CN203688224U - Engine driven air pressure system high altitude simulation tester - Google Patents
Engine driven air pressure system high altitude simulation tester Download PDFInfo
- Publication number
- CN203688224U CN203688224U CN201320744336.XU CN201320744336U CN203688224U CN 203688224 U CN203688224 U CN 203688224U CN 201320744336 U CN201320744336 U CN 201320744336U CN 203688224 U CN203688224 U CN 203688224U
- Authority
- CN
- China
- Prior art keywords
- engine
- air
- baric systerm
- air compressor
- tank
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Images
Landscapes
- Testing Of Engines (AREA)
Abstract
The utility model discloses an engine driven air pressure system high altitude simulation tester comprising an air pressure system and a power system; different altitude low pressure environments can be simulated so as to carry out air compressor plateau simulation tests. Performance changes of the engine and the engine driven air pressure system under different altitude air pressures are tested, so the plateau performance of the air pressure system using the engine as the power source is examined; under different altitude air pressures, the time of boosting the air pressure of an air tank from 0 to every 100kPa is tested, the needed time of reaching a highest pressure of the air tank is tested, and air intake flow references are tested.
Description
Technical field
The utility model relates to engine driven baric systerm technical field, particularly relates to the high height above sea level simulation test device of a kind of engine driven baric systerm.
Background technology
Baric systerm take engine as power source, in the time of the operation of highlands, there will be the problems such as serviceability deterioration, work capacity decline, failure rate rising and reliability variation conventionally.Trace it to its cause and be mainly following 2 points:
1. the impact of altitude environment on engine performance
Be mainly reflected in: dynamic property declines, economy worsens; Turbocharger performance, the emission behavior variation of coupling; Thermal load increases, and cooling system heat-sinking capability declines; The aspects such as cold start difficulty.
2. the impact of altitude environment on baric systerm performance
Be mainly reflected in: cause the baric systerm performance of mating with it to be subject to certain limitation and impact because engine performance declines, altitude environment atmospheric pressure is low and karaburan is large, not only can cause that air compressor air inflow reduces, impermeability declines, compressor gas circuit and filter cleaner easily stop up, cause the appearance of the faults such as system output pressure is not enough and action is not steady, even stuck; And can make to contain a large amount of impurity from the pressurized air of air compressor output, greatly reduce reliability and the serviceable life of baric systerm.
So research and the impact of discussion high altitude localities atmospheric conditions on the baric systerm performance take engine as power source, be basis and the prerequisite of carrying out the high height above sea level performance study of mechanized equipment.
The altitude environment test of the baric systerm take engine as power source is mainly divided into plateau site test and Plain laboratory simulation test, due to plateau site test have repeatable poor, test period is long, the many disadvantages such as climate parameter is non-adjustable, be only suitable for verifying on the spot for real vehicle, and Plain laboratory simulation test has and is not subject to area, season and time restriction, can reappear natural conditions, simulation extremum conditions, can be under same environmental conditions the outstanding advantages such as revision test repeatedly, become the one ideal of research altitude environment to engine and drive system performance impact thereof, the economic best approach.
Utility model content
The purpose of this utility model is to provide the high height above sea level simulation test device of a kind of engine driven baric systerm, can to altitude environment to motor car engine performance impact provide rationally, theoretical foundation accurately.
For realizing the technical scheme that the purpose of this utility model adopts be: the high height above sea level simulation test device of a kind of engine driven baric systerm, is characterized in that comprising baric systerm and power system thereof;
Described power system comprises engine, the admission pressure simulation system being communicated with engine intake, discharge pressure simulation system, dynamometer machine and the engine control system being communicated with engine exhaust port; Described engine and dynamometer machine are coaxially installed, by the performance parameter of the indirect observing and controlling engine of engine control system;
Described baric systerm comprises that air compressor, air tank and the variable valve being connected between air compressor and air tank by pipeline thereof form; The air intake opening of described air compressor is connected with described admission pressure simulation system;
The air compressor of described baric systerm is by described engine driven.
Described admission pressure simulation system forms by air inlet pressure stabilizing chamber with the air inlet electric control valve being positioned on air inlet pressure stabilizing chamber entrance pipe, and the outlet of described air inlet pressure stabilizing chamber is communicated with the air intake opening of described engine intake and described air compressor by pipeline respectively.
Described discharge pressure simulation system is by exhaust pressurizer tank, vacuum pump and be connected to the outlet of exhaust pressurizer tank by pipeline and form with the exhaust electric control valve between vacuum pump, described engine exhaust port is connected with heat exchanger, and the entrance of described heat exchanger and described exhaust pressurizer tank passes through pipeline connection.
Can control engine air intake opening and the environmental pressure at exhausr port position by described air inlet electric control valve and exhaust electric control valve, in order to the real atmosphere pressure in simulated high altitude area.
The course of work of the present utility model and principle are: first, warm-up the engine, is released into air tank internal gas pressure identically with environment atmospheric pressure subsequently, and air compressor air intake opening is connected with air inlet pressure stabilizing chamber; Then, start vacuum pump, open the connection valve of air inlet pressure stabilizing chamber and exhaust pressurizer tank, reconcile air inlet electric control valve and exhaust electric control valve, simulate different height above sea level environment under low pressure, carry out air compressor plateau simulation test.By the performance change of engine and the baric systerm that drives thereof under test Different Altitude atmospheric pressure, mainly comprise that under Different Altitude atmospheric pressure, air tank air pressure reaches the parameters such as top pressure required time and charge flow rate since time, the air tank of 0 every rising 100kPa, the Performance on Plateau of the baric systerm of examination take engine as power source.
Accompanying drawing explanation
Fig. 1 is the structured flowchart of the high height above sea level simulation test device of the utility model engine driven baric systerm.
Embodiment
Below in conjunction with specific embodiment, the utility model is described in further detail.Should be appreciated that specific embodiment described herein is only in order to explain the utility model, and be not used in restriction the utility model.
Embodiment:
Referring to accompanying drawing 1, the high height above sea level simulation test device of the utility model engine driven baric systerm, is characterized in that comprising baric systerm and power system thereof.
Described power system comprises diesel engine 1 (engine), also be provided with dynamometer machine 2 and engine control system 3 for observing and controlling diesel engine 1 operating condition, described diesel engine 1 is coaxially installed with dynamometer machine 2, by the performance parameter of engine control system 3 indirect observing and controlling diesel engines 1;
Power system also comprises the admission pressure simulation system being communicated with the air intake opening of diesel engine 1, the discharge pressure simulation system being communicated with the exhausr port of diesel engine 1.
Admission pressure simulation system comprises air inlet pressure stabilizing chamber 4, air inlet electric control valve 5 is housed on the entrance pipe of air inlet pressure stabilizing chamber 4, air inlet electric control valve 5 can be controlled the air inflow of air inlet pressure stabilizing chamber 4, and the outlet of air inlet pressure stabilizing chamber 4 is communicated with the air intake opening of diesel engine 1 by pipeline.
Discharge pressure simulation system comprises exhaust pressurizer tank 6 and vacuum pump 7, between the outlet of exhaust pressurizer tank 6 and vacuum pump 7, exhaust electric control valve 8 is housed, and can regulate the air capacity of exhaust pressurizer tank 6 when vacuum pump 7 starts by exhaust electric control valve 8; The exhausr port of diesel engine 1 is connected with the air intake opening of heat exchanger 9, and described heat exchanger 9 passes through pipeline connection with the entrance of described exhaust pressurizer tank 6; The object of heat exchanger 9 is to reduce the delivery temperature of diesel engine 1, to meet the requirement of vacuum pump 7 for working temperature, below 50 ℃.
Described baric systerm comprises that air compressor 10, air tank 11 and the variable valve 12 being connected between air compressor 10 and air tank 11 by pipeline thereof form; The air intake opening of described air compressor 10 is communicated with air inlet pressure stabilizing chamber 4 exhausr ports by pipeline.The air compressor of part city mid-sales is the integrated variable valve that is provided with also, and variable valve 12 so just needn't be installed separately again.The air compressor 10 of described baric systerm is arranged on described diesel engine 1, and the transmission of setting up baric systerm and engine system contacts, and just can drive air compressor 10 like this by diesel engine 1.
The conventional pipeline instrument such as valve or pressure-indication means can be set as required in above-mentioned simulation test device, so that control, overhaul or gather real time data at each pipeline position.
Principle of work: first, preheating diesel engine 1, is released into air tank 11 internal gas pressures identically with environment atmospheric pressure subsequently, and the air intake opening of air compressor 10 is connected with air inlet pressure stabilizing chamber 4; Then, start vacuum pump 7, open the connection valve of air inlet pressure stabilizing chamber 4 and exhaust pressurizer tank 6, regulate air inlet electric control valve 5 and exhaust electric control valve 8, simulate different height above sea level environment under low pressure, carry out air compressor plateau simulation test.By the performance change of engine and the baric systerm that drives thereof under test Different Altitude atmospheric pressure, mainly comprise that under Different Altitude atmospheric pressure, air tank air pressure reaches the parameters such as top pressure required time and charge flow rate since time, the air tank of 0 every rising 100kPa, the Performance on Plateau of the baric systerm of examination take engine as power source.
The technical indicator that in the present embodiment, simulation test device can be realized is:
(1) engine breathing pressure and air compressor admission pressure control system parameter: 101kPa～47kPa, Ya power control Jing Du≤± 1.5kPa (buffer tank), pressure regulates Shi Jian≤3min;
(2) tested engine maximum weight 1500kg, full admission amount 30m3/min.
The above is only preferred implementation of the present utility model; it should be noted that; for those skilled in the art; do not departing under the prerequisite of the utility model principle; can also make some improvements and modifications, these improvements and modifications also should be considered as protection domain of the present utility model.
Claims (3)
1. the high height above sea level simulation test device of engine driven baric systerm, is characterized in that: comprise baric systerm and power system thereof;
Described power system comprises engine, the admission pressure simulation system being communicated with engine intake, discharge pressure simulation system, dynamometer machine and the engine control system being communicated with engine exhaust port; Described engine and dynamometer machine are coaxially installed, by the performance parameter of the indirect observing and controlling engine of engine control system;
Described baric systerm comprises that air compressor, air tank and the variable valve being connected between air compressor and air tank by pipeline thereof form; The air intake opening of described air compressor is connected with described admission pressure simulation system;
The air compressor of described baric systerm is by described engine driven.
2. the high height above sea level simulation test device of engine driven baric systerm according to claim 1, it is characterized in that described admission pressure simulation system forms by air inlet pressure stabilizing chamber with the air inlet electric control valve being positioned on air inlet pressure stabilizing chamber entrance pipe, the outlet of described air inlet pressure stabilizing chamber is communicated with the air intake opening of described engine intake and described air compressor by pipeline respectively.
3. the high height above sea level simulation test device of engine driven baric systerm according to claim 1, it is characterized in that described discharge pressure simulation system by exhaust pressurizer tank, vacuum pump and be connected to the outlet of exhaust pressurizer tank by pipeline forming with the exhaust electric control valve between vacuum pump, described engine exhaust port is connected with heat exchanger, and the entrance of described heat exchanger and described exhaust pressurizer tank passes through pipeline connection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320744336.XU CN203688224U (en) | 2013-11-22 | 2013-11-22 | Engine driven air pressure system high altitude simulation tester |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320744336.XU CN203688224U (en) | 2013-11-22 | 2013-11-22 | Engine driven air pressure system high altitude simulation tester |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203688224U true CN203688224U (en) | 2014-07-02 |
Family
ID=51010111
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320744336.XU Expired - Fee Related CN203688224U (en) | 2013-11-22 | 2013-11-22 | Engine driven air pressure system high altitude simulation tester |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203688224U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103575540A (en) * | 2013-11-22 | 2014-02-12 | 中国人民解放军军事交通学院 | High-altitude simulation test device of engine-driven pressure system |
| CN105866584A (en) * | 2016-04-19 | 2016-08-17 | 哈尔滨东安发动机（集团）有限公司 | Aero-engine indirect igniter tester |
| CN107727400A (en) * | 2017-09-11 | 2018-02-23 | 奇瑞汽车股份有限公司 | Engine charge pressure test system and its control method |
| CN114323667A (en) * | 2022-01-06 | 2022-04-12 | 中国科学院工程热物理研究所 | Air compressor high-altitude environment test system and adjusting method |
-
2013
- 2013-11-22 CN CN201320744336.XU patent/CN203688224U/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103575540A (en) * | 2013-11-22 | 2014-02-12 | 中国人民解放军军事交通学院 | High-altitude simulation test device of engine-driven pressure system |
| CN105866584A (en) * | 2016-04-19 | 2016-08-17 | 哈尔滨东安发动机（集团）有限公司 | Aero-engine indirect igniter tester |
| CN105866584B (en) * | 2016-04-19 | 2018-10-19 | 哈尔滨东安发动机（集团）有限公司 | The indirect igniter exerciser of aero-engine |
| CN107727400A (en) * | 2017-09-11 | 2018-02-23 | 奇瑞汽车股份有限公司 | Engine charge pressure test system and its control method |
| CN114323667A (en) * | 2022-01-06 | 2022-04-12 | 中国科学院工程热物理研究所 | Air compressor high-altitude environment test system and adjusting method |
| CN114323667B (en) * | 2022-01-06 | 2023-07-25 | 中国科学院工程热物理研究所 | High-altitude environment test system and adjusting method for air compressor |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103575540A (en) | High-altitude simulation test device of engine-driven pressure system | |
| CN101672729B (en) | High-altitude and low-pressure characteristic simulation test station of air compressor in internal-combustion engine | |
| CN201600243U (en) | Experimental device for detecting engine performance under simulated altitude environment | |
| CN101788384B (en) | Engine plateau environment laboratory | |
| CN104634578B (en) | Aviation turbocharging internal-combustion engines full ambient engine altitude test system and test method | |
| CN102023096B (en) | Internal-flow high-altitude simulation test device and test method of aviation piston engine | |
| CN102221467B (en) | High-altitude simulation testing system for piston engine | |
| CN203688224U (en) | Engine driven air pressure system high altitude simulation tester | |
| CN208672312U (en) | The low-temp low-pressure experimental cabin of simulated altitude | |
| CN101738322A (en) | Vehicle high altitude performance simulation test system | |
| CN102818706B (en) | Simulating test method for plateau performance of supercharged engine and device for implementing simulating test method | |
| CN202886106U (en) | Submarine large-power diesel engine overland test device | |
| CN111927623A (en) | High-altitude ventilation and dynamic performance simulation test platform for two-stroke aviation piston engine | |
| CN201600244U (en) | Simulation device used for determining car performance at high altitude | |
| CN1437010A (en) | Internal combustion engine performance low-pressure simulating test stage | |
| CN111894882A (en) | Variable-altitude two-stage centrifugal compressor characteristic test system | |
| CN101832845B (en) | Self-correcting system and method for sealing test of exhaust gas turbocharger | |
| CN202451313U (en) | Accessory supercharging system for diesel rack testing | |
| CN102434333B (en) | Auxiliary pressurization system for diesel engine bench test and using method of auxiliary pressurization system | |
| CN203083828U (en) | Plateau performance simulation test system of engine oxygen enrichment combustion-supporting device | |
| CN110927575A (en) | High-altitude performance simulation test bed for generator set | |
| RU2403547C1 (en) | Test stand | |
| Galindo et al. | Description and performance analysis of a flow test rig to simulate altitude pressure variation for internal combustion engines testing | |
| CN2828782Y (en) | High elevation, low pressure simulator stand for fuel heater | |
| CN212111690U (en) | High-altitude performance simulation test bed for generator set |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20140702 Termination date: 20151122 |
|
| EXPY | Termination of patent right or utility model |