CN105387990A - Direct-current wind tunnel device and working method thereof - Google Patents
Direct-current wind tunnel device and working method thereof Download PDFInfo
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- CN105387990A CN105387990A CN201510803597.8A CN201510803597A CN105387990A CN 105387990 A CN105387990 A CN 105387990A CN 201510803597 A CN201510803597 A CN 201510803597A CN 105387990 A CN105387990 A CN 105387990A
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- liquefied air
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- water
- wind tunnel
- shower nozzle
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
Abstract
The invention discloses a direct-current wind tunnel device and a working method thereof. The direct-current wind tunnel device comprises a liquid air storage tank, a cryopump, a liquid air pipeline, a liquid air atomization nozzle, a water atomization nozzle, a water pipeline, a liquid pump, a water storage tank, a mixing stable segment, a test segment, a test model and a jet engine. According to the invention, a jet engine technology is adopted, a high-temperature high-speed air flow is directly generated, the air flow is mixed with liquid air, and the liquid air absorbs heat to be gasified; in addition, according to different jet temperatures of the engine and the amount change of mixed liquid air, air flows from -140 to +500 DEG C and from 0 to 500 m/s can be obtained, so that the working requirements are met.
Description
Technical field
The present invention relates to a kind of direct current wind tunnel device, what be specifically related to is a kind of direct current wind tunnel device and method of work thereof.
Background technology
Current direct-action wind tunnel generally adopts existing method to be use high speed fan, large fan, when starting wind-tunnel work, power consumption is huge, from tens kilowatts to several ten thousand kilowatts not etc., and is difficult to reach supersonic speed, require higher to electric power supply, a unstable bulk loads is large to electrical network pressure; Also have one to be adopt blast to produce air-flow, but burst period is shorter, the time, required equipment requirement was also higher probably between 0.1 to 2 second; The third utilizes gas cylinder first to store a large amount of gas, produces short time pulse high velocity air, but cannot meet existing requirement.
Summary of the invention
The technical problem to be solved in the present invention is to provide the test air-flow needed for a kind of direct generation wind-tunnel, reduces the consumption to electric energy, simplification system, reduces energy consumption, improving SNR, the direct current wind tunnel device of raising the efficiency and method of work thereof.
For solving the problems of the technologies described above, the present invention adopts following technical scheme: a kind of direct current wind tunnel device, comprise liquefied air storage tank, and store up tank connected cryopump with liquefied air, and the liquefied air pipeline to be connected with cryopump, and the liquefied air atomizer to be connected with liquefied air pipeline, and be arranged on the water atomization shower nozzle of liquefied air atomizer side, and the water lines to be connected with water atomization shower nozzle, and the liquor pump to be connected with water lines, and the water storage tank to be connected with liquor pump, and be fixed on the mixed stability section of liquefied air atomizer and water atomization shower nozzle one end, and the test section to be connected with liquefied air atomizer and the water atomization shower nozzle other end, and the test model be arranged in test section, and be arranged on the jet engine of mixed stability section side.
Further, described jet engine is turbine engine, fanjet, arteries and veins fuel-injection engine, Duct-Burning Turbofan, rocket engine.
Further, described liquefied air atomizer and water atomization shower nozzle are oppositely arranged.
Further, described mixed stability section and test section are interconnected.
Another technical matters that the present invention will solve is to provide a kind of easy to operate, and the method for work of the direct current wind tunnel device that efficiency is high, its step is as follows
1), the first liquefied air of-200 DEG C in liquefied air storage tank 1, by Pipeline transport in cryopump; 2), cryopump supercharging later by liquefied air Pipeline transport to liquefied air atomizer, certain force value can be possessed to adjust the pressure of liquefied air atomizer; 3), liquefied air atomizer is injected to mixed stability section with small drop, can produce wake flame air-flow powerful from low speed to high speed during jet engine work for wind-tunnel provides source of the gas, speed is 0 meter even higher to 500 meters, temperature is even higher to 2500 DEG C from 300 DEG C, if rocket engine, temperature can be 3500 DEG C, and speed is up to 1000 meters per second; 4), mixed by the aerosol of liquefied air atomizer ejection and jet engine high temperature bluster, liquefied air absorbs the heat of air-flow and gasifies rapidly, and form mixed airflow, the temperature of mixed airflow will significantly decline; 5) and water storage tank enters in liquor pump by pipeline, then enter into water atomization shower nozzle by liquor pump supercharging through water lines, to test the atomization of required different flow, ejection, be mixed in air-flow; 6), the water smoke of water atomization shower nozzle ejection also mixes with jet engine high temperature gas flow, liquefied air, form mixed airflow, water smoke is different according to result temperature after mixing, finally may form the different conditions such as solid-state, liquid, steam state, gaseous state in the gas flow, just fully can simulate the various environmental test requirements such as snow, rain, mist; 7), simultaneously because liquefied air vaporization, gasification are expanded, gas flowing is more fierce, the reduction of gas velocity can not be caused, after mixed stability section is mixed expanded fully, form a stable mixed airflow, meet the blowing demand of test section to test model, all can occur different temperatures when air-flow mixes, raise a km air themperature and decline 6 DEG C, the density of gas also can decline thereupon.
The beneficial effect of direct current wind tunnel device of the present invention:
1, existing construction of wind tunnel is significantly simplified, original cooling, temperature elevation system do not need;
2, adopt the energy of fuel combustion release as power, convenient, flexible, and the heat of fuel combustion all utilizes, efficiency is high;
3, work in different conditions by adjustment jet engine, as under idling, low speed, at full speed isotype, wind tunnel speed can from low speed to high speed, supersonic speed change, depend on jet-engine performance, continuously adjustabe;
4, by spraying into water smoke, the different humidity content such as different rain, snow, mist can be simulated and descend test condition to carry out wind tunnel test;
5, adjust the straying quatity of liquefied air, the finishing temperature of working air current can be adjusted, simulate from-100 DEG C until the various temperature air-flows of jet engine wake flame temperature are tested.
Accompanying drawing explanation
Fig. 1 is the structural representation of a kind of direct current wind tunnel device of the present invention;
Fig. 2 is the schematic diagram of jet engine in a kind of direct current wind tunnel device of the present invention.
Embodiment
In the present embodiment, shown in Fig. 2, a kind of direct current wind tunnel device, comprise liquefied air storage tank 1, and the cryopump 2 to be connected with liquefied air storage tank 1, and the liquefied air pipeline 8 to be connected with cryopump 2, and the liquefied air atomizer 5 to be connected with liquefied air pipeline 8, and be arranged on the water atomization shower nozzle 10 of liquefied air atomizer 5 side, and the water lines 9 to be connected with water atomization shower nozzle 10, and the liquor pump 11 to be connected with water lines 9, and the water storage tank 12 to be connected with liquor pump 11, and be fixed on the mixed stability section 4 of liquefied air atomizer 5 and water atomization shower nozzle 10 one end, and the test section 6 to be connected with liquefied air atomizer 5 and water atomization shower nozzle 10 other end, and the test model 7 be arranged in test section 6, and be arranged on the jet engine 3 of mixed stability section 4 side.
Described jet engine 3 is turbine engine, fanjet, arteries and veins fuel-injection engine, Duct-Burning Turbofan, rocket engine.
Described liquefied air atomizer 5 and water atomization shower nozzle 10 are oppositely arranged; Described mixed stability section 4 and test section 6 are interconnected.
In use, comprise the following steps:
1), the first liquefied air of-200 DEG C in liquefied air storage tank 1, by Pipeline transport in cryopump 2;
2), be transported to liquefied air atomizer 5 by liquefied air pipeline 8 after cryopump 2 supercharging, certain force value can be possessed to adjust the pressure of liquefied air atomizer 5;
3), liquefied air atomizer 5 is injected to mixed stability section 4 with small drop, can produce wake flame air-flow powerful from low speed to high speed when jet engine 3 works for wind-tunnel provides source of the gas, speed is 0 meter even higher to 500 meters, temperature is even higher to 2500 DEG C from 300 DEG C, if rocket engine, temperature can be 3500 DEG C, and speed is up to 1000 meters per second;
4), mixed by the aerosol that sprays of liquefied air atomizer 5 and jet engine 3 high temperature bluster, liquefied air absorbs the heat of air-flow and gasifies rapidly, and form mixed airflow, the temperature of mixed airflow will significantly decline;
5) and water storage tank 12 enters in liquor pump 11 by pipeline, then enter into water atomization shower nozzle 10 by liquor pump 11 supercharging through water lines 9, to test the atomization of required different flow, ejection, be mixed in air-flow;
6) water smoke that, water atomization shower nozzle 10 sprays also mixes with jet engine 3 high temperature gas flow, liquefied air, form mixed airflow, water smoke is different according to result temperature after mixing, finally may form the different conditions such as solid-state, liquid, steam state, gaseous state in the gas flow, just fully can simulate the various environmental test requirements such as snow, rain, mist;
7), simultaneously because liquefied air vaporization, gasification are expanded, the total amount of gas is increased, gas flowing is more fierce, the reduction of gas velocity can not be caused, after mixed stability section 4 is mixed expanded fully, form a stable mixed airflow, meet the blowing demand of test section 6 pairs of test models 7, all can occur different temperatures when air-flow mixes.
The present invention adopts above-mentioned direct current wind tunnel device, and it simplifies very much, and original cooling, temperature elevation system do not need; And the heat of fuel combustion all utilizes, efficiency is high; In addition, performance of wind tunnel from low speed to high speed, supersonic speed, depend on jet-engine performance, continuously adjustabe; And wind-tunnel under different sleet, moisture content can be simulated.
Above-described embodiment, just an example of the present invention, be not for limiting enforcement of the present invention and interest field, all technical schemes identical or equivalent with content described in the claims in the present invention, all should be included in scope.
Claims (5)
1. a direct current wind tunnel device, comprise liquefied air storage tank, and store up tank connected cryopump with liquefied air, and the liquefied air pipeline to be connected with cryopump, and the liquefied air atomizer to be connected with liquefied air pipeline, and be arranged on the water atomization shower nozzle of liquefied air atomizer side, and the water lines to be connected with water atomization shower nozzle, and the liquor pump to be connected with water lines, and the water storage tank to be connected with liquor pump, and be fixed on the mixed stability section of liquefied air atomizer and water atomization shower nozzle one end, and the test section to be connected with liquefied air atomizer and the water atomization shower nozzle other end, and the test model be arranged in test section, and be arranged on the jet engine of mixed stability section side.
2. a kind of direct current wind tunnel device as claimed in claim 1, is characterized in that: described jet engine is turbine engine, fanjet, arteries and veins fuel-injection engine, Duct-Burning Turbofan, rocket engine.
3. a kind of direct current wind tunnel device as claimed in claim 1, is characterized in that: described liquefied air atomizer and water atomization shower nozzle are oppositely arranged.
4. a kind of direct current wind tunnel device as claimed in claim 1, is characterized in that: described mixed stability section and test section are interconnected.
5. a method of work for direct current wind tunnel device as claimed in claim 1, is characterized in that, comprise the following steps:
1), the first liquefied air of-200 DEG C in liquefied air storage tank, by Pipeline transport in cryopump;
2), cryopump supercharging later by liquefied air Pipeline transport to liquefied air atomizer, certain force value can be possessed to adjust the pressure of liquefied air atomizer;
3), liquefied air atomizer is injected to mixed stability section with small drop, and can produce wake flame air-flow powerful from low speed to high speed during jet engine work for wind-tunnel and provide source of the gas, speed is 0 meter to 500 meters, and temperature is from 300 DEG C to 2500 DEG C;
4), mixed by the aerosol of liquefied air atomizer ejection and jet engine high temperature bluster, liquefied air absorbs the heat of air-flow and gasifies rapidly, and form mixed airflow, the temperature of mixed airflow will significantly decline;
5) and water storage tank enters in liquor pump by pipeline, then enter into water atomization shower nozzle by liquor pump supercharging through water lines, to test the atomization of required different flow, ejection, be mixed in air-flow;
6), the water smoke of water atomization shower nozzle ejection also mixes with jet engine high temperature gas flow, liquefied air, form mixed airflow, water smoke is different according to result temperature after mixing, finally form solid-state, liquid, steam state, gaseous state different conditions in the gas flow, just fully can simulate various environmental test requirement;
7), simultaneously because liquefied air vaporization, gasification are expanded, the total amount of gas is increased, after mixed stability section is mixed expanded fully, forms a stable mixed airflow, meet the blowing demand of test section to test model.
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| CN201510803597.8A CN105387990A (en) | 2015-11-20 | 2015-11-20 | Direct-current wind tunnel device and working method thereof |
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| CN201510803597.8A CN105387990A (en) | 2015-11-20 | 2015-11-20 | Direct-current wind tunnel device and working method thereof |
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| CN105387990A true CN105387990A (en) | 2016-03-09 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108645589A (en) * | 2018-07-13 | 2018-10-12 | 无锡友鹏机场除雪装备有限公司 | Wind tunnel experiment vehicle |
| CN115326345A (en) * | 2022-10-17 | 2022-11-11 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel test device and test method for trailing flame radiation characteristic of draft tube |
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| US2914941A (en) * | 1954-04-27 | 1959-12-01 | Snecma | High-speed wind tunnels |
| CN2723978Y (en) * | 2004-05-18 | 2005-09-07 | 中国科学院力学研究所 | Igniter for explosive driving shock wave tunnel |
| CN102914416A (en) * | 2012-09-20 | 2013-02-06 | 同济大学 | Direct-cooling freezing wind tunnel realization method and direct-cooling freezing wind tunnel realization system |
| CN203702370U (en) * | 2014-02-12 | 2014-07-09 | 苟仲武 | Liquid air hybrid power rocket engine equipment |
| CN104454015A (en) * | 2014-10-27 | 2015-03-25 | 中国科学院工程热物理研究所 | Isothermal expansion power system by hydraulic pressure |
| CN205138753U (en) * | 2015-11-20 | 2016-04-06 | 苟仲武 | Direct current wind -tunnel device |
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2015
- 2015-11-20 CN CN201510803597.8A patent/CN105387990A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2914941A (en) * | 1954-04-27 | 1959-12-01 | Snecma | High-speed wind tunnels |
| CN2723978Y (en) * | 2004-05-18 | 2005-09-07 | 中国科学院力学研究所 | Igniter for explosive driving shock wave tunnel |
| CN102914416A (en) * | 2012-09-20 | 2013-02-06 | 同济大学 | Direct-cooling freezing wind tunnel realization method and direct-cooling freezing wind tunnel realization system |
| CN203702370U (en) * | 2014-02-12 | 2014-07-09 | 苟仲武 | Liquid air hybrid power rocket engine equipment |
| CN104454015A (en) * | 2014-10-27 | 2015-03-25 | 中国科学院工程热物理研究所 | Isothermal expansion power system by hydraulic pressure |
| CN205138753U (en) * | 2015-11-20 | 2016-04-06 | 苟仲武 | Direct current wind -tunnel device |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108645589A (en) * | 2018-07-13 | 2018-10-12 | 无锡友鹏机场除雪装备有限公司 | Wind tunnel experiment vehicle |
| CN115326345A (en) * | 2022-10-17 | 2022-11-11 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel test device and test method for trailing flame radiation characteristic of draft tube |
| CN115326345B (en) * | 2022-10-17 | 2022-12-20 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel test device and test method for trailing flame radiation characteristic of draft tube |
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