve with the C mouth of the Ejector of retaining valve, the first valve and the first combustion chamber charge pipeline successively again by the middle valve, first that connects; After first loop is connected, first turbine and the first pneumatic plant accelerate to fast state from stationary state gradually, gas in first pneumatic plant gas outlet flows into first with the A mouth of the Ejector of retaining valve under the drive of the first pneumatic plant, flow out from C mouth, then enter the first firing chamber by the first valve and the first combustion chamber charge pipeline successively.
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, for a device for turbosupercharger start/stop impact test, effectively can be used for examining the reliability of turbosupercharger under start and stop operating mode, and 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.
Fig. 2 is first with the enlarged diagram of the Ejector of retaining valve.
Fig. 3 is second with the enlarged diagram of the Ejector of retaining valve.
Wherein, 1-first firing chamber, 2-first combustor exit pipeline, 3-first compressor air inlet machine pipeline, 4-first pneumatic plant, 5-first turbine, 6-first turbine outlet pipeline, 7-second turbine outlet pipeline, 8-second turbine, 9-second pneumatic plant, 10-second compressor air inlet machine pipeline, 11-second combustor exit pipeline, 12-second firing chamber, 13-second pneumatic plant gas outlet, 14-second combustion chamber charge pipeline, 15-second valve, 16-second is with the Ejector of retaining valve, valve is connected in the middle of 17-, 18-first is with the Ejector of retaining valve, 19-first valve, 20-first combustion chamber charge pipeline, 21-first blower outlet pipeline.
Embodiment
In order to make those skilled in the art person 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.
As shown in Figure 1, device comprises the first loop, second servo loop is connected valve 17 with centre, and two cover turbosupercharger in two loops are identical with firing chamber.
First turbosupercharger comprises the first pneumatic plant 4 and the first turbine 5; Second turbosupercharger comprises the second pneumatic plant 9 and the second turbine 8, and these two turbosupercharger are tested turbosupercharger.
First loop comprises Ejector 18, first valve 19, the first combustion chamber charge pipeline 20 of the first firing chamber 1, first combustor exit pipeline 2, first turbine 5, first turbine outlet pipeline 6, first compressor air inlet machine pipeline 3, first pneumatic plant 4, first blower outlet pipeline 21, first with retaining valve.
Second servo loop comprises Ejector 16, second valve 15, the second combustion chamber charge pipeline 14 of the second firing chamber 12, second combustor exit pipeline 11, second turbine 8, second turbine outlet pipeline 7, second pneumatic plant 9, second compressor air inlet machine pipeline 10, second pneumatic plant gas outlet 13, second with retaining valve.
Annexation: the first firing chamber 1 is connected with the first turbine 5 of the first turbosupercharger by the first combustor exit pipeline 2; First pneumatic plant 4 is connected with the first compressor air inlet machine pipeline 3, first blower outlet pipeline 21; First blower outlet pipeline 21 other end is connected with the A mouth of the Ejector 18 of retaining valve with first; First is connected with the first valve 19 with the C mouth of the Ejector 18 of retaining valve; First valve 19 is connected with the first firing chamber 1 by the first combustion chamber charge pipeline 20; Second firing chamber 12 is connected with the second turbine 8 of the second turbosupercharger by the second combustor exit pipeline 11; Second pneumatic plant 9 is connected with the second compressor air inlet machine pipeline 10, second blower outlet pipeline 13; Second blower outlet pipeline 13 other end is connected with the D mouth of the Ejector 16 of retaining valve with second; Second is connected with the second valve 15 with the F mouth of the Ejector 16 of retaining valve; Second valve 15 is connected with the second firing chamber 12 by the second combustion chamber charge pipeline 14; First is connected valve 17 with the B mouth and second of the Ejector 18 of retaining valve respectively with the E mouth of the Ejector 16 of retaining valve connects with centre; First unidirectionally can flow to B mouth from A mouth with gas in the Ejector 18 of retaining valve, and as shown in Figure 2, second unidirectionally can flow to E mouth from D mouth with gas in the Ejector 16 of retaining valve, as shown in Figure 3.
The startup optimization method concrete steps of device are as follows:
Step one. starter gear
Before startup, open the first valve 19, connect valve 17, close the second valve 15 in the middle of closing, now the first loop is connected, and second servo loop disconnects, and start the first firing chamber 1, the heat-driven provided in the first firing chamber 1 is issued to predetermined stabilized (steady-state) speed.
Step 2. handoff procedure
First valve 19 is closed, and meanwhile, the middle valve 17 that connects is opened and stops the fuel delivery of the first firing chamber 1, and the second valve 15 is opened, and now the first loop disconnects, and second servo loop is connected, the first turbine 5 in first loop and the first pneumatic plant 4 are decelerated to stationary state gradually from fast state, gas in first blower outlet pipeline 21 enters first with the A mouth of the Ejector 18 of retaining valve under the drive of the first pneumatic plant 4 dump energy, flowed out from B mouth by retaining valve, valve 17 is connected successively again by middle, second with the E mouth of the Ejector 16 of retaining valve, second with the F mouth of the Ejector 16 of retaining valve, second valve 15 and the second combustion chamber charge pipeline 14 enter the second firing chamber 12, in good time oil spout point connects valve 17 in the middle of fighting and closing, after second servo loop is connected, second turbine 8 and the second pneumatic plant 9 accelerate to fast state from stationary state gradually, gas in second pneumatic plant gas outlet 13 flows into second with the D mouth of the Ejector 16 of retaining valve under the drive of the second pneumatic plant 9, flow out from F mouth, enter the second firing chamber 12 by the second valve 15 and the second combustion chamber charge pipeline 14 successively again, the heat-driven provided in the second firing chamber 12 is issued to predetermined stabilized (steady-state) speed.
Step 3. oppositely handoff procedure
First valve 19 is opened, and meanwhile, open middle valve 17, second valve 15 that connects and close, now the first loop is connected, and second servo loop disconnects, and stops the fuel delivery of the second firing chamber 12 simultaneously; The second turbine 8 in second servo loop and the second pneumatic plant 9 are decelerated to stationary state gradually from fast state, gas in second blower outlet pipeline 13 enters second with the D mouth of the Ejector 16 of retaining valve under the drive of the second pneumatic plant 9 dump energy, flowed out from E mouth by retaining valve, the first firing chamber 1 is entered, in good time oil spout igniting with the B mouth, first of the Ejector 18 of retaining valve with the C mouth of the Ejector 16 of retaining valve, the first valve 19 and the first combustion chamber charge pipeline 20 successively again by the middle valve 17, first that connects; After first loop is connected, first turbine 5 and the first pneumatic plant 4 accelerate to fast state from stationary state gradually, gas in first pneumatic plant gas outlet 21 flows into first with the A mouth of the Ejector 18 of retaining valve under the drive of the first pneumatic plant 4, flow out from C mouth, then enter the first firing chamber 1 by the first valve 19 and the first combustion chamber charge pipeline 20 successively.
Step 4. repeatedly repeat step 2 and step 3, the test of turbosupercharger start/stop impact can be realized.
Above adjustment process can manual adjustments, also can be realized automatically regulating by special controller.
Claims (4)
1. the device for the test of turbosupercharger start/stop impact, it is characterized in that: comprise the first loop, second servo loop is connected valve (17) with centre, two cover turbosupercharger in two loops are identical with firing chamber, 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 the first firing chamber (1), the first combustor exit pipeline (2), the first turbine (5), the first turbine outlet pipeline (6), the first compressor air inlet machine pipeline (3), the first pneumatic plant (4), the first blower outlet pipeline (21), first with Ejector (18), the first valve (19), the first combustion chamber charge pipeline (20) of retaining valve;
Second servo loop comprises the second firing chamber (12), the second combustor exit pipeline (11), the second turbine (8), the second turbine outlet pipeline (7), the second pneumatic plant (9), the second compressor air inlet machine pipeline (10), the second pneumatic plant gas outlet (13), second with Ejector (16), the second valve (15), the second combustion chamber charge pipeline (14) of retaining valve;
Annexation: the first firing chamber (1) is connected with first turbine (5) of the first turbosupercharger by the first combustor exit pipeline (2); First pneumatic plant (4) is connected with the first compressor air inlet machine pipeline (3), the first blower outlet pipeline (21) respectively; The other end of the first blower outlet pipeline (21) is connected with the A mouth of the Ejector (18) of retaining valve with first; First is connected with the first valve (19) with the C mouth of the Ejector (18) of retaining valve; First valve (19) is connected with the first firing chamber (1) by the first combustion chamber charge pipeline (20); Second firing chamber (12) is connected with second turbine (8) of the second turbosupercharger by the second combustor exit pipeline (11); Second pneumatic plant (9) is connected with the second compressor air inlet machine pipeline (10), the second blower outlet pipeline (13) respectively; Second blower outlet pipeline (13) other end is connected with the D mouth of the Ejector (16) of retaining valve with second; Second is connected with the second valve (15) with the F mouth of the Ejector (16) of retaining valve; Second valve (15) is connected with the second firing chamber (12) by the second combustion chamber charge pipeline (14); First is connected valve (17) with the B mouth and second of the Ejector (18) of retaining valve respectively with the E mouth of the Ejector (16) of retaining valve connects with centre; First unidirectionally can flow to B mouth from A mouth with gas in the Ejector (18) of retaining valve, and second unidirectionally can flow to E mouth from D mouth with gas in the Ejector (16) of retaining valve.
2. a kind of device for the test of turbosupercharger start/stop impact as claimed in claim 1, is characterized in that: described first turbosupercharger comprises the first pneumatic plant (4) and the first turbine (5); Second turbosupercharger comprises the second pneumatic plant (9) and the second turbine (8).
3. a kind of method of testing of device for the test of turbosupercharger start/stop impact as claimed in claim 1, is characterized in that: concrete steps are as follows:
(1) start: open the first valve (19), valve (17) is connected in the middle of closing, close the second valve (15), now the first loop is connected, second servo loop disconnects, start the first firing chamber (1), the heat-driven provided in the first firing chamber (1) is issued to predetermined stabilized (steady-state) speed;
(2) handoff procedure: the first valve (19) is closed, meanwhile, the middle valve (17) that connects is opened and stops the fuel delivery of the first firing chamber (1), and the second valve (15) is opened, now the first loop disconnects, and second servo loop is connected, the first turbine (5) in first loop and the first pneumatic plant (4) are decelerated to stationary state gradually from fast state, gas in first blower outlet pipeline (21) enters first with the A mouth of the Ejector (18) of retaining valve under the drive of the first pneumatic plant (4) dump energy, flowed out from B mouth by retaining valve, valve (17) is connected successively again by middle, second with the E mouth of the Ejector (16) of retaining valve, second with the F mouth of the Ejector (16) of retaining valve, second valve (15) and the second combustion chamber charge pipeline (14) enter the second firing chamber (12), in good time oil spout point connects valve (17) in the middle of fighting and closing, after second servo loop is connected, second turbine (8) and the second pneumatic plant (9) accelerate to fast state from stationary state gradually, gas in second pneumatic plant gas outlet (13) under the drive of the second pneumatic plant (9) inflow second with the D mouth of the Ejector (16) of retaining valve, flow out from F mouth, enter the second firing chamber (12) by the second valve (15) and the second combustion chamber charge pipeline (14) successively again, the heat-driven provided in the second firing chamber (12) is issued to predetermined stabilized (steady-state) speed,
(3) reverse handoff procedure: the first valve (19) is opened, meanwhile, open middle connection valve (17), the second valve (15) is closed, and now the first loop is connected, second servo loop disconnection, the second turbine (8) in second servo loop and the second pneumatic plant (9) are decelerated to stationary state gradually from fast state, gas in second blower outlet pipeline (13) enters second with the D mouth of the Ejector (16) of retaining valve under the drive of the second pneumatic plant (9) dump energy, flowed out from E mouth by retaining valve, valve (17) is connected successively again by middle, first with the B mouth of the Ejector (18) of retaining valve, first with the C mouth of the Ejector (16) of retaining valve, first valve (19) and the first combustion chamber charge pipeline (20) enter the first firing chamber (1), in good time oil spout igniting, after first loop is connected, first turbine (5) and the first pneumatic plant (4) accelerate to fast state from stationary state gradually, gas in first pneumatic plant gas outlet (21) under the drive of the first pneumatic plant (4) inflow first with the A mouth of the Ejector (18) of retaining valve, flow out from C mouth, then enter the first firing chamber (1) by the first valve (19) and the first combustion chamber charge pipeline (20) successively,
(4) repeatedly repeat step (2) and step (3), namely realize the test of turbosupercharger start/stop impact.
4. a kind of method of testing of device for the test of turbosupercharger start/stop impact as claimed in claim 3, it is characterized in that: in handoff procedure, the gas flow flowing through firing chamber has fluctuation, by the fluctuation automatically regulating distributive value to adapt to gas flow, thus realize smooth combustion and smooth transition.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510580377.3A CN105203330B (en) | 2015-09-11 | 2015-09-11 | A kind of device for the test of turbocharger start/stop impact |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510580377.3A CN105203330B (en) | 2015-09-11 | 2015-09-11 | A kind of device for the test of turbocharger start/stop impact |
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| Publication Number | Publication Date |
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| CN105203330A true CN105203330A (en) | 2015-12-30 |
| CN105203330B CN105203330B (en) | 2019-02-19 |
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| CN201510580377.3A Expired - Fee Related CN105203330B (en) | 2015-09-11 | 2015-09-11 | A kind of device for the test of turbocharger start/stop impact |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106596084A (en) * | 2016-12-08 | 2017-04-26 | 北京理工大学 | Device for testing start/stop service life of turbocharger |
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| CN105203330B (en) | 2019-02-19 |
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