CN203053672U - Wind tunnel for reflux type experiments - Google Patents
Wind tunnel for reflux type experiments Download PDFInfo
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- CN203053672U CN203053672U CN 201220681793 CN201220681793U CN203053672U CN 203053672 U CN203053672 U CN 203053672U CN 201220681793 CN201220681793 CN 201220681793 CN 201220681793 U CN201220681793 U CN 201220681793U CN 203053672 U CN203053672 U CN 203053672U
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Abstract
The utility model relates to a wind tunnel for reflux type experiments, which comprises a power section for providing a power source, a first diffuser section communicated with the power section, a pressure stabilizing section communicated with the first diffuser section, a contraction section communicated with the pressure stabilizing section, and a closed experimental section. The output end of the first diffuser section and the input end of the pressure stabilizing section are communicated with a first corner section of a first corner guide vane, a second diffuser section, and a second corner section of a second corner guide vane, wherein the first corner section of the first corner guide vane, the second diffuser section, and the second corner section of the second corner guide vane are sequentially arranged etween the output end of the first diffuser section and the input end of the pressure stabilizing section. The end port of the pressure stabilizing section is provided with a honeycomb. A damping gauze is arranged inside the pressure stabilizing section. The outer wall of the constriction section is in the shape of a quintic shrinkage curve. The output end of the contraction section and the closed experimental section are communicated with each other. According to the utility model, the contour of the contraction section of the wind tunnel for reflux type experiments is in the shape of a quintic shrinkage curve and the outer wall of the contraction section is designed as a smooth transition wall. In this way, when being accelerated, the air flow is better ensured to be uniform, stable and low in turbulence. Therefore, the experimental air flow obtained at the outlet of the contraction section, namely the experimental section, is ensured to be higher in quality more sufficiently.
Description
Technical field
The utility model relates to the technical field of aeromechanics performance test, especially a kind of reverse-flow type experiment wind-tunnel.
Background technology
The wind tunnel experiment of fluid mechanics aspect refers in wind-tunnel to settle aircraft or other object models, learning gas flow and with the interaction of model, with a kind of aerodynamic experiment method of the air dynamic behaviour of understanding practical flight device or other objects; Then be aspect ecological in a coffin that ventilating air arranged at insect chemistry, observe the live body insect to the experiment of the behavior reaction of odoring substance.The ultimate principle of wind tunnel experiment is relativity principle and similarity principle.According to relativity principle, the aircraft suffered aerodynamic force of flying in still air blows with same speed in the other direction with aircraft transfixion, air, and both effects are the same.
Because at present traditional wind tunnel experiment, there is certain defective in the contraction section method for designing that adopts, cause existing experiment to exist a following gordian technique difficult problem with wind-tunnel: 1. experimental section steady air current performance is poor; 2. experimental section gas velocity, the even poor performance of direction; 3. the experimental section stream turbulence is big; 4. the wind-tunnel integral energy is than low.Because the existence of above problem, often cause that wind tunnel experiment section flow field quality is low, energy loss is big, seriously restricting the accuracy of wind tunnel experiment.
The utility model content
The technical problems to be solved in the utility model is: in order to overcome the problem that exists in above-mentioned, provide a kind of reverse-flow type experiment wind-tunnel, it has solved air-flow instability, inhomogeneous, the phenomenon of hanging down turbulent flow, has guaranteed high-quality experiment air-flow.
The technical scheme that its technical matters that solves the utility model adopts is: a kind of reverse-flow type experiment wind-tunnel, comprise be used to the power section that power source is provided, first diffuser that is connected with power section, the pressure-stabilizing section that is connected with first diffuser and the contraction section that is connected with pressure-stabilizing section and the experimental section of remaining silent, be communicated with first round corner section and second diffuser that the first turning guide vane is housed and second round corner section that the second turning guide vane is housed between the output terminal of described first diffuser and the input end of pressure-stabilizing section successively, the port of described pressure-stabilizing section is provided with honeycomb, damping screen is installed in the pressure-stabilizing section, the outer wall of described contraction section is five power shrinkage curve shapes, the Vickers curve that five power shrinkage curves are more traditional, the cube curve, bicubic side's curve etc. has better smooth transition ability, guarantee the homogeneity of air-flow when accelerating better, stable and low turbulent flow, and then guarantee the contraction section exit more maturely, be that experimental section has high-quality experiment air-flow, the output terminal of described contraction section is connected with the experimental section of remaining silent.
Offer be used to the view window of checking situation in the experimental section of remaining silent on the described experimental section of remaining silent.
In order to regulate the diffuser internal pressure at any time, offer a plurality of regulator holes on described first diffuser.
The beneficial effects of the utility model are: described a kind of reverse-flow type experiment wind-tunnel, adopt five power curves to generate the curvilinear contraction section of smooth transition wall shape, can guarantee homogeneity, stability and the low turbulent flow of air-flow when accelerating better, and then guarantee the contraction section exit more maturely, namely experimental section has high-quality experiment air-flow.
Description of drawings
Below in conjunction with drawings and Examples the utility model is further specified.
Fig. 1 is structural representation of the present utility model;
1. power section among the figure, 2. first diffuser, 21. regulator holes, 3. pressure-stabilizing section, 4. contraction section, the experimental section of 5. remaining silent, 51. view windows, the 6. first turning guide vane, 7. second diffuser, the 8. second turning guide vane, 9. honeycomb, 10. damping screen.
Embodiment
By reference to the accompanying drawings the utility model is described in further detail now.These accompanying drawings are the synoptic diagram of simplification, basic structure of the present utility model only is described in a schematic way, so it only show the formation relevant with the utility model.
A kind of reverse-flow type experiment wind-tunnel as shown in Figure 1, comprise be used to the power section 1 that power source is provided, first diffuser 2 that is connected with power section 1, pressure-stabilizing section 3 and the contraction section 4 that is connected with first diffuser 2 and the experimental section 5 of remaining silent, output terminal at diffuser 2 is communicated with first round corner section that the first turning guide vane 6 is housed, offer a plurality of regulator holes 21 at first diffuser 2, first round corner section is connected with second diffuser 7, second diffuser 7 is connected with second round corner section that the second turning guide vane 8 is housed, second round corner section is connected with the input end of pressure-stabilizing section 3, port at pressure-stabilizing section 3 is provided with honeycomb 9, damping screen 10 is installed in pressure-stabilizing section 3, the output terminal of pressure-stabilizing section 3 docks with the port of the contraction section 4 that is five power shrinkage curve shapes, the output terminal of contraction section 4 is connected with the experimental section 5 of remaining silent, and offers be used to the view window 51 of checking situation in the experimental section 5 of remaining silent at experimental section 5.
A kind of reverse-flow type experiment wind-tunnel of the present utility model, in use, the power resources of total system are in power section 1, the single flow blower fan is housed on the power section 1, power source as total system, air-flow through first diffuser 2 after, behind the first turning guide vane 6, pass through first round corner section, then through second diffuser 7, and through the preliminary rectification of the second turning guide vane, 8 back arrival honeycombs 9 realizations, then enter pressure-stabilizing section 3, air-flow is realized pressure equalization for the first time in pressure-stabilizing section 3, be provided with damping screen 10 in the pressure-stabilizing section 3, and its effect is the turbulence vortex fragmentation that makes in the air-flow, it is uniform and stable that air-flow further becomes, then enter contraction section 4, air-flow is realized evenly accelerating in contraction section 4, after accelerating to finish, leave contraction section 4 and enter the experimental section 5 of remaining silent, the experiment air-flow environment of uniform and stable and low turbulent flow is provided for experimental section.
Be enlightenment with above-mentioned foundation desirable embodiment of the present utility model, by above-mentioned description, the related work personnel can carry out various change and modification fully in the scope that does not depart from this utility model technological thought.The technical scope of this utility model is not limited to the content on the instructions, must determine its technical scope according to the claim scope.
Claims (3)
1. a reverse-flow type is tested and is used wind-tunnel, it is characterized in that: comprise be used to the power section that power source is provided (1), first diffuser (2) that is connected with power section (1), the pressure-stabilizing section (3) that is connected with first diffuser (2) and the contraction section (4) that is connected with pressure-stabilizing section (3) and the experimental section of remaining silent (5), second round corner section that is communicated with first round corner section that the first turning guide vane (6) is housed and second diffuser (7) between the input end of the output terminal of described first diffuser (2) and pressure-stabilizing section (3) successively and the second turning guide vane (8) is housed, the port of described pressure-stabilizing section (3) is provided with honeycomb (9), damping screen (10) is installed in the pressure-stabilizing section (3), the outer wall of described contraction section (4) is five power shrinkage curve shapes, and the output terminal of described contraction section (4) is connected with the experimental section of remaining silent (5).
2. wind-tunnel is used in a kind of reverse-flow type experiment according to claim 1, it is characterized in that: offer on the described experimental section of remaining silent (5) be used to the view window (51) of checking the interior situation of the experimental section of remaining silent (5).
3. wind-tunnel is used in a kind of reverse-flow type experiment according to claim 1, it is characterized in that: offer a plurality of regulator holes (21) on described first diffuser (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220681793 CN203053672U (en) | 2012-12-12 | 2012-12-12 | Wind tunnel for reflux type experiments |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220681793 CN203053672U (en) | 2012-12-12 | 2012-12-12 | Wind tunnel for reflux type experiments |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203053672U true CN203053672U (en) | 2013-07-10 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220681793 Expired - Fee Related CN203053672U (en) | 2012-12-12 | 2012-12-12 | Wind tunnel for reflux type experiments |
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| Country | Link |
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| CN (1) | CN203053672U (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104316286A (en) * | 2014-08-26 | 2015-01-28 | 中国直升机设计研究所 | Low-turbulence design method of rotor wing pneumatic testing stand |
| CN105509929A (en) * | 2015-12-21 | 2016-04-20 | 中国燃气涡轮研究院 | Backflow type high temperature hot wind tunnel structure |
| CN105572422A (en) * | 2014-10-13 | 2016-05-11 | 辽宁省计量科学研究院 | High performance wind speed detection system |
| CN106017854A (en) * | 2016-07-14 | 2016-10-12 | 山东科技大学 | Dust environment simulation and measurement system |
| CN107436220A (en) * | 2017-07-19 | 2017-12-05 | 国网福建省电力有限公司 | A kind of reverse-flow type frequency control multi-fan array wind-tunnel and its test method |
| CN108931663A (en) * | 2017-05-22 | 2018-12-04 | 深圳木瓦科技有限公司 | Sensor and the method for utilizing the sensor measurement wind speed and direction |
| CN112109920A (en) * | 2020-09-01 | 2020-12-22 | 长沙神弓信息科技有限公司 | Unmanned aerial vehicle multi freedom attitude test system |
-
2012
- 2012-12-12 CN CN 201220681793 patent/CN203053672U/en not_active Expired - Fee Related
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104316286A (en) * | 2014-08-26 | 2015-01-28 | 中国直升机设计研究所 | Low-turbulence design method of rotor wing pneumatic testing stand |
| CN104316286B (en) * | 2014-08-26 | 2018-04-27 | 中国直升机设计研究所 | A kind of rotor aerodynamic testing platform low turbulence design method |
| CN105572422A (en) * | 2014-10-13 | 2016-05-11 | 辽宁省计量科学研究院 | High performance wind speed detection system |
| CN105509929A (en) * | 2015-12-21 | 2016-04-20 | 中国燃气涡轮研究院 | Backflow type high temperature hot wind tunnel structure |
| CN106017854A (en) * | 2016-07-14 | 2016-10-12 | 山东科技大学 | Dust environment simulation and measurement system |
| CN108931663A (en) * | 2017-05-22 | 2018-12-04 | 深圳木瓦科技有限公司 | Sensor and the method for utilizing the sensor measurement wind speed and direction |
| CN107436220A (en) * | 2017-07-19 | 2017-12-05 | 国网福建省电力有限公司 | A kind of reverse-flow type frequency control multi-fan array wind-tunnel and its test method |
| CN112109920A (en) * | 2020-09-01 | 2020-12-22 | 长沙神弓信息科技有限公司 | Unmanned aerial vehicle multi freedom attitude test system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130710 Termination date: 20131212 |