CN1083587A - The mat heat separator reduces the cryonetic wind tunnel of stagnation temperature - Google Patents
The mat heat separator reduces the cryonetic wind tunnel of stagnation temperature Download PDFInfo
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- CN1083587A CN1083587A CN 93117590 CN93117590A CN1083587A CN 1083587 A CN1083587 A CN 1083587A CN 93117590 CN93117590 CN 93117590 CN 93117590 A CN93117590 A CN 93117590A CN 1083587 A CN1083587 A CN 1083587A
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Abstract
The cryonetic wind tunnel that mat heat separator of the present invention reduces stagnation temperature belongs to the aviation ground-testing plant.It is made up of heat separator, wind-tunnel pressure-stabilizing section, test chamber, diffuser and heat exchanger, core content of the present invention is to adopt gases at high pressure as the refrigeration energy, at wind-tunnel pressure-stabilizing section upstream dress heat separator, the air communication of injecting is crossed throttling valve, air-flow is eliminated disturbance steadily in pressure-stabilizing section after, acceleration enters test section, is for experiment, and air-flow slows down after heat exchanger is discharged atmosphere through diffuser.The present invention has overcome shortcomings such as involving great expense of prior art, has that operating cost is low, energy resource consumption is little and advantage such as free from environmental pollution.
Description
The cryonetic wind tunnel that mat heat separator of the present invention reduces stagnation temperature belongs to the aviation ground-testing plant.
The present age, high performance airplane generally all adopted various advanced aerofoil profiles, the aerodynamic characteristic of these aerofoil profiles is all very responsive to Reynolds number, sixties U.S.'s development large transport airplane C141, because the wind tunnel test Reynolds number is more much lower than practical flight Reynolds number, the nose-down pitching moment coefficient that wind-tunnel provides is low by 11% than the practical flight value, causes machine to ruin accident in taking a flight test narrowly.Improve the wind tunnel test Reynolds number and become the task of top priority.
Improving the wind tunnel test Reynolds number can enlarge tunnel size, raising air-flow stagnation pressure or reduction test gas flow temperature and reach by using heavy test gas instead.Adopt heavy test gas, because specific heat ratio is different with air, pressure rising value difference influences shock-wave spot behind the shock wave, and experimental data is difficult to handle.Enlarging tunnel size sharply rises cost and running expense, generally say, the wind-tunnel cost is directly proportional with wind-tunnel linear dimension 2.5 powers, driving power is with square increase of wind-tunnel linear dimension, at present, the transonic wind tunnel cost of maximum in the world normal temperature operation is up to multi-billion dollar, and driving power is up to 300,000 watts.Mat further enlarges tunnel size and improves the test Reynolds number, and the required cost and the energy all are difficult to bear.Improve the air-flow stagnation pressure, correspondingly will strengthen construction of wind tunnel, dynamic pressure also increases thereupon, and the model load increases, and model pole is wanted overstriking, and pole is disturbed and aeroelasticity is disturbed and is difficult to elimination.Reduce the test gas flow temperature and have many tangible advantages: when tunnel size and stagnation pressure one timing, if the air-flow stagnation temperature drops to chilling temperature 100K by the 322K that normal temperature moves, the test Reynolds number can increase by 500.Driving power can descend 45%.Therefore cryonetic wind tunnel becomes a kind of preferred plan of high reynolds number transonic wind tunnel.
Since beginning to develop cryonetic wind tunnel from early seventies, at present the U.S., Russia and German, English, method, day and China priority build up nearly 20 cryonetic wind tunnels.The heat that heat that the driving merit transforms and wind-tunnel shell wall import into is kept testing the low temperature of air-flow by the heat of evaporation of the liquid nitrogen that sprays into wind-tunnel.Mid-1980s, existing two large-scale low-temperature wind-tunnel inputs are formally used.One is the KKK low temperature low-speed wind tunnel of German aeronautical research institute, Mach Number Never To Be Exceeded 0.35; Another is country's equipment (NTF) transonic speed at U.S. NASA langley center.This is a present unique in the world wind-tunnel that satisfies the requirement of advanced design aircraft testing Reynolds number, and this test chamber cross section is 2.5m * 2.5m, range of Mach numbers 0.2-1.2, working pressure 0.1-0.9MPa.High reynolds number 120 * 10
6(M=1.0), fan motor power 90,000KW.Also have a scale and performance under construction near the Europe transonic wind tunnel (ETW) of NTF by method, moral, English and Dutch cooperative construction.
The low temperature high Reynola number wind tunnel is compared with the other types high Reynola number wind tunnel, has outstanding advantage, and has built up the large productive wind-tunnel.Remain improved weak point but still exist, wherein topmost for consuming the liquid nitrogen of a large amount of high prices, cause the operating cost height.Turn round under high reynolds number condition as U.S. NTF wind-tunnel, per minute needs with liquid nitrogen about 250 tons, and by 700 dollars per ton, per minute needs 1.8 ten thousand dollars.High running expense is the developing stage that present most cryonetic wind tunnel still rests on small size or utmost point low speed, and the basic reason of failing to apply.The exhaust of a large amount of in addition low temperature, anoxic is in line goes into atmosphere, not only to local climate but also totally unfavorable to ecologic environment, this exhaust must be mixed a large amount of air earlier, could discharge after improving temperature and oxygen content.
In order to overcome above-mentioned deficiency, the invention provides the cryonetic wind tunnel that the mat heat separator reduces stagnation temperature.Directly adopt high-pressure air source, at first utilize the exhaust cold that high pressure gas is lowered the temperature by heat exchanger, further cool the temperature to the low temperature that chilling temperature keeps the test chamber air-flow by heat separator again, utilize the refrigeration of liquid nitrogen vaporization heat to replace prior art.
It is low to the purpose of this invention is to provide a kind of operating cost, and energy resource consumption is little, cryonetic wind tunnel free from environmental pollution.
Fig. 1 is a through type cryonetic wind tunnel structural representation of the present invention.
Fig. 2 is a reverse-flow type cryonetic wind tunnel structural representation of the present invention.
Fig. 3 is the heat separator structural representation.
Among Fig. 1, Fig. 2, (1) is heat separator, and (2) are throttling valve, and (3) are the wind-tunnel pressure-stabilizing section, and (4) are test chamber, and (5) are diffuser, and (6) are heat exchanger.Among Fig. 3, (7) are rotary nozzle, and (8) are shock tube.Fig. 1 in 2,3, (A) is air intake opening, (B) is exhausr port.Whole wind-tunnel is characterised in that, directly adopt gases at high pressure as the refrigeration source of the gas, it comprises, heat separator (1) and be attached thereto the pressure-stabilizing section (3) that connects, rear portion at pressure-stabilizing section (3) connects test section (4), the diffuser (5) that is connected with test section (4), heat exchanger (6) is connected with the afterbody of diffuser (5), wherein can also be connected in series throttling valve (2) in the exit of heat separator (1).The pressure limit of the gases at high pressure of whole wind-tunnel is 2-10MPa.
Below in conjunction with accompanying drawing the present invention is introduced in detail.Fig. 1 is a through-type cryonetic wind tunnel structural representation of the present invention, core content of the present invention is to adopt gases at high pressure as the refrigeration energy, at wind-tunnel pressure-stabilizing section (3) upstream dress heat separator (1), the air-flow of injecting enters from air intake opening (A), by throttling valve (2), air-flow is eliminated disturbance steadily in pressure-stabilizing section (3) after, acceleration enters test section (4), use for model test, the air-flow of test section (4) outlet after diffuser (5) deceleration supercharging, and through heat exchanger (6) after by exhausr port (B) discharge atmosphere.Present technique utilizes heat separator (1) to reduce and keep the gas flow temperature of test chamber (4), to utilize in the replacement prior art, the refrigeration of liquid nitrogen vaporization heat absorption, reduce cryonetic wind tunnel simultaneously and discharge the huge waste of a large amount of cryogenic gas contaminated environment and the energy, the present invention also proposes to dispose between the air intake opening of wind-tunnel and exhausr port and gives cold air inlet heat exchanger (6), the temperature of utilizing the entrained cold of exhaust will enter the preceding gases at high pressure of thermal release (1) reduces, delivery temperature by heat exchanger (6) is enhanced near atmospheric temperature contaminated environment no longer, and the pressure limit of the gases at high pressure of input wind-tunnel is 2 to 10MPa.The present invention not only can be used for through type wind-tunnel shown in Figure 1, also can be used for return circuit wind tunnel shown in Figure 2.
Structural representation such as Fig. 3 of heat separator (1), when entering rotary nozzle (7) and inject successively by tubular shaft, gases at high pressure closely are arranged in garden each shock tube (8) on week outside the rotary nozzle (7), (being generally 24 to 48) injects gas in the shock tube (8), compress former low-pressure gas in shock tube, and form the shock wave of propagating forward therein.Shock wave skims over part, and gas is compressed, and quickens and heating.After rotary nozzle (7) was removed, shock tube (8) was connected with the low pressure exhaust mouth.The gas of injecting shock tube (8) oppositely flows out through rarefaction wave, and is discharged by exhausr port (8).Owing to inject gas to former gas work done in shock tube (8), temperature therefore descends.Former in shock tube (8) heated gas dispel the heat by tube wall.Each shock tube (8) begins to terminate as a working cycle to exhaust when injecting gas, eluting gas is intermittent, because many shock tubes (8) are also overlapping exhaust of most of the time successively, heat separator (1) exit (B) flow parameter can be kept permanent number.
When gases at high pressure pass through heat separator (1) step-down, stagnation temperature also reduces, the freezing efficiency of thermal release (1) has at present reached 80%, during using, engineering keeps 70% easily, when freezing efficiency is not 80% and 70%, air or nitrogen as working medium of wind tunnel are reduced to 100K from 300K, require porch pressure to exceed 500 times and 4.2 ten thousand times than outlet pressure respectively, and requiring so, high pressure all is impracticable technically and economically.
The present invention proposes to dispose a heat exchanger (6), reduce with the temperature of utilizing the entrained cold of exhaust will enter the preceding gases at high pressure of heat separator (1), heat exchanger (6) efficient can be according to cost, size and have related parameter selected, if heat separator (1) efficient is 70%, then as long as heat exchanger (5) efficient utilizes the high-pressure air source (P ≈ 10MPa) of common wind-tunnel wind tunnel test air-flow stagnation temperature can be reduced to 100K greater than 55%.
At low temperature particularly near under the critical conditions, throttling cooling efficient is higher, because the throttling cooling system is very simple, less imperfect loss, can be at heat separator (1) back serial connection throttling valve with the progression that reduces heat separator (1) (if heat exchanger (6) efficient reaches more than 80%, might only lower the temperature with throttling valve), also can divide liquid gas, the suitable reflux cycle formula wind-tunnel that is applied in throttling level generating unit.
The present invention adopts gases at high pressure to replace the energy of liquefied ammonia of the prior art as refrigeration, has avoided the liquid nitrogen process units of equipment cost and operating cost costliness, and the operating cost of cryonetic wind tunnel and expenditure of construction are obviously reduced.For the unit of those existing high-pressure air source, only need to add heat separator (1) and heat exchanger (6).Effect of the present invention is more outstanding, the operation maintenance technology of high-pressure air source, aerodynamic experiment department on top of already, liquid nitrogen production is stored transportation and is then needed operator training, the liquid nitrogen spray atomizing is a gordian technique, the atomizing imperfection causes gasification not exclusively, and wind-tunnel is with cisco unity malfunction, and the present invention does not have this respect requirement.
Need stop owing to change test model and change test condition, more owing to reduce general power, general large tunnel adopts energy storage temporarily towards formula work more.Store liquid nitrogen, it is more complex to store the pressure gas technical requirement, and cost is also higher.Outstanding more is to adopt the heat separator scheme to be convenient to recycle the exhaust cold, can save a large amount of energy consumptions, and free from environmental pollution, and the liquid nitrogen scheme then is difficult to accomplish.
The gordian technique that effectively realizes the present invention program is development high efficiency heat separator (1) and heat exchanger (6), as high-pressure air source gas is room temperature (300K), wind tunnel test air-flow stagnation temperature is 100K, if the efficient of heat separator (1) and heat exchanger (6) is 70%, then heat separator (1) inlet is 14.7 with the top hole pressure ratio, if both efficient are 65%, then enter the mouth and the top hole pressure ratio is upgraded to 33.5, consider that heat branch parallel operation (6) and pipeline flow losses and wind-tunnel discharging directly into atmosphere need, high-pressure air source pressure is respectively 2MPa and 5MPa, can meet the demands.According to calculating, if high-pressure air source pressure is 10MPa, then the av eff of heat separator (1) and heat exchanger (6) is higher than 62.5% and just can satisfies the demand.
Claims (7)
1, a kind of mat heat separator reduces the cryonetic wind tunnel of stagnation temperature, it is characterized in that, directly adopt gases at high pressure as the refrigeration source of the gas, it comprises, heat separator (1) and be attached thereto the pressure-stabilizing section (3) that connects, rear portion at pressure-stabilizing section (3) connects test section (4), the diffuser (5) that is connected with test section (4), and heat exchanger (6) is connected with the afterbody of diffuser (5).
2, by the described cryonetic wind tunnel of claim 1, it is characterized in that heat separator (1) is contained between air intake opening (A) and the wind-tunnel pressure-stabilizing section (3).
3, by the described cryonetic wind tunnel of claim 1, it is characterized in that heat exchanger (6) is contained between diffuser (5) and the exhausr port (B).
4, by the described cryonetic wind tunnel of claim 1, it is characterized in that the pressure limit of gases at high pressure is at 20-100 atmospheric pressure.
5, by the described cryonetic wind tunnel of claim 1, it is characterized in that wind-tunnel is a direct-action wind tunnel.
6, by the described cryonetic wind tunnel of claim 1, it is characterized in that wind-tunnel is a return circuit wind tunnel.
7, by the described cryonetic wind tunnel of claim 1, it is characterized in that the exit of heat separator (1) can also be connected in series throttling valve (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN93117590A CN1039553C (en) | 1993-09-20 | 1993-09-20 | Low temp. wind tunnel reducing total temp. by heat separator |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN93117590A CN1039553C (en) | 1993-09-20 | 1993-09-20 | Low temp. wind tunnel reducing total temp. by heat separator |
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| Publication Number | Publication Date |
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| CN1083587A true CN1083587A (en) | 1994-03-09 |
| CN1039553C CN1039553C (en) | 1998-08-19 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN93117590A Expired - Fee Related CN1039553C (en) | 1993-09-20 | 1993-09-20 | Low temp. wind tunnel reducing total temp. by heat separator |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100348964C (en) * | 2005-01-07 | 2007-11-14 | 北京航空航天大学 | Sand/dust blowing environmental test equipment system |
| CN102192828A (en) * | 2010-03-02 | 2011-09-21 | 中国科学院理化技术研究所 | Low-temperature wind tunnel |
| CN103787407A (en) * | 2013-12-25 | 2014-05-14 | 河北科技大学 | Method for preparing nano TiCN/Al2O3 composite powder through reactive ball milling |
| CN105628331A (en) * | 2015-12-28 | 2016-06-01 | 中国航天空气动力技术研究院 | Energy-saving environment-friendly layout of large-scale routine hypersonic wind tunnel |
| CN106959201A (en) * | 2017-05-18 | 2017-07-18 | 西北工业大学 | Continuous high-speed wind-tunnel liquid nitrogen cooling supplies air distribution system |
| CN107219056A (en) * | 2017-05-18 | 2017-09-29 | 西北工业大学 | Continuous high-speed wind-tunnel cooling system liquid nitrogen sprays into experimental section |
| CN107655654A (en) * | 2017-08-30 | 2018-02-02 | 浙江大学 | A kind of disperse type low-temperature wind-tunnel gas extraction system |
| CN113375892A (en) * | 2021-08-12 | 2021-09-10 | 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 system and test method based on reverse Brayton cycle of turboexpander |
| CN113483985A (en) * | 2021-08-12 | 2021-10-08 | 中国空气动力研究与发展中心高速空气动力研究所 | Temporary-impulse wind tunnel system adopting reverse Brayton cycle to control temperature and test method |
| CN117589415A (en) * | 2023-11-22 | 2024-02-23 | 中国科学院力学研究所 | Wind tunnel total temperature control system and method |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0092557A1 (en) * | 1981-10-20 | 1983-11-02 | S.M. RESEARCH & DEVELOPMENT LIMITED | Skydiving simulator |
| US4953397A (en) * | 1989-07-25 | 1990-09-04 | The Boeing Company | Continuous flow hypersonic centrifugal wind tunnel |
| US5127264A (en) * | 1991-05-20 | 1992-07-07 | Thermal Surveys, Inc. | Methods of infrared visualization of air flow |
-
1993
- 1993-09-20 CN CN93117590A patent/CN1039553C/en not_active Expired - Fee Related
Cited By (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100348964C (en) * | 2005-01-07 | 2007-11-14 | 北京航空航天大学 | Sand/dust blowing environmental test equipment system |
| CN102192828A (en) * | 2010-03-02 | 2011-09-21 | 中国科学院理化技术研究所 | Low-temperature wind tunnel |
| CN102192828B (en) * | 2010-03-02 | 2013-07-24 | 中国科学院理化技术研究所 | Low-temperature wind tunnel |
| CN103787407A (en) * | 2013-12-25 | 2014-05-14 | 河北科技大学 | Method for preparing nano TiCN/Al2O3 composite powder through reactive ball milling |
| CN103787407B (en) * | 2013-12-25 | 2016-04-20 | 河北科技大学 | Reaction ball milling legal system is for nano TiC N/Al 2o 3the method of composite powder |
| CN105628331B (en) * | 2015-12-28 | 2017-12-22 | 中国航天空气动力技术研究院 | The energy-conserving and environment-protective system of large-scale conventional hypersonic wind tunnel |
| CN105628331A (en) * | 2015-12-28 | 2016-06-01 | 中国航天空气动力技术研究院 | Energy-saving environment-friendly layout of large-scale routine hypersonic wind tunnel |
| CN106959201A (en) * | 2017-05-18 | 2017-07-18 | 西北工业大学 | Continuous high-speed wind-tunnel liquid nitrogen cooling supplies air distribution system |
| CN107219056A (en) * | 2017-05-18 | 2017-09-29 | 西北工业大学 | Continuous high-speed wind-tunnel cooling system liquid nitrogen sprays into experimental section |
| CN106959201B (en) * | 2017-05-18 | 2023-02-28 | 西北工业大学 | Continuous high-speed wind tunnel liquid nitrogen cooling gas supply and distribution system |
| CN107219056B (en) * | 2017-05-18 | 2023-05-26 | 西北工业大学 | Liquid nitrogen spraying experiment section of continuous high-speed wind tunnel cooling system |
| CN107655654A (en) * | 2017-08-30 | 2018-02-02 | 浙江大学 | A kind of disperse type low-temperature wind-tunnel gas extraction system |
| CN113375892A (en) * | 2021-08-12 | 2021-09-10 | 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 system and test method based on reverse Brayton cycle of turboexpander |
| CN113483985A (en) * | 2021-08-12 | 2021-10-08 | 中国空气动力研究与发展中心高速空气动力研究所 | Temporary-impulse wind tunnel system adopting reverse Brayton cycle to control temperature and test method |
| CN113483985B (en) * | 2021-08-12 | 2023-04-25 | 中国空气动力研究与发展中心高速空气动力研究所 | Temporary flushing type wind tunnel system adopting reverse brayton cycle to control temperature and test method |
| CN117589415A (en) * | 2023-11-22 | 2024-02-23 | 中国科学院力学研究所 | Wind tunnel total temperature control system and method |
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| Publication number | Publication date |
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| CN1039553C (en) | 1998-08-19 |
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