CN111307395A - Large-caliber multi-channel straight-flow wind tunnel - Google Patents
Large-caliber multi-channel straight-flow wind tunnel Download PDFInfo
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- CN111307395A CN111307395A CN202010158263.0A CN202010158263A CN111307395A CN 111307395 A CN111307395 A CN 111307395A CN 202010158263 A CN202010158263 A CN 202010158263A CN 111307395 A CN111307395 A CN 111307395A
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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
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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
- G01M9/04—Details
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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
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
- G01M9/065—Measuring arrangements specially adapted for aerodynamic testing dealing with flow
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- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a large-caliber multichannel straight-flow wind tunnel, which relates to the technical field of wind tunnel test devices and comprises the following components: the device comprises a wind tunnel body and a confluence disc arranged at an inlet of the wind tunnel body; the wind tunnel body is equipped with the stable section from the entry to the export in proper order, the contraction section, the test section, extension section and output section, be equipped with a plurality of collecting pipes on the cylinder manifold, be connected with power fan on a plurality of collecting pipes respectively, the test section is equipped with puts the thing platform, be equipped with the observation window with putting the corresponding position of thing platform on the outer wall of wind tunnel body, be equipped with the transparent window lid of detachable on the observation window, the output section is equipped with the anemoscope, this wind tunnel has solved can't realize the high velocity draught at the test section under current condition, and the high velocity flow dynamics is experimental difficult, test cycle length, the high scheduling problem of expense, and the problem of current wind tunnel.
Description
Technical Field
The invention relates to the technical field of wind tunnel test devices, in particular to a large-caliber multi-channel straight-flow wind tunnel.
Background
The wind tunnel, i.e. wind tunnel laboratory, is a pipeline-shaped test device which generates and controls airflow in a manual mode, is used for simulating the flowing condition of air around an aircraft or an entity, tests the effect of the airflow on the entity and observes physical phenomena, and is one of the most effective and most commonly used tools for aerodynamic tests.
At present, China has wind tunnels of low speed, high speed, super high speed, shock wave, electric arc and the like. The conventional wind tunnel equipment has the defects of insufficient power of a power fan for testing, long test period and high cost, and cannot meet the product tests of scientific research institutions, universities and certain equipment manufacturers.
Disclosure of Invention
The invention aims to provide a large-caliber multi-channel straight-flow wind tunnel, which can adjust high-speed airflow realized by a high-power fan under the condition of the conventional power fan, solves the problems that the high-speed airflow cannot be realized in a test section under the conventional condition, the high-speed airflow dynamics test is difficult, the test period is long, the cost is high and the like, provides a solution for realizing the high-speed airflow test under the conventional condition, and provides a reliable test platform for scientific research institutions, universities and equipment manufacturers.
The technical scheme for solving the technical problems is as follows:
a large-caliber multichannel straight-flow wind tunnel comprises: the device comprises a wind tunnel body and a confluence disc arranged at an inlet of the wind tunnel body; the wind tunnel body is equipped with stabilizing section, shrink section, test section, extension section and output section from the entry to the export in proper order, is equipped with a plurality of collecting pipes on the cylinder manifold, is connected with power fan on a plurality of collecting pipes respectively, and the test section is equipped with puts the thing platform, is equipped with the observation window on the outer wall of pneumatic body with put the corresponding position of thing platform, is equipped with the transparent window lid of detachable on the observation window, and the output section is equipped with the anemoscope.
Be equipped with a plurality of collecting pipes on the cylinder manifold, be connected with power fan on a plurality of collecting pipes respectively, the air current in a plurality of collecting pipes assembles and gets into the stable section, but fan independent control on a plurality of collecting pipes adjusts alone, cooperates jointly and obtains required wind-tunnel test environment. The confluence disc is fixedly and hermetically connected with the stabilizing section, the tail end of the stabilizing section is fixedly and hermetically connected with the contracting section, the tail end of the contracting section is fixedly and hermetically connected with the testing section, the testing section is provided with a test object placing table, the testing section is provided with an observation window, the tail end of the testing section is fixedly and hermetically connected with the expanding section, the tail end of the expanding section is fixedly and hermetically connected with the output section, and the output section is provided with an anemoscope for measuring the air flow speed of the output section.
Further, in a preferred embodiment of the present invention, the power fan is provided with an airflow pipe, the manifold pipe extends along an axial direction of the wind tunnel body, one end of the manifold pipe is disposed in the inlet of the wind tunnel body, and the other end of the manifold pipe is disposed outside the inlet of the wind tunnel body and is communicated with the airflow pipe of the power fan.
The direction that sets up of collecting pipe and wind tunnel body is the same, can reduce the energy loss of air current in the collecting pipe, and the air current of being convenient for like of a plurality of collecting pipe air outlets assembles.
Further, in the preferred embodiment of the present invention, the cross-sectional radius of the contracting section extending from the stabilizing section to the testing section decreases linearly, the cross-sectional radius of the testing section is equal everywhere, the cross-sectional radius of the expanding section extending from the testing section to the output section increases linearly, and the cross-sectional radii of the stabilizing section and the output section are equal.
The air flow in different collecting pipes is gathered in the stable section and conveyed to the contraction section through a distance, the contraction section further accelerates the air flow, then the air flow enters the test section, the test main body is acted, and then the air flow is output through the expansion section and the output section. The sectional area of the output section and the sectional area of the test section have a fixed proportion, and the output section is provided with an anemoscope which can convert the wind speed of the test section according to the experimental data measured by the anemoscope.
Further, in a preferred embodiment of the present invention, the inner surfaces of the wind tunnel body and the collecting pipe are both smooth circular arcs.
The wind tunnel body and the inner wall of the collecting pipe are smooth arc-shaped wall surfaces, so that smooth air flow operation is ensured, and the energy loss of the air flow is reduced.
Further, in a preferred embodiment of the present invention, the wind tunnel body is made of a rigid material as a whole.
The wind tunnel is integrally provided with a rigid body framework to bear the pressure impact of airflow under the condition of low air pressure and high speed.
Further, in a preferred embodiment of the present invention, an insulating protective coating is disposed on an outer wall of the wind tunnel body.
An insulating protective layer is arranged on the outer side of the rigid body, so that the wind tunnel structure is prevented from running in an electrified mode.
Further, in the preferred embodiment of the present invention, the window cover is made of a transparent acrylic plate.
The window cover can play a role in sealing the wind tunnel test section, and the test main body can be observed through the transparent material. And the acrylic material is firm and can bear the pressure impact of air flow.
The invention has the following beneficial effects:
1. the invention adopts the confluence disc to collect the airflow of a plurality of power fans, and realizes the high-speed airflow environment required by the test through the acceleration of the contraction section, thereby solving the problem that the power of a single power fan of the existing power fan is insufficient;
2. the invention realizes the requirement of the test on the high-speed airflow speed by utilizing the existing multiple power fans through the mutual matching and the independent adjustment of the multiple power fans, compared with one high-power fan, the stability of the test can be ensured by arranging the multiple power fans, the test termination caused by the fault of one fan is avoided, and the test device has smaller integral volume and lower cost, and is suitable for product tests in scientific research institutions, universities or merchants.
Drawings
FIG. 1 is a schematic structural diagram of the present invention.
Wherein: 1-a confluence disc; 11-a collector pipe; 2-a stabilization section; 3-a contraction section; 4-test section; 41-a placing table; 42-a viewing window; 5-an extension segment; 6-an output section; 61-an anemometer; 7-a power fan; 71-gas flow tubes;
Detailed Description
The principles and features of this invention are described below in conjunction with the following drawings, which are set forth by way of illustration only and are not intended to limit the scope of the invention.
Examples
A large-caliber multichannel straight-flow wind tunnel comprises: the wind tunnel comprises a wind tunnel body and a confluence disc 1 arranged at an inlet of the wind tunnel body, wherein the wind tunnel body is integrally made of rigid materials, and an insulating protective coating is arranged on the outer wall of the wind tunnel body.
Be equipped with eight collecting pipes 11 on the cylinder manifold 1, the internal surface of wind-tunnel body and collecting pipe 11 is glossy circular-arcly, is equipped with power fan 7 on a plurality of collecting pipes 11 respectively, is equipped with airflow pipe 71 on the power fan 7, and collecting pipe 11 extends the setting along the axis direction of wind-tunnel body, and the one end setting of collecting pipe 11 is in the entry of wind-tunnel body, and the other end setting of collecting pipe 11 is outside the entry of wind-tunnel body and communicate with airflow pipe 71 of power fan 7.
The wind tunnel body is equipped with stabilizing section 2, contraction section 3, test section 4, extension section 5 and output section 6 from the entry to the export in proper order, and contraction section 3 reduces from stabilizing section 2 to the section radius linearity that 4 directions of test section extend, and the section radius everywhere of test section 4 equals, and extension section 5 increases from the section radius linearity that 4 directions of test section extend to output section 6, and stabilizing section 2 equals with the section radius of output section 6. In this embodiment, the inlet section of the test section 4 is circular, the diameter of the inlet section is 3.0m, the maximum wind speed of the inlet section of the test section 4 is 100m/s, the contraction ratio of the contraction section 3 is 7, the test section 4 is provided with the object placing table 41, the outer wall of the pneumatic body is provided with the observation window 42 at a position corresponding to the object placing table 41, the observation window 42 is provided with a detachable transparent window cover, and the window cover is a transparent acrylic plate. The output section 6 is provided with an anemometer 61.
The test process comprises the following steps: during testing, determining corresponding testing conditions, opening a window cover on an observation window 42, fixing a testing main body on an object placing table 41 of the testing section 4, closing the window cover, opening part of the power fans 7 when the wind speed required by the testing is small, opening all eight power fans 7 when the wind speed required by the testing is large, and selecting the number of the started power fans 7 by a tester according to the testing requirement to adjust the wind speed in the wind tunnel to the wind speed required by the testing; during the test, the power fan 7 collects the air flow through the collecting pipe 11 on the collecting tray 1, accelerates the air flow through the contraction section 3, conveys the air flow to the test section 4 to perform the related test on the test main body, and during the test, the power of the power fan 7 is adjusted by observing the anemoscope 61 on the output section 6, so that the accurate adjustment of the speed required by the test is realized, and the related test under the high-speed air flow is smoothly performed.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (7)
1. A large-caliber multichannel straight-flow wind tunnel is characterized by comprising: wind-tunnel body and setting are in converge dish (1) of wind-tunnel body entrance, wind-tunnel body is equipped with in proper order from the entry to the export and stabilizes section (2), shrink section (3), test section (4), extension section (5) and output section (6), it is equipped with a plurality of collecting pipes (11) on converge dish (1), it is a plurality of be connected with power fan (7) on collecting pipe (11) respectively, test section (4) are equipped with puts thing platform (41), on the outer wall of wind-tunnel body with put thing platform (41) corresponding position and be equipped with observation window (42), be equipped with the transparent window lid of detachable on observation window (42), output section (6) are equipped with anemoscope (61).
2. The large-caliber multichannel straight-flow wind tunnel according to claim 1, characterized in that an airflow pipe (71) is arranged on the power fan, the manifold (11) extends along the axial direction of the wind tunnel body, one end of the manifold (11) is arranged in the inlet of the wind tunnel body, and the other end of the manifold (11) is arranged outside the inlet of the wind tunnel body and is communicated with the airflow pipe (71) of the power fan (7).
3. A large aperture multichannel straight-flow wind tunnel according to claim 2, characterized in that the cross-sectional radius of said convergent section (3) in the direction extending from said steady section (2) to said test section (4) decreases linearly, the cross-sectional radius of said test section (4) is equal everywhere, the cross-sectional radius of said divergent section (5) in the direction extending from said test section (4) to said output section (6) increases linearly, and the cross-sectional radii of said steady section (2) and said output section (6) are equal.
4. A large aperture multichannel straight-flow wind tunnel according to claims 1 to 3 characterised in that the internal surfaces of the wind tunnel body and the collector pipe (11) are both smooth arc-like.
5. The large-caliber multichannel straight-flow wind tunnel according to claim 1, characterized in that the whole wind tunnel body is made of rigid material.
6. The large-caliber multichannel straight-flow wind tunnel according to claim 5, characterized in that an insulating protective coating is provided on the outer wall of the wind tunnel body.
7. A large aperture multichannel straight flow wind tunnel according to claim 1, characterised in that said window cover is a transparent acrylic plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010158263.0A CN111307395A (en) | 2020-03-09 | 2020-03-09 | Large-caliber multi-channel straight-flow wind tunnel |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010158263.0A CN111307395A (en) | 2020-03-09 | 2020-03-09 | Large-caliber multi-channel straight-flow wind tunnel |
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| CN111307395A true CN111307395A (en) | 2020-06-19 |
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| CN202010158263.0A Pending CN111307395A (en) | 2020-03-09 | 2020-03-09 | Large-caliber multi-channel straight-flow wind tunnel |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117147091A (en) * | 2023-07-25 | 2023-12-01 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Maintenance platform for dew point measurement of low-temperature wind tunnel test section and use method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH06137991A (en) * | 1992-10-22 | 1994-05-20 | Mitsubishi Heavy Ind Ltd | Low-noise wind tunnel |
| US20030089167A1 (en) * | 2001-11-14 | 2003-05-15 | Freightliner Llc | Vehicle wind tunnel method and apparatus |
| CN103630323A (en) * | 2013-05-22 | 2014-03-12 | 河南科技学院 | Digitized wheat lodging-resistant experiment wind tunnel |
| CN206656846U (en) * | 2017-05-08 | 2017-11-21 | 仲恺农业工程学院 | Novel agricultural small-size straight-flow low-speed wind tunnel |
| CN208938480U (en) * | 2018-03-20 | 2019-06-04 | 厦门理工学院 | A kind of wind tunnel experiment equipment for teaching |
-
2020
- 2020-03-09 CN CN202010158263.0A patent/CN111307395A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH06137991A (en) * | 1992-10-22 | 1994-05-20 | Mitsubishi Heavy Ind Ltd | Low-noise wind tunnel |
| US20030089167A1 (en) * | 2001-11-14 | 2003-05-15 | Freightliner Llc | Vehicle wind tunnel method and apparatus |
| CN103630323A (en) * | 2013-05-22 | 2014-03-12 | 河南科技学院 | Digitized wheat lodging-resistant experiment wind tunnel |
| CN206656846U (en) * | 2017-05-08 | 2017-11-21 | 仲恺农业工程学院 | Novel agricultural small-size straight-flow low-speed wind tunnel |
| CN208938480U (en) * | 2018-03-20 | 2019-06-04 | 厦门理工学院 | A kind of wind tunnel experiment equipment for teaching |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117147091A (en) * | 2023-07-25 | 2023-12-01 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Maintenance platform for dew point measurement of low-temperature wind tunnel test section and use method |
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Application publication date: 20200619 |