CN102866017B - Altitude environment simulation test cabin for internal combustion power equipment - Google Patents
Altitude environment simulation test cabin for internal combustion power equipment Download PDFInfo
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- CN102866017B CN102866017B CN201110190551.5A CN201110190551A CN102866017B CN 102866017 B CN102866017 B CN 102866017B CN 201110190551 A CN201110190551 A CN 201110190551A CN 102866017 B CN102866017 B CN 102866017B
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Abstract
The invention discloses a kind of altitude environment simulation test cabin for internal combustion power equipment, comprise cabin body, this cabin body is divided into normal temperature and pressure district and the altitude environment simulation region for placing Devices to test by partition, described normal temperature and pressure district is provided with the dynamometer machine for detecting Devices to test, be provided with the air supply system be communicated with altitude environment simulation region by supply air line, be provided with the first vacuum system and the second vacuum system that are connected with Devices to test exhausr port and altitude environment simulation region respectively by vacuum line.Altitude environment simulation test cabin for internal combustion power equipment of the present invention can simulate the test condition such as infrabar, height epidemic disaster, and according to testing requirements, experimental enviroment condition is controlled, complete the record to experimental enviroment data and controling parameters and process, video monitoring and record process of the test.
Description
Technical field
The present invention relates to a kind of boiler-plate, particularly relating to a kind of altitude environment boiler-plate for testing inner combustion power equipment performance.
Background technology
In recent years, along with China's Qinghai-xizang Plateau Region national defence, the continuing to increase of economic construction and social development paces, all kinds of inner combustion power equipments run in highlands are under the severe natural climate conditions such as the distinctive low-temperature and low-pressure in highlands, each leading indicators such as dynamic property, economy, startability, thermal equilibrium all have decline in various degree, cause the altitude environment adaptability of these equipment general not good, so how effectively the altitude environment adaptability of research and raising power-equipment more and more has very important status.
For the adaptive experimental study means of inner combustion power equipment altitude environment, mainly be divided into the large class of the former simulation test two of plateau site test peace, because Plain simulation test has the advantages such as cost is low, favorable repeatability, analog parameter can regulate arbitrarily, the test period is short, be subject to very big attention in environmental test field at present.
At present, Plain simulation test many employings altitude environment boiler-plate mode, is placed in boiler-plate body by inner combustion power equipment, cabin body is implemented to the air pressure vacuumizing to reduce in cabin.Owing to discharging high-temperature gas after inner combustion power equipment startup, the temperature and pressure in the body of cabin is constantly raised, so the pressure change in the body of cabin is relatively more violent, very difficult accurate simulation goes out real altitude environment.
Summary of the invention
The invention provides a kind of inner combustion power equipment altitude environment boiler-plate that steadily can reduce pressure in the body of cabin.
A kind of altitude environment simulation test cabin for internal combustion power equipment, comprise cabin body, this cabin body is divided into normal temperature and pressure district and the altitude environment simulation region for placing Devices to test by partition, described normal temperature and pressure district is provided with the dynamometer machine for detecting Devices to test, be provided with the air supply system be communicated with altitude environment simulation region by supply air line, be provided with the first vacuum system and the second vacuum system that are connected with Devices to test exhausr port and altitude environment simulation region respectively by vacuum line.
The first described vacuum system, from Devices to test exhaust port side, comprises heat interchanger, surge tank, by-pass valve control and vacuum pump successively.
The second described vacuum system, from the end of altitude environment simulation region, comprises heat interchanger, by-pass valve control and vacuum pump successively.
Environmental parameter acquisition system is provided with in described altitude environment simulation region, Measurement and Control System is provided with in described normal temperature and pressure district, Measurement and Control System described in the signal output part of described environmental parameter acquisition system is accessed by circuit, the circuit part of described air supply system, the first vacuum system and the second vacuum system all accesses and is controlled by described Measurement and Control System.
Described air supply system comprises for carrying the pressure fan of air to supply air line and acting on temperature control equipment and the humidity control apparatus of air in supply air line.
Be provided with the ultraviolet ray generating apparatus acting on altitude environment simulation region.Can install in appropriate position, sending can the ultraviolet radiation of simulated high altitude environment, and the product affected by Ultraviolet radiation for some or material provide experimental enviroment.The circuit part of this ultraviolet ray generating apparatus accesses and is controlled by described Measurement and Control System.
Described cabin body adopts integrated steel-structure form, for increasing compressive resistance, and the inside and outside all reinforcements of steel plate; By cut off will be divided into Cang Ti normal temperature and pressure district and altitude environment simulation region, altitude environment simulation region and cabin external body environment are isolated, and under height above sea level 6000m can be met infrabar to the requirement of structural mechanical property.
Cut off the material using heat-insulation and heat-preservation and good pressure-resistant performance, iron floor is installed on the ground of compartment, and in order to be incubated, the inwall of altitude environment simulation region or outer wall are with color steel sandwich thermal insulation board.
Environmental parameter acquisition system is multiple corresponding sensors, can gather altitude environment simulation region environmental parameter, such as air pressure, temperature, humidity, harmful gas concentration etc., and the parameter of collection is sent to Measurement and Control System.
Measurement and Control System is as the control system of whole altitude environment simulation test cabin for internal combustion power equipment, by the parameter gathered, and according to Test Condition Requirements, control signal is exported to air supply system, the first vacuum system and the second vacuum system, for controlling each control panel, as pump, valve, motor, switch etc.Set up the condition that the experimental enviroment that meets testing requirements and altitude environment simulation region normally use.
The effect of air supply system provides stable source of the gas to the air-breathing of Devices to test.Outdoor new wind is first after air strainer, and the dust impurity in removing air, then enters pressure fan.
In order to the low temperature environment of altitude environment simulation region, provide enough amount of cooling water take away Devices to test (engine) run in the heat distributed, this just need to pressure fan export air precooling to regulate temperature.
Temperature control equipment in air supply system and humidity control apparatus can regulate in altitude environment simulation region carry the temperature and humidity of air, temperature control equipment can utilize refrigeration plant of the prior art and firing equipment, air in supply air line, by the exchange heat between the heat interchanger of refrigeration plant and firing equipment, realizes the adjustment of temperature.
In like manner, described humidity control apparatus can utilize humidification of the prior art, dehumidification equipment, regulates the water vapour content of air, to provide required humidity environment to altitude environment simulation region.
In order to monitor the running status of Devices to test in real time, be provided with video system, the circuit part of video system accesses and is controlled by described Measurement and Control System.Video system can comprise high definition video camera, demoder and DVR etc.
In addition, in whole altitude environment simulation test cabin for internal combustion power equipment, also some auxiliary devices can be installed, such as illuminating lamp, compressed air supply system, window for keeping pressure balance, hanging mechanism etc.
Altitude environment simulation test cabin for internal combustion power equipment of the present invention can simulate the test condition such as infrabar, height epidemic disaster, and according to testing requirements, experimental enviroment condition is controlled, complete the record to experimental enviroment data and controling parameters and process, video monitoring and record process of the test, the parameter such as atmospheric pressure, temperature, humidity, uitraviolet intensity of altitude environment simulation region can regulate arbitrarily in the limit range of design.
The system such as hydraulic system, baric systerm of engine and its driving or assembly can be placed in altitude environment simulation region jointly in addition and test, the Performance on Plateau of these backup systems or assembly can be obtained, therefore altitude environment simulation test cabin for internal combustion power equipment has tested object widely, can contain power system, hydraulic system, baric systerm, material etc.
Accompanying drawing explanation
Fig. 1 is the composition schematic diagram of altitude environment simulation test cabin for internal combustion power equipment of the present invention.
Embodiment
See accompanying drawing, a kind of altitude environment simulation test cabin for internal combustion power equipment of the present invention, comprise cabin body 1, cabin body 1 is divided into normal temperature and pressure district 2 and the altitude environment simulation region 3 for placing Devices to test 4 by partition.Cabin body adopts integrated steel-structure form, and steel plate is inside and outside with reinforcement, and the outer wall of altitude environment simulation region 3 is with color steel sandwich thermal insulation board.
Be provided with the air supply system be communicated with altitude environment simulation region 3 by supply air line 9, air supply system comprises for carrying the pressure fan 7 of air to supply air line 9 and acting on temperature, the humidity control apparatus 8 of air in supply air line 9.Supply air line 9 can be installed necessary by-pass valve control and filtrator.
Temperature, humidity control apparatus 8 can regulate in altitude environment simulation region 3 carry the temperature and humidity of air, temperature control equipment can utilize refrigeration plant of the prior art and firing equipment, air in supply air line, by the exchange heat between the heat interchanger of refrigeration plant and firing equipment, realizes the adjustment of temperature.In like manner, humidity control apparatus can utilize humidification of the prior art, dehumidification equipment, regulates the water vapour content of air, to provide required humidity environment to altitude environment simulation region 3.
Be provided with the first vacuum system 5 be connected with Devices to test 4 exhausr port by vacuum line.First vacuum system 5, from Devices to test 4 exhaust port side, comprises heat interchanger 11, surge tank 10, by-pass valve control and vacuum pump 12 successively.
Be provided with and be connected the second vacuum system 6 by vacuum line with altitude environment simulation region.Second vacuum system 6, from the end of altitude environment simulation region 3, comprises heat interchanger 14, by-pass valve control and vacuum pump 13 successively.
Environmental parameter acquisition system (not shown) is provided with in altitude environment simulation region 3, Measurement and Control System 2 (not shown) is provided with in normal temperature and pressure district, environmental parameter acquisition system is several sensors, the environmental parameter of altitude environment simulation region 3 can be gathered, such as air pressure, temperature, humidity, harmful gas concentration etc., and the parameter of collection is sent to Measurement and Control System.
The ultraviolet ray generating apparatus be also provided with in altitude environment simulation region 3, sending can the ultraviolet radiation of simulated high altitude environment.
In order to the running status of Real-Time Monitoring Devices to test, be also provided with video system in altitude environment simulation region 3, video system can comprise high definition video camera, demoder and DVR etc.
In addition, also some auxiliary devices can be installed, such as illuminating lamp, compressed air supply system, window for keeping pressure balance, hanging mechanism etc.
In whole altitude environment simulation test cabin for internal combustion power equipment, each consuming parts that electric signal can be utilized to control all can be accessed by circuit and be controlled by Measurement and Control System.
Measurement and Control System is as the control system of whole altitude environment simulation test cabin for internal combustion power equipment, by the parameter gathered, and according to Test Condition Requirements, control signal is exported to air supply system, the first vacuum system, the second vacuum system, ultraviolet ray generating apparatus etc., for controlling each control panel, as pump, valve, motor, switch etc.Set up the condition that the experimental enviroment that meets testing requirements and altitude environment simulation region normally use.
Altitude environment simulation region and Devices to test regulate concrete principle to be: when Devices to test is higher than needs low-pressure starting, connects the second vacuum system and take out negative pressure to altitude environment simulation region; Meanwhile, utilize the vacuum pump in the first vacuum system to take out negative pressure to surge tank, make the target setting value that surge tank pressure reaches consistent with altitude environment simulation region negative pressure, and then start Devices to test.
When needing the plateau runnability detecting Devices to test, air inlet swabbing action after utilizing Devices to test (engine) to start directly is bled in the altitude environment simulation region meeting negative pressure requirements, simultaneously, utilize air supply system to regulate altitude environment simulation region pressure in real time, meet setting value; The simulation of Devices to test discharge pressure is then realized by the real-time adjustment of the first vacuum system.
Temperature, humidity control apparatus can be utilized automatically to regulate altitude environment simulation region environmental parameter simultaneously.
Connection between Devices to test and dynamometer machine, and dynamometer machine itself all can adopt prior art, when Devices to test runs under the simulated environment set, is carried out the performance of detecting and assessing Devices to test by dynamometer machine.
Altitude environment simulation test cabin for internal combustion power equipment the key technical indexes of the present invention is as follows:
1) when engine normally runs, altitude environment simulation region and buffering pressure tank range of adjustment: 101 ~ 47kPa (height above sea level 0 ~ 6000m);
2) engine start operating mode, altitude environment simulation region pressure regulation spectrum: 101 ~ 47kPa (0 ~ 6000m);
3) altitude environment simulation region regulation of relative humidity scope: 15 ~ 95%;
4) altitude environment simulation region temperature and engine air Flash Gas Compression Skid System simulation context :-45 DEG C to 70 DEG C;
5) pilot system meets the requirement that engine maximum pump discharge is the engine plateau environment Steady-state simulation test of 13L.
6) the maximum illumination intensity of ultraviolet ray generating apparatus is 10W/m
2.
Altitude environment simulation test cabin for internal combustion power equipment of the present invention can simulate the test condition such as infrabar, height epidemic disaster, and according to testing requirements, experimental enviroment condition is controlled, complete the record to experimental enviroment data and controling parameters and process, video monitoring and record process of the test.
Claims (7)
1. an altitude environment simulation test cabin for internal combustion power equipment, comprise cabin body, this cabin body is divided into normal temperature and pressure district and the altitude environment simulation region for placing Devices to test by partition, described normal temperature and pressure district is provided with the dynamometer machine for detecting Devices to test, be provided with the air supply system be communicated with altitude environment simulation region by supply air line, it is characterized in that, described air supply system comprises for carrying the pressure fan of air to supply air line and acting on temperature control equipment and the humidity control apparatus of air in supply air line, be provided with the first vacuum system and the second vacuum system that are connected with Devices to test exhausr port and altitude environment simulation region respectively by vacuum line, when Devices to test needs low-pressure starting, connect the second vacuum system and negative pressure is taken out to altitude environment simulation region, simultaneously, the vacuum pump in the first vacuum system is utilized to take out negative pressure to surge tank, make the target setting value that surge tank pressure reaches consistent with altitude environment simulation region negative pressure, and then start Devices to test, when needing to detect the plateau runnability of Devices to test, the air inlet swabbing action after utilizing Devices to test to start directly is bled in the altitude environment simulation region meeting negative pressure requirements, simultaneously, utilize air supply system to regulate altitude environment simulation region pressure in real time, meet setting value, the simulation of Devices to test discharge pressure is then realized by the real-time adjustment of the first vacuum system.
2. altitude environment simulation test cabin for internal combustion power equipment as claimed in claim 1, it is characterized in that, environmental parameter acquisition system is provided with in described altitude environment simulation region, Measurement and Control System is provided with in described normal temperature and pressure district, Measurement and Control System described in the signal output part of described environmental parameter acquisition system is accessed by circuit, the circuit part of described air supply system, the first vacuum system and the second vacuum system all accesses and is controlled by described Measurement and Control System.
3. altitude environment simulation test cabin for internal combustion power equipment as claimed in claim 2, it is characterized in that, be provided with the ultraviolet ray generating apparatus acting on altitude environment simulation region, the circuit part of this ultraviolet ray generating apparatus accesses and is controlled by described Measurement and Control System.
4. altitude environment simulation test cabin for internal combustion power equipment as claimed in claim 3, it is characterized in that, described environmental parameter acquisition system is multiple sensor.
5. altitude environment simulation test cabin for internal combustion power equipment as claimed in claim 4, it is characterized in that, be provided with video system, the circuit part of video system accesses and is controlled by described Measurement and Control System.
6. the altitude environment simulation test cabin for internal combustion power equipment as described in any one of Claims 1 to 5, is characterized in that, the first described vacuum system, from Devices to test exhaust port side, comprises heat interchanger, surge tank, by-pass valve control and vacuum pump successively.
7. the altitude environment simulation test cabin for internal combustion power equipment as described in any one of Claims 1 to 5, is characterized in that, the second described vacuum system, from the end of altitude environment simulation region, comprises heat interchanger, by-pass valve control and vacuum pump successively.
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| CN201110190551.5A CN102866017B (en) | 2011-07-08 | 2011-07-08 | Altitude environment simulation test cabin for internal combustion power equipment |
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| CN201110190551.5A CN102866017B (en) | 2011-07-08 | 2011-07-08 | Altitude environment simulation test cabin for internal combustion power equipment |
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| CN102866017B true CN102866017B (en) | 2015-08-19 |
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| CN103630364B (en) * | 2013-12-10 | 2016-06-29 | 中国重汽集团济南动力有限公司 | A kind of method of simulated high altitude environmental test diesel engine |
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